new 1 sly mission profile as - 503 saturn launch vehicle … · 2018. 1. 14. · 1.1.1 launch 1.1.2...
TRANSCRIPT
-
FCOO4 9/3/58
NATIONAL AERONAUTICS AND SPACE ADMINISTRATION
SATURN LAUNCH VEHICLE SYSTEMS HANDBOOK
AS-503
SEPTEMBER 3, 1968
PREPARED BY
MARSHALL SPACE FLIGHT CENTER/FLIGHT CONTROL OFFICE
FLIGHT CONTROL DIVISION
1 SLY MISS ION PROF IL E AS - 503
2 SEQUENT I A L
SYSTEMS
3 ELECTR ICAL POWER SYSTEMS
4 ENV I RONMENTAL CONTROL SYSTEM
5 INSTRU/
COMMUN ICA nON SYSTEM
6 GU I DANCE AND
NAVIGA T ION SYS T EM
7 CONTROL
8 PROPULS ION AND
STRUC TURES
9 EMERGENCY
DETECT ION SYSTEM
,.; ;~~ . I ~ ~: ~ ')1 IOINTERFACE . • ( ~, ' MANNED SPA CECRAFT C ENTER ..... SY_STE_Ms_-I
'..,; ~C: .... ~)! H OUSTON,TEXAS • • 'O(.
::;
1 T PGM ---n.. S
SUBJECT ( ::.L
LOC u _ -
,~
A C K NOW LED G MEN T
The flight control systems data as presented in this document was prepared by the MSFC Flight Control Team. Team members contributing to this document include Flight Controllers from the following flight control elements:
System Engineering Office, Astrionics Laboratory, International Business Machines Corporation, McDonnell-Douglas Astronautics Company.
iii
~. \ ,
*
APOLLO
SATURN LAUNCH VEHICLE SYSTEMS HANDBOOK
AS-503
PREFACE
This handbook has been prepared by the Marshall Space Flight Center/ Flight Control Office, and Flight Control Division, Manned Spacecraft Center, Houston, Texas. Information contained within this handbook represents the Saturn Launch Vehicle Systems AS-503 as of September 3, 1968.
Information as shown, reflects the launch vehicle systems with major emphasis on material for use by flight control personnel in real time; however, caution should be exercised in using these systems drawings for any purpose other than flight control.
Comments and questions concerning this handbook are solicited and should be referenced to the Marshall Space Flight Center/Flight Control Office located at the Manned Spacecraft Center, Houston, Texas.
Approved by:
R. Scott Hamner Manager, Marshall Space Flight
Center/Flight Control Office
Concurrence by:
Control Division
ii
* CONTENTS
Section
1 SLV MISSION PROFILE
1.1 DESCRIPTION OF SLV MISSION AND VEHICLE
1.1.1 Launch
1.1.2 S-IVB First Burn
1.1.3 Parking Orbit Coast
1.1.4 S-IVB Second Burn
1.1.5 S-IVB Third Burn
1.1.6 Orbital Safing
2 SEQUENTIAL SYSTEMS
2.1 GENERAL
2.2 DEFINITION OF TIME BASES FOR TIME SEQUENCING
2.3 FLIGHT SEQUENCE PROGRAM
2.4 INTRODUCTION TO SWITCH SELECTOR CONTROL COMMANDS
2.4.1 IU Switch Selector Functions (Octal)
2.4.2 S-IVB Switch Selector Functions (Octal)
2.4.3 S-II Switch Selector Functions (Octal)
2.4.4 S-IC Switch Selector Functions (Octal)
2.5 SWITCH SELECTOR CROSS-REFERENCE TABLES
2.6 SWITCH SELECTOR NOTES
3 ELECTRICAL POWER SYSTEMS
3.1 GENERAL NOTES
3.2 IU ELECTRICAL SYSTEM
3.3 S-IVB ELECTRICAL SYSTEM
4 ENVIRONMENTAL CONTROL SYSTEM
4.1 ENVIRONMENTAL CONTROL SYSTEM NOTES
5 INSTRUMENTATION/COMMUNICATION SYSTEM
5.1 DIGITAL COMMAND SYSTEM
5.1.1 Purpose
5 .1. 2 General
5.1.3 Modulation Technigues
5.1.4 MSFN Command Loads
iv
Page
1-1
1-1
1-1
1-2
1-2
1-2
1-3
1-3
2-1
2-1
2-2
2-7
2-8
2-8
2-30
2-57
2-74
2-81
2-91
3-1
3-1
3-2
3-10
4-1
4-1
5-1
5-1
5-1
5-1
5-1
5-2
*
Section
5.1.5 Decoder Bit Coding and Timing
5.1.6 Data Verification
5.1.7 TM Data for Command System Analysis
5.2 TELEMETRY SYSTEMS
5.3 DESCRIPTION OF THE S-IVB TAPE RECORDER
6 GUIDANCE AND NAVIGATION SYSTEM
6.1 BOOST PHASE GUIDANCE
6.2 ORBITAL PHASE GUIDANCE
6.3 GUIDANCE AND NAVIGATION ALIGNMENT
6.4 GYRO AND ACCELEROMETER SERVO SYSTEM
6.5 ACCELEROMETER SIGNAL CONDITIONER
6.6 LAUNCH VEHICLE DATA ADAPTER
6.7 LAUNCH VEHICLE DIGITAL COMPUTER
6.8 NOTES - CIU
7 CONTROL
7.1 DEFINITION OF THE CONTROL SYSTEM
7.2 CONTROL SYSTEM OPERATION
7.3 CONTROL SYSTEM REDUNDANCY
7.4 CONTROL SYSTEM GENERAL NOTES
7.5 CONTROL SIGNAL PROCESSOR CHARACTERISTICS
8 PROPULSION AND STRUCTURES
8.1 S-IC STAGE
8.1.1 Propulsion and Structures
8.1.2 Staging
8.1.3 RP-1 Pressurization
8.1.4 LOX Pressurization
8.1.5 S-IC Pneumatic Control S;y:stem
8.1.6 F-1 Engines
8.1. 7 S-IC H;y:draulic S;y:stem
8.2 S-II STAGE
8.2.1 Propulsion and Structures
8.2.2 Staging S;y:stems Operation
v
Page
5-2
5-3
5-4
5-5
5-14
6-1
6-1
6-9 6-11 6-12
6-13
6-15
6-20
6-37
7-1
7-1
7-3
7-12
7-14
7-22
8-1
8-1
8-1
8-4
8-10
8-13
8-18
8-21
8-26
8-28
8-28
8-31
*
Section
8.3
8.2.3 S-II LH2 Pressurization
8.2.4 LOX Pressurization
8.2.5 S-II Pneumatic Control
8.2.6 J-2 Engine S;y:stem
8.2.7 S-II H;y:draulic S;y:stem
S-IVB STAGE
8.3.1 Propulsion
8.3.2 Structures
8.3.3 Staging
8.3.4 LH2 Pressurization
8.3.5 LOX Pressurization
S;y:stem
8.3.6 Propellant Chilldown Subsystem
8.3.7 Pneumatic Control S;y:stem
8.3.8 Propellant Utilization
8.3.9 J-2 Engine
8.3.10 H;y:draulics System
8.3.11 Auxiliary Propulsion
9 EMERGENCY DETECTION SYSTEM
9.1 GENERAL NOTES
9.2 SC-SLV INTERFACE REQUIREMENTS
9.3 S-IVB RANGE SAFETY SYSTEM
9.3.1 Range Safet;y:
10 INTERFACE SYSTEM
vi
Page
8-35
8-38
8-41
8-43
8-49
8-54
8-54
8-54
8-56
8-59
8-63
8-66
8-68
8-70
8-72
8-76
8-80
9-1
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9-2
9-10
9-10
10-1
SATURN LAUNCH VEHICLE SYSTEMS HANDBOOK
AS-503 Symbols
To be provided later.
vii
1 1
1.1.1
SECTION 1
SLY MISSION PROFILE
DESCRIPTION of SLY MISSION AND VEHICLE
SLY AS-503
The 1961 flight of AS-501 provided an initial demonstration
of the flight planning and hardware design of the Saturn V vehi
cle. The flight of AS-503 will be the first manned flight of
this configuration. The primary purpose of this mission will
be to demonstrate the capability of the launch vehicle,
spacecraft, astronaut crew, and ground support facilities to
perform the lunar orbital rendezvous (LOR) mission operations.
These capabilities will be shown in an earth orbital mission,
figure 1.1.
The Saturn V launch vehicle will rise from pad 39A of Kennedy
Space Center (KSC) carrying the S-IVB stage, a lunar module
(1M) and a command and service module (CSM) containing a crew
of three astronauts. The S-IVB will burn once to establish
a 100 n.mi. circular parking orbit. During the second and
third revolutions, the CSM will separate, transpose, and dock
with the 1M/S-IVB. The CSM/1M will then separate from the
S-IVB. The S-IVB will then burn a second time, then coast
on the outward leg of 109 by 1,800 n.mi. elliptical orbit.
The third burn phase will place the S-IVB into an earth escape
trajectory. An orbital safing will be conducted after the
termination of this third burn.
Launch
The AS-503 vehicle will be launched from the KSC Launch
Complex 39A on a launch azimuth of 90°. Shortly after tower
clearance, the vehicle will execute a pre programed pitch and
roll maneuver to a trajectory with a 12° east of north flight
azimuth.
1-1
1 SLY MiSSION PROFILE AS-!503
1.1.2
1.1.3
1.1.4
SLY AS-503
S-IC stage engine shutdown will be initiated by propellant
level sensor actuation. The spent S-IC stage will be separated
1 second later and will impact approximately 350 n.mi. down
range.
After coasting for approximately 3 seconds, the S-11 stage
ignition occurs. The aft interstage and the launch. escape
tower are jettisoned approximately 30 seconds later. Engine
shutdown for the S~11 stage is initiated by the actuation of
the low-level propellant sensors. At approximately 520 seconds
after liftoff, the S-11 will be separated.
S-IVB First Burn
The S-1VB engine start sequence is initiated 0.2 seconds
following S-11 stage separation. The S-IVB first burn duration
is approximately 152 seconds measured from Engine Start com
mand. At the end of the first S-IVB burn, the iterative
guidance system will have steered the vehicle into a 100 n.mi.
circular orbit.
Parking Orbit Coast
The vehicle will coast in the parking orbit for 4-1/2 hours
during which time transposition and docking of.the CSM with
the 1M and the extraction of the 1M from the S-1VB stage will
occur. A service propulsion system (SPS) ignition to propel
the spacecraft onto an intermediate ellipse, for further
manned orbital operations, will then take place.
S-IVB Second Burn
Shortly after 4-1/2 hours, when adequate separation distance
between the spacecraft and the S-IVB has been assured, the
S-IVB stage will reignite and burn for approximately 70 seconds
1.1.5
1.1.6
SLV AS-503
measured from the time of 90 percent thrust. This burn phase
will insert the S-IVB/IU into an approximate 109 by 1,800 n.mi.
elliptical orbit. Following S-IVB second cutoff, the vehicle
will coast in the intermediate orbit for approximately 80 minutes.
S-IVB Third Burn
After the 80-minute coast, the S-IVB will burn for the third
time at a constant vehicle attitude for approximately 220 seconds
measured from the time of 90 percent thrust. This burn phase
will propel the S-IVB/IU onto an earth escape orbit.
Orbital Safing
After third burn cutoff, the S-IVB safing procedures are enabled.
The 10- to 20,000 pounds of residual propellants will then be
dumped through the main LOX and fuel valves and out of the
J-2 engine bell. Propellant tank vents will then be opened.
All other high pressure containers will be vented.
1-3
I-' I
+=" PARKING ORBIT
S-IC, S-II, AND S-IVB BOOST TO PARKING ORBIT
'\. THIRD S-IVB "'- BURN
FINAL ORBIT (EARTH ESCAPE)
---NOMINAL (THIRD S-IVB BURN) ---CONTINGENCY (SECOND S-IVB BURN)
Figure 1.1. AS-503 D Mission Profile
-v -503N
* SECTION 2
SEQUENTIAL SYSTEMS
SLY AS-503
2.1 GENERAL
A. Sequential operations (control of discrete functions) in
the Saturn Launch Vehicle are controlled by the Launch
Vehicle Digital Computer (LVDC) through the Launch Vehicle
Data Adapter (LVDA) either directly through output discrete
commands, or through the switch selector located in each
of the stages. The switch selector output drives relays
located either in the unit affected, or in the stage
sequencer.
B. The switch selector provides for isolation of power between
the separate stages. The inputs utilize 28 Vdc from the
IU while each stage switch selector output operates from
28 Vdc supplied by the stage in which the switch selector
is located.
2-1
2 SEQUENTIAL SYSTEMS
*
2.2
SLV AS-503
DEFINITION OF TIME BASES FOR TIME SEQUENCING
A. General
The Launch Vehicle Flight Sequence Program contains nine
primary time bases and three alternate time bases in order to
achieve an optimum vehicle mission with suitable sequential
operation and timing of flight vehicle events.
Safeguards are used where necessary to prevent premature
initiation of time bases.
Proper establishment of time bases provide a safe and
reliable vehicle on the pad and throughout the flight.
Each time base will be established by the normal method
when the required criteria, as outlined in MSFC lCD 40M33623,
have been received by the Launch Vehicle Digital Computer
(LVDC).
If a time base is not established, subsequent time bases
cannot be started and the vehicle mission cannot be com
pleted. Therefore, to further increase mission reliability
in the absence of the normal time base signals, backup
methods are used for establishing time bases.
Both the normal and backup methods for starting each time
base are explained in the following paragraphs.
B. Time Base #1 (TI
)
Time Base #1 (TI
) is initiated by a liftoff signal provided
by the deactuation of the liftoff relay in the IU at the
umbilical disconnect. However, as a safety measure, the
Launch Vehicle Digital Computer (LVDC) will not recognize
the liftoff signal and start Tl prior to receiving guidance
reference release plus 16.0 seconds (liftoff - I second).
A backup method for starting T1 is provided should the LVDC
fail to receive or recognize the liftoff signal. If Tl is
2-2
6D31
ESE cmd on
KI0
Command AZUSA trans power power
Off SS 104 chan 98
ESE .. -~cmd
off
SW SEL 603A17J3
6D31
28Vdc
28Vdc KI0
Power on Power on
AZUSA RF filter assy (603A426) and AZUSA transponder (603A427)
Figure 2-6
2-16
SLV AS-503
SLY AS-503
C-band transponder control
ESE cmd no. 1 inhibit
No.1 inhibit
55114 chan 55
Both on
SS 164 chan 54
ESE cmd both on
6031*----... .28Vd
K21 c Ln. _
1- -
-
. C-band no. 1
inhibit on
C-band transponder no. 1 603A635
Figure 2-5 2-15
No.2 inhibit
SS 124 chan 56
C SW SEL 603A17J3
ESE cmd no.2 inhibit
K22 ..n.1 ~6D31 28 Vdc
1---
.. C-band no. 2
inhibit on
C-band transponder no. 2 602A634
SLY AS-503
N , ..... ~
Inhibit no.1 simulate • ESE
• ,.. I From SIC
K1
Command S-IC two engines out auto abort
SW SEL 603A17J2
Inhibit no.2 • I simulate
ESE
• I. . From • SIC
Kl
Inhibit on
55036 chan 35
p
ESE
I I I
Inhibit enable
on 55016 chan 51
N
ESE
I • K20 ..J.-o K19 ).-0>------
Inhibit no.3 • I simulate
ESE
• 14 I From SIC
A6
bOll 28 Vdc
{
I K1 .. :{ ..
~ . 6095 Two-engs out (+28V) A7 ~o I ~:~iUd under
~ K1 .. .bort conditio ... ' I A8 T 3 >~ K A6 ......,. ",r
K1 .. ~< o
'" Figure 2-4
'" , .... '"
SW SEL 603A17J2
To SIC -(S-IC/S-I[ eng no.l or S-NB eng out>
Out
Lamp B
K91
K63
See figure 2.1
B on
55163 chan 11
~ EDS bus no.3
Command S-NB engine out indication enable
B reset
SS 041 chan.53
ESE reset group 1
602AS
ESE reset group 2
K93 K92 See figure 2.1
A reset
SS 063 chan 18
a
S-NB • S-IVB ~dCTOkA T ok B
I S-IVB S-IVB stage aft bat.
• no. 1
Figure 2.3
A on
SS 023 chan 9
FF
K6
To S/C-(S-IC/S-I[ eng no.l or S-NB eng out)
Out
Lamp A
! 602A5 ~ K89 See figure 2.1
-EDS bus no.l
>11> II>r ,< .... 0 ....
* SLV AS-503
not initiated by 17.5 seconds after guidance reference
release, the LVDC will monitor the vertical accelerometer.
If a significant positive acceleration (in excess of Ig)
exists, the LVDC assumes that liftoff has occurred and
begins Tl • A time adjustment is made by the computer.
No "negative backup" (i. e., provisions for the LVDC to
return to prelaunch conditions) is provided because the
Saturn V vehicle could safely complete Tl on the pad with
out catastrophic results, in the event Tl began by error.
C. Time Base #2 (T2 )
The S-IC inboard engine will be cut off by the LVDC through
the S-IC switch selector at a predetermined time. The LVDC
will monitor the downrange accelerometer. If sufficient
downrange velocity exists, the LVDC will start Time Base #2
(T2
) •
Use of the downrange velocity reading provides a safeguard
against starting T2 on the pad should Tl be started without
liftoff. Furthermore, if T2 is not established, no subse
quent time bases can be started. This insures a safe
vehicle requiring at least one additional failure to render
the vehicle unsafe on the pad.
D. Time Base #3 (T3
)
Time Base #3 (T3
) is initiated at S-IC outboard engines
cutoff by either of two redundant outboard engines cutoff
signals. However, the LVDC must arm outboard engines pro
pellant depletion cutoff prior to starting T3
. Outboard
engines propellant depletion cutoff relay is armed prior to
predicted outboard engines cutoff.
E. Time Base #4 (T4)
After arming S-II/LOX depletion cutoff sensors, the LVDC
will initiate Time Base #4 (T4) upon receiving either of
2-3
* 8LV A8-503
two signals, 8-11 engines cutoff or 8-11 engines out. The
S-II engines depletion cutoff signal is the primary signal
for starting T4' The S-II engines out signal from the
thrust OK circuitry is a backup. A redundant S-II cutoff
command is issued at T4 + 0.0.
F. Alternate Time Base #4a (T4a)
Time Base #4a will be initiated by spacecraft initiation
of S-II/S-IVB separation. The starting of Time Base #4a
will be inhibited until T3 + 1.3 seconds. This time base
and its sequence of events will be programed for use in
early staging of the S-IVB stage.
If T4a is used, the LVDC will return to primary Time Base #5
at S-IVB cutoff.
G. Time Base #5 (T5
)
Time Base #5 is initiated by any two of the following four
inputs to the LVDC.
1. J2 engine out "A" LVDC interrupt from the engine thrust
not okay switch A.
2. J2 engine out "B" LVDA discrete input from the engine
thrust not okay switch B.
3. The command from the LVDC indicating that the proper
velocity has been achieved.
4. Loss of thrust indicated by a program check of the
8T124 platform accelerometers.
As a safeguard against starting T5 with the engine operating,
the LVDC will issue a redundant cutoff command at the start
of T5•
H. Time Base #6 (T6)
The starting of Time Base #6 will be inhibited in the LVDC.
This inhibit (restart inhibit) must be removed prior to the
LVDC solving the restart equation by DCS Command. After a
predetermined time in Time Base #5 (approximately 15, 113
2-4
*
SLY AS-503
seconds) and with the restart inhibit removed, Time Base #5
will be initiated by the LVDC upon solving the restart
equation.
I. Alternate Time Base #T6a (T6a )
Alternate Time Base T6a will be programed for use should
the 02 - H2 burner malfunction between the times T6 + 48.0
seconds and T6 + 496.9 seconds. This alternate time base
will be initiated by the LVDC upon receiving a "02 - H2
Burner Malfunction" signal from the S-IVB stage. The LVDC
returns to Time Base (T6) after completion of the events
in Time Base T6a .
J. Time Base #7 (T7 )
Time Base #7 is initiated in the same manner as Time Base
#5 with the exception that a time, T6 + 585 seconds, replaces
the velocity cutoff condition in the initiation logic. Any
two of the four will start Time Base T7'
K. Time Base #8 (T8)
The starting of Time Base #8 will be inhibited in the LVDC.
This inhibit (restart inhibit) must be removed by DCS com
mand prior to a predetermined time in Time Base #5 (T6 +
4981.0 seconds) to allow initiation of T8'
If Time Base #7 has been initiated and the restart inhibit
removed, the LVDC will initiate Time Base #8 at 4990.0
seconds after first restart equation convergence (T6 + 4990.0
seconds) •
L. Time Base #8a (T8a )
This alternate time base will be programed for use in the
event Time Base #6 is not initiated and a second burn of
the S-IVB stage is· desired.
The starting of Time Base #8a will be inhibited in the
LVDC. This inhibit (restart inhibit) must be removed by
2-5
* SLV AS-503
DCS command prior to a predetermined time from LVDC re
start equation convergence (convergence + 5621.0 seconds).
With the inhibit remQved and Time Base #6 not having been
initiated, T8a will be initiated 5630.4 seconds after
equation convergence.
M. Time Base #9 (T9
)
Time Base #9 will start after receiving any two of the
four functions monitored by the LVDC, same as Time Base
#7 (T7
)·
This time base will be programed for use in the nominal
sequence as the second orbital coast time base following
S-IVB restart.
2-6
*
2.3 FLIGHT SEQUENCE PROGRAM
SLY AS-503
The flight sequences of events is not incorporated in this
handbook since frequent and late changes to the flight program
does not lend itself to meeting the scheduled completion date
of this document.
Consequently, it is incumbent on the user to obtain an updated
copy of the Interface Control Document, MSFC, 40M33623, for
this information.
2-7
SLV * AS-503
2.4 INTRODUCTION TO SWITCa SELECTOR CONTROL COMMANDS
2.4.1
CH CODE
000 37 001
5 002 30 003 74 004 81 005 97 006 63 007
010 87 011
111 012 94 013 49 014 14 015 51 016 39 017
020 16 021 24 022 9 023
75 024 109 025
82 026 71 027
030 68 031 57 032 96 033 33 034
7 035 35 036 17 037
Switch selector controlled commands, and the channel designa
tion, are organized so that the IU, S-IVB, S-II, and S-IC are
independently listed in paragraphs 2.4.1, 2.4.2, 2.4.3, and
2.4.4. Switch selector functions labeled as spares are not
wired for use on this mission.
IU Switch Selector Functions (Octal)
SPARE SPARE SPARE
FUNCTION FIGURE NO.
COMMAND FLIGHT CONTROL COMPUTER S-IVB BURN MODE ON "B" 2.1 COMMAND S-IVB RESTART ALERT OFF 2.1 SPARE COMMAND CCS COAX SWITCH-FAIL SAFE-HIGH GAIN ANTENNA 2.13
SPARE SPARE SPARE SPARE COMMAND IU TAPE RECORDER PLAYBACK OFF 2.7 COMMAND S-IC TWO ENGINES OUT AUTO-ABORT INHIBIT ENABLE 2.4 COMMAND IU TAPE RECORDER RECORD ON 2.7
COMMAND AUTO-ABORT ENABLE RELAYS RESET 2.12 COMMAND TELEMETER CALIBRATOR STOP INFLIGHT CALIBRATE 2.9 COMMAND S-IVB ENGINE OUT INDICATION ENABLE "A" ON 2.3 COMMAND FLIGHT CONTROL COMPUTER S-IVB BURN MODE OFF "B" 2.1 COMMAND SENSOR BIAS ON 2.17 COMMAND IU COMMAND SYSTEM ENABLE 2.11 SPARE
COMMAND SPACECRAFT CONTROL OF SATURN ENABLE SPARE SPARE COMMAND SWITCH ENGINE CONTROL TO S-II AND S-IC OUTBOARD
ENGINE CANT OFF 2.1 COMMAND FLIGHT CONTROL COMPUTER SWITCH POINT NO. 7 COMMAND S-IC TWO ENGINES, OUT AUTO-ABORT INHIBIT 2.4 COMMAND IU TAPE RECORDER RECORD OFF 2.7
2-8
SLV * AS-503
CH CODE FUNCTION FIGURE NO.
040 53 041 COMMAND S-IVB ENGINE OUT INDICATION "B" RESET 2.3 23 042 COMMAND TELEMETER CALIBRATOR INFLIGHT CALIBRATE 2.9 31 043 COMMAND FLIGHT CONTROL COMPUTER S-IVB BURN MODE ON "An 2.1 61 044 COMMAND PCM COAX SWITCH-OMNI ANTENNA 2.13 93 045 SPARE
102 046 SPARE 90 047 SPARE
050 69 051 SPARE 65 052 COMMAND CCS COAX SWITCH-LOW GAIN ANTENNA 2.13 73 053 SPARE 48 054 COMMAND ENABLE S-II ENGINE OUT INDICATION ENABLE "B" ON 2.1 6 055 SPARE
52 056 SPARE 40 057 COMMAND IU TAPE RECORDER PLAYBACK ON 2.7
060 38 061 COMMAND ENABLE LAUNCH VEHICLE ENGINES EDS CUTOFF 2.14 44 062 COMMAND FLIGHT CONTROL COMPUTER SWITCH POINT NO. 5 2.2 18 063 COMMAND S-IVB ENGINE OUT INDICATION "A" RESET 2.3
110 064 COMMAND COOLING SYSTEM ELECT ASSY POWER OFF 2.17 92 065 SPARE
101 066 SPARE 67 067 SPARE
070 58 071 COMMAND CCS TRANSMITTER INHIBIT ON 2.13 64 072 COMMAND CCS COAX SWITCH-OMNI ANTENNA 2.13 95 073 SPARE 29 074 COMMAND S-IVB EDS ENGINE CUTOFF DISABLE 25 075 SPARE 36 076 SPARE
8 077 SPARE 100
21 101 COMMAND FLIGHT CONTROL COMPUTER SWITCH POINT NO. 2 2.2 46 102 COMMAND S-IVB ULLAGE THRUST PRESENT OFF 2.8 32 103 SPARE 98 104 SPARE 2.6
108 105 COMMAND H20 COOLANT VALVE CLOSED 2.16 76 106 SPARE 89 107 SPARE
llO 66 III SPARE 62 112 COMMAND PCM COAX SWITCH-HIGH GAIN ANTENNA 2.13
112 113 COMMAND MEASURING RACK (602A408) POWER OFF 2.15 105 114 SPARE 12 115 COMMAND FLIGHT CONTROL COMPUTER S-IVB BURN MODE OFF "A" 2.1 41 116 COMMAND INHIBIT EXCESSIVE P, Y & R AUTO-ABORT OFF 2.18 34 117 COMMAND EXCESSIVE ROLL AUTO ABORT INHIBIT ON 2.18
2-9
*
CH CODE
120 22 121 19 122 45 123 56 124 91 125 99 126 86 127
130 84 131
100 132 60 133 88 134 27 135 42 136
2 137 140
4 141 3 142
10 143 55 144
107 145 77 146 85 147
150 83 151 79 152 59 153 70 154 47 155 20 156 15 157
160 50 161 13 162 11 163 54 164
106 165 78 166
104 167 170
103 171 80 172 72 173 28 174 26 175 43 176 1 177
FUNCTION
SLV AS-503
COMMAND FLIGHT CONTROL COMPUTER SWITCH POINT NO. COMMAND IV TAPE RECORDER PLAYBACK REVERSE ON SPARE COMMAND C-BAND TRANSPONDER NO. 2 INHIBIT ON SPARE SPARE COMMAND S-IC OUTBOARD ENGINE CANT OFF "B"
COMMAND S-IC OUTBOARD ENGINE CANT ON "B" SPARE
3
COMMAND PCM COAX SWITCH-FAIL SAFE-LOW GAIN ANTENNA SPARE COMMAND FLIGHT CONTROL COMPUTER SWITCH POINT NO. 9 COMMAND ENABLE EXCESSIVE ROLL AUTO ABORT INHIBIT OFF COMMAND EXCESSIVE RATE (p, Y & R) AUTO-ABORT INHIBIT ON
COMMAND FLIGHT CONTROL SWITCH POINT No.4 COMMAND IV TAPE RECORDER PLAYBACK REVERSE OFF SPARE COMMAND C-BAND TRANSPONDER NO. 1 INHIBIT ON COMMAND WATER COOLANT VALVE OPEN SPARE COMMAND S-IC OVTBOARD ENGINE CANT ON "c"
COMMAND S-IC OUTBOARD ENGINE CANT ON "A" SPARE COMMAND CCS TRANSMITTER INHIBIT OFF SPARE COMMAND FLIGHT CONTROL COMPUTER SWITCH POINT NO. 8 COMMAND INHIBIT EXCESSIVE ROLL AUTO-ABORT OFF COMMAND ENABLE EXCESSIVE RATE (p, Y & R) AUTO-ABORT
INHIBIT
COMMAND INHIBIT EXCESSIVE ROLL AUTO ABORT
FIGURE NO.
2.2 2.7
2.5
2.13
2.18 2.18
2.2 2.7
2.5 2.16
2.13
2.18
2.18
2.18 COMMAND ENABLE EXCESSIVE P, Y & R AUTO-ABORT INHIBIT OFF 2.18 COMMAND S-IVB ENGINE OUT INDICATION ENABLE "B" ON 2.3 COMMAND C-BAND TRANSPONDERS NO.1 AND NO.2 ON 2.5 COMMAND S-I RF ASSEMBLY POWER OFF 2.19 SPARE SPARE
SPARE S-IVB RESTART ALERT ON 2.1 SPARE COMMAND S-II ENGINE OUT INDICATION ENABLE "An ON 2.1 COMMAND FLIGHT CONTROL COMPUTER SWITCH POINT NO. 1 2.2 COMMAND S-IVB ULLAGE THRUST PRESENT ON 2.8 COMMAND Q-BALL POWER OFF 2.10
2-10
EDS bus no. 3
602A5
~~2_ ~22-2' K23-2 J --K24-2, K25-2 tYPlca I S places ~-IC engine out
S-IC or S-II
[
engine no. lout B J typical for S engines (indicators)
A12
K1 __ IK2, K3,K4, Ksl-~yplcalS place:j
EDS bus no.1
K21-1 [ l ___ K22-1, K23-1 __ K24-1, K2S-2 tYPlcalS places S-IC engine out A
S-IC or S-II
[
engine no. lout A ] typical for S engines (indicators)
Thrust O. K. enable inhIbIt
ESE ESE A B
~02AS K89
----- - 602AS K90
K90
S-II meas, engine thrust O. K.
B
OK2, K3, K4, Ksl typical 5 places J
A
All 602AS A 12
_ __ K2, K3, K4, KS ______ _
IK2, K3, K4, KS] LtYPlca I S places
S-II aft Interstage separatIOn meas
A B
S-IVB
Command 5-II engine out indIcation enable B
On SSOS4 chan 48
ESE reset
A On
55174 chan 28
Command sWItch eng me pos Ition control from S-ICtoS-II
SS 034 chan 33
602A4A5
EDS bus no. 1 EDS bus no. 3 group 2
ESE reset group 1
AlO A4 CD K1 ® 602A5AlO
CD Kl ® K1 [ J K1 typicalS places
A4
K1~
28V v1c 1 602A5A4 J ____________ K~ ____________ Kl_ .... __ -- __
ESE reset group 2
K94-1 K94-2 K94-1 K94-2
AI0 Kl 602ASA3 602ASA9
K4 Kl
K94-1 K94-2
ESE cmd vehIcle hftoff inhibIt
K4
ESE reset group 1 603A2
® K34 CD
LVDC J2
Switch TM
meas S21S4
l::q03A2
-- ------------- ------------
m
Chan 81 SS OOS
off Command 5- IVB restart alert
Chan 80 SS 172
on
SW SEL 603Al7J3
5- II second sep A and S- IVB restart alert A
FIgure 2. 1
5 - II second sep B and S-IVB restart alert B
SIC 6D11
28 Vdc
5 -II stage •
ESEn---separatIon simulation
A L
S-IC burn
M
Off B 55024 chan 7S
6D11
S-IVB burn
Command flight control computer S-IVB burn mode
On B On A SS 004 55043 chan 74 chan 31
6D31
28~ __ _
S-IVB burn
Off A SS l1S chan 12
SW SEL 603Al7J2
SLY AS-S03
Th rust 'not OK from S48 stage
2.11
•
~----------------------------------------------------------------------------- -- ---------------------------------
LH2 REPRESS REG BACKUP
®-485-335
PS-IA
J:
ON SS 017 CH 39
MODE SELECT
CRYOGEN IC ~
OFF SS 005 CH 81
BURNER /SHUTDOWN
CIRCUIT
LH2 TANK ~ ~ GND ~lLL, ~ -
PREPRESS, 31 28 REPRESS & PSIA' FLT CONTROL PRESS SW
AMB MODE
K52-1 ,~
-=
CRYO MODE )
(fjfj--;I 31-28' PSIA
~
LH2 TANK REPRESS S\o.
I .\MgIE~!T '
1
J:
K9-1
A
TIM K184
ON SS 031 CH 68'
f-----i B
OFF SS 051
CHI 69
1 L 1 L ~ ~1~ J I ~::]::::::::::-=====±:i=::::::::;1, I L J E HEll UM ============::::t~ TO LH?
TANK SUPPLY TO 02/H2 FROM AMBI ENT BURNER HELIUM SPHERES
Commands LH2 Tank Press and Repress Valves
-
SECOND BURN RELAY
ON SS 103
CHI 32
OFF SS 034
CHI 33
- - - - -K8-1
-=
I
1 I
CONTROL I I ~ VALVE ~ I
;:1 :><
~ I
I I
~ I 1 :::: I ~ I
I
STEP',PRESS: VALVE "
-Rl-~
Lnt::: IK PK~SS CONT MOD
I
SLV AS-503N
4015 ~' ------j
(--- ---r
B
, Lr':-l ....... ' t FROM J-2 ENGINE
FIGURE ?- 2.7 2-40a
'" , .... '"
ESE reset group 2
SW SEL switch point
no.l
SS 175 chan 26
603A2A5
® Kl C9
ESE reset group 2
S-IC fI ight contro' gains
Pitch Vaw
Attitude error and att itude rate
SW SEL switch point
no.2
SS 101 chan 21
S-IC flight contro' gains
Pitch Vaw {
Att itude error and attitude rate
Control of fl ight control computer
SW SEL switch point
no.3
SS 121 chan 22
ESE reset group 2
s-rr flight control gains
Pitch Vaw
F'ight contro' computer b02A27
Figur. 2-2
Attitude error and attitude rate
SW SEL switch point
110.4
SS 141 chan 04
s-n ftitht control gains
Pitch Vaw {
Attitud. error and attitude rate
SW SEL switch point
no.5
SS 062 chan 44
SW SEL 603A17J2
Pitch Vaw
6031 28 Vd.
{Attitude rate
~'" 'f!C '" o
'"
N , .... ~
5W 5EL 603A17J2
6031 28 Vdc
Kll
Off 55142 chan 3
Playback reverse
On 55122 chan 19
E5E ~ • 14 I reset
group 1
Tape recorder playback reverse
End of tape signal
Command tape recorder
Playback
E5E reset group 1
Off 55 015 chan 14
603A2 KIO
KIa
Tape recorder playback
IU tape recorder 602A604
Figure 2-7
On 55 057 chan 40
603A2 K9
Record
On 55 017 chan 39
Off 55037 chan 17
E5E • 14 l reset
group 1
)oil> 11>1"'" ,< U1 o
'"
Command S-NB ullage thrust present
SW SEL 603A17J2
AGC bus
28 Vdc
On SS 176 chan 43
h
Off SS 102 chan 46
w
© 602AS ® ~ K26 ....
K26 - - - - - - 'o::;Oj-,-"o::IO
SIC S-IVB ullage thrust present (indicator)
Figure 2-8
2-18
SLY AS-S03
ESE reset group 2
ESE reset group 2
Command telemetry inflight calibration
Off SS 022 chan 24
On SS 042 chan 23
n SW SEL 603A17J2
603A2A4 ,0 K6 <9+
.. On
Telemetry calibrator
602A602
Figure 2.9
2-19
I I I I I 1-
- 28 Vdc 6D41
SLY AS-503
ESE
Q ball power
Off SS 177 chan 1 -7f SW SEL 603A17J2
ESE cmd on cmd .1---.....
off ® 603A2 0 .-K14 \!:I
6D41
... ... t-rr~- -~l-l-l-~--------
K14 -'-
IU
6D21
SLV AS-503
•••••••••• •••• • •••
•••••••••• PAYLOAD
Figure 2-10
2-20
Q ball power
N , N .....
ESE reset group 1
Launch vehicle data adapter
603A29
Command I U command system enable
602A5 K95-1
603A2 K51
SS 026 chan 82
u SW SEL 603A17J3
602A5 K95-2
603A2 r--_:J'J K52
K52
Figure 2-11
I U command decoder
assembly 603A450
»(f) (f)r ,< VI o w
'" , '" '"
Reset SS 021 chan 16
EOS system auto abort enable
SW SEL b03A17J2
ESE CMO auto abort system B enable
I ESE meas I I
ESE CMO . auto abort system A enablt
auto abort I I. I system B I K66 I ESE me.s enabled I 65 ..J--o I auto abort
I K I system A I I enabled
To SIC I I auto abort I • I 60119. I TO SIC enable system B K66 J..o-------, 28 Vdc K65 ~ ,auto abort
enabl. system A
EOS bus no. 3 28 Vdc K3
A
602A5 K3
To ESE
~I energized
until LlO
Figure 2-12
K2 AI
To ESE I
~~~itzed~ LlO r b02A5
K2
EOS bus no. 1 28 Vdc
»11> II> r,< '" o ...
PC" antenna
lo
Omi <Jain
SS 044 SS 133 chan 61 chan 60
6
UHFxnV
HI qall\
SS 112 ch;m 62
0,
SS 071 chan 58
CCS transmitter
inhibit
Onni .... t.
I I c 1 •• 1 ('logJ'lnant.
PCM CO<lX
switch
Hi gain ant.
Off
SS 153 chan 59
ccs Kponder
603Ab36
Figure 2.13 2-23
Omi
SS 072 c~an 64
CC' antenna
HI ga'n
SS 007 chan bJ
lo 'lain
SS 052 chan 65
603A2 >45
SWSEI.. 60JA17J3
SLV AS-50)
I ~1 ______ ~~~ ____ --1 "tv
,6D3l [ f ~6D3l I [ ____ ~ I 28Vdc I· I 1 .~--------_
14 00,""
T r--~;f} ®
ccs pwr amp
6OJA637
To ESE
CCS cnax switcn
Lo gain .,t. o i".1 CHigainant.
Ol1lli..,t.
b092 28 Vdc
6092 28 Vdc
6031 28 Vdc
Engine cutoff enable
Command engines EOS cutoff enab Ie
SS 061 chan 38
~
SW SEL 603A17J2
602ASA4 K6
ESE reset group no. 1
602AS ® K19 ®
N , K29 ------------ti:iXJ N ... 1021
28 Vdc
I K86-1 -L 1 b02AS
K8b-l
•
ESE
Meas S-IC or S-II or S-IVB eng manual cutoff enab Je command (B), received
--
2011 -:- 4031 4011 -:- 1011 28 Vdc 28 Vdc 28 Vdc 28 Vdc
- -L K8b-l K86-2 K9-1 K9-1 m1---'t---1 1---1--
--
S-IC command S-II command S-IVB command S-IVB command S-IC command engines EOS engine EOS engine EOS engine EOS engine EOS
cutoff cutoff cutoff cutoff cutoff
S-IVB interface
Figure 2-14
b02AS K9-1
-L ---
6091 28 Vdc
Relays, K40, K41-1: K41-2 and K42, L V engines EOS cutoff from spacecraft nomtallyenergized
b09l 28 Vdc
----------1 K19
b02AS K9-2
-L --
2021 28 Vdc
-1 K9-2
S-IT command engines EOS
cutoff
K19
ESE me< eng mam command
s S-IC or S-II or S-IVB al cutoff enable (Al received
>V> v>.-~< o '"
Off SS 113
chan 112
Measuring rack 602A408
Power off command
6D41
ESE cmd meas rack on
28 Vdc
K9-5
Meas rack 602A408
Figure 2.15
2-25
sw SEL 603A17J 3
ESE cmd meas pwr off
SLY AS-S03
ESE
Open SS 145
chan 107
K
Command water coo lant valve
Closed SS 105
chan 108
28 Vdc
To sub! imator .... ~--I---1
Figure 2-16
2-26
SW SEL 603A17J3
SLV AS-503
ESE cmd cooling system GN 2 fi 11 valve open
GSE I--~ fill
N , N ....
TM
6021 ~A_ 28 Vdc..,. 12K; l
Command cooling system elect
assy pwr
Off SS 064
chan 110
r--l 6021 1 '" ..,. 28 Vdc
Command sl!nsor bias
On SS 025 chan 109
R Switch s.Iector 603A17 J3
------u.:I.:I..:I • : ESE
r--I60119
1,. _r28VdO
(----------ESE
Jl A
Thermistor 601A38
B B
6021 28 Vdc
ESE
601A33 <D K18 ®
60119 28 Vdc
~.-------------------~-----
u
Cooling system electronic control assy
601A40
o Jl
Figure 2.17
ESE
ESE
601A33 K19
>'" "',.. J,< o
'"
'" • '" '"
SIN SEl f>03A17J2
Command enable excessive P, Yand R auto abort
inhibit
On SS 157 chin 15
J
Off SS 162 chin 13
ESE
160119 ~ _ 28 Vdc bOll 28 Vdc
~reset group 1
------\- ------~ K15
----- -------------
ESE measurement auto-lbort inhibit functions reset
Klb
From SIC
---
Command inhibit excessive P, Yand R
luto abort
On SS 137 chan 2
K
Off SS 116 chin 41
ESE
Command inhibit excessive rol1
auto abort
On SS 161 chin 50
M
Off SS 156 chan 20
g
f-l4-I reset group 2
From SIC
K18
Command inhibit excessive roll
auto abort
On SS 117 chan 34
Off SS 136 chan 42
ESE meas auto abort inhibit functions reset
b0119 28 Vdc
ESE I. . I I • ~. • .1 • 14. • I ESE
Excessive 1--... __ roll "te , ..
.. --""'0 • ..
Figure 2-18
Excessive roll rate
Excessive pitch rate
Excessive 1. .. yaw rate
6095 abort bus (energize under abort conditions)
>VO VOr v,< o W
N I
N -D
J1
Off SS 165
chan 106
Sl RF assy power
, I ESE
K
Sl RF assy 602A597
Power on
Figure 2-19
Switch selector
603A17J3
.--*"6041 1 "'28Vdc
l>Vl Vlr G,< o \J)
2.4.2 S-IVB Switch Selector Functions (Octal)
SLV AS-503
CH Code Function
000
Figure No.
37 001
5 002
30 003
74 004
81 005
97 006
63 007
010
87 011
III 012
94 013
49 014
14 015
51 016
39 017
020
16 021
24 022
9 023
75 024
109 025
82 026
71 027
030
68 031
57 032
96 033
33 034
7 035
35 036
17 037
040
COMMAND AMBIENT REPRESSURIZATION MODE SELECTOR OFF AND CRYOGENIC ON
COMMAND PU ACTIVATE ON
COMMAND START TANK VENT CONTROL VALVE OPEN ON
COMMAND BURNER LOX SHUTDOWN VALVE CLOSE ON
COMMAND LH2 TANK REPRESS CONTROL VALVE OPEN OFF
COMMAND POINT LEVEL SENSOR ARMING
COMMAND SPECIAL TM CALIBRATE OFF
COMMAND LH2 TANK CONTINUOUS VENT VALVE CLOSE OFF
COMMAND LH2 TANK CONTINUOUS VENT ORIFICE SHUTOFF VALVE OPEN ON
COMMAND LOX TANK VENT VALVE CLOSE
COMMAND INFLIGHT CALIBRATION MODE OFF
Dwg 8.3.2a
2.42
Dwg 8.3.8a
Dwg 8.3.2a
2.27, Dwg 8.3.2a
2.34
2.35
2.24
2.24
2.21, Dwg 8.3.3
2.35
COMMAND ENGINE MAINSTAGE CONTROL VALVE OPEN ON 2.37, Dwg 8.3.8a
COMMAND HEAT EXCHANGER BYPASS VALVE CONTROL DISABLE Dwg 8.3.3
COMMAND LH2 TANK REPRESS CONTROL VALVE OPEN ON.
COMMAND FUEL INJECTION TEMPERATURE OK BYPASS RESET
COMMAND ENGINE PUMP PURGE CONTROL VALVE ENABLE·ON
COMMAND S-IVB ENGINE START ON
COMMAND BURNER LOX SHUTDOWN VALVE CLOSE OFF
COMMAND ENGINE HELIUM CONTROL VALVE OPEN ON
COMMAND PREVALVES CLOSE ON
COMMAND BURNER EXCITERS OFF
COMMAND FIRST BURN RELAY ON
COMMAND FIRE ULLAGE JETTISON ON
2.27, Dwg 8.3.2a
2.32
2.38
2.21
Dwg 8.3.2a
Dwg 8.3.8a
2.39, Dwg 8.3.4
Dwg 8.3.2a
2.27
2.26
COMMAND LOX TAN~ VENT AND NPV VALVES BOOST CLOSE OFF 2.33
COMMAND SECOND BURN RELAY OFF 2.27
COMMAND PU INVERTER AND DC POWER ON
COMMAND PU FUEL BOILOFF BIAS CUTOFF ON
COMMAND PU VALVE HARDOVER POSITION ON
2-30
2.22
2.30
2.30a
SLV AS-503
CH Code Function Fi~re No.
53 041 COMMAND MEASUREMENT TRANSFER MODE POSITION.A 2.40, Dwg 8.3.4 23 042 COMMAND LOX CHILLDOWN PUMP OFF Dwg 8.3.8a 31 043 COMMAND START TANK VENT CONTROL VALVE OPEN OFF Dwg 8.3.2a 61 044 COMMAND BURNER LH2 PROPELLANT VALVE CLOSE OFF 2.21, Dwg 8.3.3
93 045 COMMAND LOX TANK VENT VALVE OPEN 2.36, Dwg 8.3.10
102 046 COMMAND S-IVB APS ULLAGE ENGINE RELAY #2 OFF Dwg 8.3.2a
90 047 COMMAND BURNER LOX SHUTDOWN VALVE OPEN OFF
050
69 051 COMMAND FIRST BURN RELAY OFF 2.27, Dwg 8.3.2
65 052 COMMAND PCM RF ASSEMBLY POWER OFF
73 053 COMMAND ULLAGE FIRING RESET 2.26
48 054 COMMAND INFLIGHT CALIBRATION MODE ON 2.35
6 055 COMMAND PU ACTIVATE OFF 2.42
52 056 COMMAND MEASUREMENT TRANSFER MODE POSITION B
40 057 COMMAND ENGINE IGNITION PHASE CONTROL VALVE OPEN 2.41, Dwg 8.3.8a
060
38 061 COMMAND LH2 TANK VENT VALVE OPEN'ON 2.23, Dwg 8.3.2
44 062 COMMAND LOX TANK NPV VALVE LATCH ON 2.21, Dwg 8.3;3
18 063 COMMAND PU VALVE HARDOVER POSITION OFF 2.30a
110 064 COMMAND ENGINE HELIUM CONTROL VALVE OPEN OFF Dwg 8.3.8a
92 065 COMMAND CHILLDOWN SHUTOFF PILOT VALVE CLOSE OFF 2.33, Dwg 8.3.4
101 066 COMMAND S-IVB APS ULLAGE ENGINE RELAY #2 ON 2.36, Dwg 8.3.10
67 067 COMMAND FM/FM TRANSMITTER OFF 2.41
070
58 071 COMMAND FUEL CHILLDOWN PUMP ON 2.40, Dwg 8.3.4
64 072 COMMAND LH2 TANK LATCHING RELIEF VALVE LATCH ON 2.23, Dwg 8.3.2
95 073 COMMAND LOX TANK VENT AND NPV VALVES BOOST CLOSE ON 2.21, Dwg 8.3.3
29 074 COMMAND AUXILIARY HYDRAULIC PUMP FLIGHT MODE OFF 2.25, Dwg 8.3.9
25 075 COMMAND ENGINE PUMP PURGE CONTROL VALVE ENABLE OFF 2.38 36 076 COMMAND AMBIENT REPRESSURIZATION MODE SELECTOR ON Dwg 8.3.2a
AND CRYOGENIC OFF
8 077 COMMAND PU INVERTER AND DC POWER OFF 2.22
100
21 101 COMMAND ENGINE PNEUMATIC SYSTEM VENT OPEN OFF 2.37, Dwg 8.3.8a
46 102 COMMAND SINGLE SIDEBAND FM.TRANSMITTER ON 2.41
2-31
SLV AS-503
CH ~ Function Fi!lure No.
32 103 COMMAND SECOND BURN RELAY ON 2.27, Dwg 8.3.2
98 104 COMMAND POINT LEVEL SENSOR DISARMING 2.34
108 105 COMMAND LHt
TANK CONTINUOUS VENT RELIEF OVERRIDE 2.21, Dwg 8.3.2 SHUTOFF VA VE OPEN OFF
76 106 COMMAND LH2 TANK VENT VALVE OPEN OFF 2.23, Dwg 8.3.2
89 107 COMMAND BURNER LOX SHUTDOWN VALVE OPEN ON Dwg 8.3.2a
110
66 III COMMAND FM/FM TRANSMITTER ON 2.41
62 112 COMMAND TM CALIBRATE ON 2.35
112 113 COMMAND LH2 TANK CONTINUOUS VENT ORIFICE SHUTOFF Dwg 8.3.2 VALVE OPEN OFF
105 114 COMMAND LOX TANK NPV VALVE OPEN ON 2.21, Dwg 8.3.3
12 115 COMMAND S-IVB ENGINE CUTOFF ON 2.28
41 116 COMMAND ENGINE IGNITION PHASE CONTROL VALVE CLOSE 2.31, Dwg 8.3.8a
34 117 COMMAND PU FUEL BOILOFF BIAS CUTOFF ,OFF 2.30
120
22 121 COMMAND LOX CHILLDOWN PUMP ON 2.40, Dwg 8.3.4
19 122 COMMAND LH2 TANK LATCHING RELIEF VALVE LATCH OFF 2.23, Dwg 8.3.2
45 123 COMMAND LOX TANK NPV VALVE LATCH OFF 2.21, Dwg 8.3.3
56 124 COMMAND FIRE ULLAGE IGNITION ON 2.26
91 125 COMMAND CHILLDOWN SHUTOFF PILOT VALVE CLOSE ON 2.33, Dwg 8.3.4
99 126 COMMAND LH2 TANK LATCHING RELIEF VALVE OPEN ON 2.23, Dwg 8.3.2
86 127 COMMAND BURNER AUTOMATIC CUTOFF SYSTEM DISARM Dwg 8.3.2a
130
84 131 COMMAND LH2 TANK CONTINUOUS VENT VALVE CLOSE ON 2.24, Dwg 8.3.2
100 132 COMMAND LH2 TANK LATCHING RELIEF VALVE OPEN OFF 2.23, Dwg 8.3.2
60 133 COMMAND BURNER LH2 PROPELLANT VALVE CLOSE ON Dwg 8.3.2a
88 134 COMMAND ULLAGE CHARGING RESET 2.26
27 135 COMMAND S-IVB ENGINE START OFF 2.29
42 136 COMMAND S-IVB APS ULLAGE ENGINE RELAY #1 ON 2.26, Dwg 8;3.10
2 137 COMMAND PASSIVATION DISABLE Dwg 8.3.8a
140
4 141 COMMAND LOX TANK REPRESS CONTROL VALVE OPEN OFF Dwg 8.3.2a
3 142 COMMAND LOX TANK REPRESS CONTROL VALVE OPEN ON Dwg 8.3.2a
10 143 COMMAND ENGINE READY BYPASS 2.28
55 144 COMMAND CHARGE ULLAGE JETTISON ON 2.26
2-32
CH Code
107 145
77 146
85 147
150
83 151
79 152
59 153
70 154
47 155
20 156
15 157
160
50 161
13 162
11 163
54 164
106 165
78 166
104 167
170
103 171
80 172
72 173
28 174
26 175
43 176
1 177
Function
COMMAND LHt
TANK CONTINUOUS VENT RELIEF OVERRIDE SHUTOFF VA VE OPEN ON
COMMAND LH~ TANK VENT AND LATCHING RELIEF VALVE BOOST CLOS ON
BURNER AUTOMATIC CUTOFF SYSTEM ARM
COMMAND PREVALVES CLOSE OFF
SLV AS-503
Fis;ure No.
2.24, Dwg 8.3.2
2.23, Dwg 8.3.2
Dwg 8.3.2a
2.39, Dwg 8.3.4
COMMAND LOX TANK PRESSURIZATION SHUTOFF VALVES CLOSE Dwg 8.3.3
COMMAND FUEL CHILLDOWN PUMP OFF 2.40, Dwg 8.3.4
COMMAND BURNER EXCITERS ON Dwg 8.3.2a
COMMAND SINGLE SIDEBAND FM TRANSMITTER OFF 2.41
COMMAND ENGINE PNEUMATIC SYSTEM VENT OPEN ON 2.31, Dwg 8.3.8a
COMMAND ENGINE MAINSTAGE CONTROL VALVE OPEN OFF 2.37, Dwg 8.3.3a
COMMAND HEAT EXCHANGER BYPASS VALVE CONTROL ENABLE Dwg 8.3.3
COMMAND S-IVB ENGINE CUTOFF OFF 2.28
COMMAND FUEL INJECTION TEMPERATURE OK BYPASS 2.32
COMMAND CHARGE ULLAGE IGNITION ON 2.26
COMMAND LOX TANK NPV VALVE OPEN OFF 2.21, Dwg 8.3.3
COMMAND LH~ TANK VENT AND LATCHING RELIEF VALVE 2.23, Dwg 8.3.2 BOOST CLOS OFF
COMMAND LOX TANK FLIGHT PRESSURE SYSTEM OFF Dwg 8.3.3
COMMAND LOX TANK FLIGHT PRESSURE SYSTEM ON Dwg 8.3.3
COMMAND LOX TANK PRESSURIZATION SHUTOFF VALVES OPEN Dwg 8.3.3
COMMAND BURNER LH2 PROPELLANT VALVE OPEN OFF Dwg 8.3.2a
COMMAND AUX HYDRAULIC PUMP FLIGHT MODE ON 2.25, Dwg 8.3.9
COMMAND BURNER LH2 PROPELLANT VALVE OPEN ON Dwg 8.3.2a
COMMAND S-IVB APS ULLAGE ENGINE RELAY #l OFF 2.36, Dwg 8.3.10
COMMAND PASSIVATION ENABLE Dwg 8.3.8a
2-33
GROUND COMMAND (U:,mLICAL) .... /
l_+4Dl,5 --1 -i .,.
. --I
I I :_UJ 1_1_0 ..... ...",.",..,
-::~'-:-
404A3A 1'9K6D.
TIM • ~"'~ I
KO"1551 +4015 .. ;
·ff- r-1--
r.=. .• __ ...• -, .••. - ~... ..• I I; CO:11WID LOX TANK . ~ PRESSURIZATION H SHUTOFF VALVES
i] CLOSE OPEN . S-IVB [1 rl S5 152 SS 172 . SWITCH ;j II CH 79 CH flO SELECTOR' l·_ --;u.= .~. .
o -:.r;1<'-1 - tf." -.;,-
404A3A13K34
® ,. rt -~I --;;.-
'-[-':':-~ -
u '. <..
SLY AS-503N
,FROM LOX. TANK flIGHT PRESSURIZATION SYSTEM
(SHEET , 2) -GROUND
COI/J.IAND .• ·-----11
. (UMBILICAL) . • t _ •
404A3A12K30 . .. ,---~-l"-:'l
o ---P tl ~' OPEN· I
1J . 335 PSiA ,1·
COLD HELIUM ~ COLD HELI.U.M ~ SUPPLY SUPPLY ~-: . SHUTOFF. , . SHUTOFF
.. no VALVE i ,_ VALVE i
. c::c9<J~~ , :: . ~ :~ J H COLD HELIUM REGULATOR BACKUP fi [,i'PRESSURE SWITCH 403A74S1 tl t--.. -~ ... _ .. -'-=.' -~.-.-....,..".",~j
LOX HELIUM REGULATOR PRESSURE CONTROL IIODULE 403A74Al t L", _____ , ..... :':":~c_~·:::::.':~: __ :0:: .-__ ._'Sf'..:l
LOX Tank Pressurization Control Schematic (Sheet I of 2) FIGURE 2-20 2-34
fI- • ,- -" ...... ', -"-', .' •... ,'- . - '.
1; -,-tP_~~K?-HE:ii 'Ei~i~~GEi---"'-l! BYPASS, VALVE CONTROL,
'\ "
,I ~; -ENABLE ,DISABLE Il SS 161,SS 016' II CH- 50 - - Cf-r 51 - i ~:.-...""':".-:....-~-"._:-::'.,_-:::=---- ___ o~
!; ,! ---.-.-- t' 'S-IVB' (: J ___ ~ "
! SWITCH'. :! , SELECTORtl ~:-=,.:.."":::::':"-:"::'J
~ ~COMMA~Jj-t:OX -TANIC; __ , : FLI GHT PRESSURE SYSTEM:
SLY AS-S03N
+4D15' H -_._ .. --.~.: -- . - ,----·-·-i· .... :; ON' OFF _~S-IVB" :__ _ . ;, SS 171. SS 167_.0_WITCH ':' I' I
:: CH 103' CH 104 SELECTORfi c' .i ~.--.. .....,.,,"-=,-,.:- .:-=.;::-::-..:'-.----;: ' \" In' ,,-
, 404A3A6Kll.! '? ,':;:'.:,\)::.l \' CD I I® I ,
fl ... -.- ~ I -,>ri I I -'- • t, ~ if:". ~ -::",,:- ''0'_. -- .
- -;- :<: -!- - - \- -'- ',-; -~- J - 404A3A20K74 '-"---"-' n'- '-~-...., I 404A3A8Kl S I 1'1 1 I . CRS ' - Jl~t I
. " K0102 '
, :=£ .. Zi!CL2.. z::s:;:: I '"% !It : $-.1 tl HEAT EXCHANGER LOX HELIUM t
H ~ BYPASS VALVE REGULATOR n ~ (N.O.) PRESSURE [1 "j . >r CONTROL r, ! i ..l. lJ
tl ~ MODULE tl t: L2'l :; ~J
~ 403A74Al 1 IJ __ .. _ ==--:. l....;:::: ==-:1 _~
404A3A43 I TO LOX TANK FLIGHT PRESSURI ZATTONSYS-TEM -(SHEET 1) L_+_4PJ_5-j
<.. .">
;------r---l
TO REPRESS SYSTEM
(SECTION 2.14)
I
r~.::.·-~--:-;,:;;..-:-:....:.~-::.-,;~ Ii i; LOX TANK CLOSE: ' U
~.j FLIGHT C.O NTROL, -c1 41 PSIA [1 r. PREPRESS. :J ;~lKGROUND--FILL _ P OPEN: 'i liOVERPRESSUREr 38 PSIA !: V.PRESSURE f1 II SW ITCH ~~ I
n -' t~ i'
f: 403S8 il :1 __ .' =--,-_.
LOX Tank Pressurization. Control Schematic (Sheet 2 of 2) FIGURE 2-20a 2-34a
::- L~fC~~~~~E'~}EL-SV:SE~B~0'rpj;Ei7~~'-'-~--!\ FROMl02-H2 BURNER •• ~ N . t. ~, • i
~ ,SIO~17 ,0"_' :S~rvB :: VOTING CIRtUlT
bG.H 3..9_ SS 005 . SWITCH !,i T +4D15 , - ____ =-.:--===~~..,..8J2ELECTOR;; <'--_"' __ . _J I -- -'. -._-... "
]
_ " ~ ., 404A3A50 .- " ,~ .~, ~ c---; C R5 .,' CR6 -', A mE" T T 404A3ASOCRl., ' s;<"
@K1 0 ~R 404A3A7! I i __ ~ <;_ CR2
J, I -' , ,J r 404A3AW, - ' 404A3A71 T
FROM MODE SELECTOR
~SWrTCHES(4'lS2 and 411S4) K87
1\ -4 I K:76_11 - - -- ~~~3~49 _L ~ FROM LH2 TANK PRESSURE L IT] FROM LHi'TANK REPRESS • fI-t-- ---
REG BACKUP PRESS SW ,404A3A49 -== r (403S6) (SEE SECTION 2.14.5) . -_
I ~ __ 1 II .==;r 1 1 1 I I I I I LH2 REPRESS ,I 1 LH2 REPRESS : H I CO NT VALVE 1 1 CO NT VALVE I U
4 1 I I !l I I I r' I II lJ I LH2 REPRESS. I I H i CONT VALVE I I 'I L 1 ,
SLV AS-503N
1 _______ L~, L _____ • __ L~I ,'\
NC AMBIENT LH2 TANK I NC l~ 403D73A4 REPRESS CO NT MODULE 11
Ill------~--------i NO CRYOGENIC LH2 I NO h 403A6 I REPRESS CONT MODULE •
:: --'--""'""=--~-~l"""""- :::e:z:::o.o. -'- ...L-
t::::::;:- --~---~-- • - -_1_ -'_
LH2 Tank Repressurization Control Valve FIGURE 2-20b 2-34b
[jC()~r1t\tio"iMBIEir"REPRIssuRizAilOljt~ rjf-1ODE_SELECTOR AND ,CRYOGENIC: ~ ij SEL(OFF).-. ,:SEC'(ONli tj,-----,--, ;J CRee Of'lT ,S-IVB~ CRY (OFF): i!:FRQM BURN,ER I _
CH 37' SELECTOR CH 36' , , ' '
... - . - -
Inl ; FROM LOX TANKJUGHLCONT .l ____ ,_ ~ I PREPRESS & GRD FILL OVER PRESS SW.'
!, AND_~Q,X TA~K R'EPRES~- , -' I REG. BACKUP PRESS SW. i .+4D15
~I SS 001; ,SHITCH. SS 076 ,I1VOTING CIRCUIl z:2!r""~ ~--~-:---~~ •. -.:.:..... ~- . .:..:..:-. _:_~":':-=":"'--=-:::.-..i 'I
.'. CR3 o ,'TO LH2.JANK REFRE,S,S_CONTRO-L.
: VALVE OPEN CIRCUITRY 1'-' , ,
+ k CR4 I '( SEESfcT'ION'-2 '.14~ 4)
K35 i CD ~
w
(
404A3A50 \,+4Dl,5 ~
'~~T~
• MEAS_. K0195
9 I
K87
----O-r'HJ 1 . ~ 404A3A49
K31'
K52 > , , I; ". -=-1-----
--404A3A41
+4D15 1-., " .. _.-.I
-<- ~ r > 1"---.-----;
SLY AS-503N,
ME AS,., K010l
w-~~~~~~====~~=='~~?:~~~:====~ . '-I LOX TK~ II LOX TK 1I;;,l LOX TK --~-II - LOX'TK ql rL\ CIP [1
I REPRESS 1'1 REPRESS 11 .... ,.' .. '.1 REPRESS II REPRESS "j ti Q il I CONT. • I. CONT I!'!,;i CONT -- II CONT I:! I, ----, !1 I VLV I ", I::J I 'i :, i . I VLV !';:i' VLV ~ ~ I VLV i \1 ~l \ 485- 335 i,
flL(::c~ ___ !:2:~L_ ~r::) __ :I~~':~N':) ____ lL.l:t_ L2 _~C2_1~lllLH2 TANK REPRESS REG :j ~_~O.X REPRESS CONl A~ Cq~~g,- 40~~7i<ih.Ol RillI5.S_ I rOp,lAr.jB!=-' 4Q,3AZ.4~~ ~:,~ACKUP PRESS SW 4.o~,~,6_i~ -- -... _.-.. ... .... - - --. ""--- - --
Repressurization System Mode Selector Control FIGURE 2-20c 2-34c
r; ---C(;M;~AN[)"-LoX --iArii<--REP',iss--- ---"-'--'-~l f
SLY AS-503N
~ CONTROL VALVE OPEN ,1 I .
U· ON OFF S-IVB n I [8JFROM LOX TANK FLIGHT CO~T.
MEAS SS 142 SS 141 SWITCH ~ FROM BURNER I PREPRESS AND GROUND FILL K0108. C~ 3 C_~ 4 S.E.LE.Cl.OBJ VOTING CIRCUIT lOVER PRESS SWITCH, AND LOX
Lrr ( =::.J I I TANK REPRESS REG BACKUP
A " CRl •• PRESS SWITCH. -- 404A3A50 CR2";'- I
. C0 ® (l~ r I ITIMAGLATCH RELAY (404A3A13K35)
• 0 -,> K7 <r- 1-~.4.o.~5-:f I CONTROLLED BY REPRESS SYS. -"'-- <_.".. I MODE SELECTOR SWITCH SELECTOR (.--1---4 I COMMAND. 4 L +4D15 - - - - - - - - - - - - -.- - -
= ~~.. \----------m K75 L ~
J ::r:r-r-l1-----t 404A3A44
--
.L---------IJ~ 404A3A49 r------~--.-o/ l K87 -;.=-
r
~ == ~-F! 4 = -Ii fl' 1T ~ X'TT S [ .. !
~ [1 i X' -J =.s " t~· 'i tl rl ]" - / 11 ' LOX REPRESS I, t; .. ~X REPRESS .li, Ii q MOD (CRYO) 403A7 1:1 !~ I MOD (AMB) 403A74A3 fl i. - $ - J l . --•. __ ... ~:::=:::::...I
_L l J~ ~=-~ ~ ----~---------~-~-------------------
LOX Tank Repressurization Control Valve FIGURE 2-20d 2-34d
SL AS-503N
fJCOI~i~AND_LOX TANK CoMMAND LO(TANK._VENLJ\ND-'COMt~AND._LOLTArJK ~. COMMIl,ND_LOLTAiIK =-.. --.- ;i i; VENT VALVE NPV VALVES BOOST CLOSE NPV VALVE LATCH NPV VALVE OPEN 1. ii OPEN CLOSE ON OFF ' ON OFF ON OFF \1 ,~SS 045 SS 013 ..~,SS 073 SS033 ISS 062 SS 123. .1 SS114 _ SS 165 _ S-IVB (i !j CH' 93 CH' 94 [I 4015 M cH 95 CH 96 CH 44 c845- 1: 4015 tl CH
u
l05- CH 106 - SWITCH (1 r;-=, I lie' .f.:! -r I -r ---,--- .,jc ".:1 --r- -,-- SELECTORiJ L:=- - . -==.:.i l- :,:----. .- ,-:C -.,:::=.J.-=C .-.. --" --'-'.-'-... -.. .,.:.=.==-=:.1
'<9 Kl ®I r:1 ltth~1 1<9...'3,4 ®I rI. 1<9 Kl3 0. . 4- _~\ \ __ - __ ;J l:ttd -r:twJ-~~ \~--~1~-
":;' Kl-lY I K2-1":;' -= K14-1Y IK13-1 ":;' r -~,.
ESEf--j~, '. e---f ESE
Ll
, -, ":;' , -=-, TANK VENTS
OPEN : , BOOST CLOSE TANK VENT ~NC NCnPILOT VALVE PILOT VALVE ~ ~~~
,.."I."Ir-VL\" .... ' 1\ PNEU ;,
LOX TANK VENT
LOX T VENT VALVE (41-4
LOX TANK NONPROPUL VENTS
NK RELIEF
PSIA)
VE
--_ .. _-
FROM LOX TANK
LOX NPV VENT AND RELIEF VALVE (41-45.5 PSIA)
ME CHAN ICALLY LATCHED
I
~ I I I I
I I
I NC n TANK NPV OPEN I ~.J-!PILOT VALVE
NC ;-
TANK NPV ~~- I 1 VENT & RELI EF
C)..,LATCH PILOT VALVE .~_. I
PNEU SOURCE
CHANNEL 93 WILL OPEN THE'VENT VALVE AND NORMALLY'ACTUATION OF CHANNEL 94 WILL CAUSE THE VALVE TO CLOSE. JO'OPEN THE NPV VENT & RELIEF VALVE AND KEEP IT LATCHED OPEN, CHANNEL 105 IS ACTUATED FOLLOWED BY CHANNEL 44. THIS LATCHES THE VALVE OPEN. NEXT. CHANNEL 106 IS ACTUATED FOLLOWED BY CHANfIEL 45. THE VALVE IS NOv! MECHANICALLY LATCHED OPEN. NORI'iALLY ACTUATION OF CHANNEL 105 FOLLOWED BY CHANNEL 106 WILL CLOSE THE VALVE. TO INSURE CLOSURE OF BOTH THE VENT VALVE & THE NPV VENT & RELIEF VALVE, THE BOOST CLOSE Cmt,;1AND (CH 95) IS SENT. TWO SECONDS LATER. BOOST CLOSE IS RELEASED BY CHAN 96. -
Commands LOX Tank Vent and Relief Valves FLGURE 2-2l 2-35
SLV AS-503N
r-·---------------------------------------------~
~:~~~~'~.~~~:=~~::~::-=-:~:L=:==~~
I! PU INVERTER AND 1 ; DC POI'IERj
! I 4D21 I
I ON OFF ):---)
j SS 035 SS 077 f-·~"r CHAN 7 CHAN 8 28VDC "T -- S-IVB
SWITCH 1 SELECTOR
'O'~h~J:~"~=~'~, K1-1
PU INVERTER PU OVEN
Command PU Inverter And DC Power
PU ELECTRONICS
ASSEMBLY
FIGURE 2-22 2-36
SL~ AS-
I' COMMAND LH2 TANK CoMMANO"'L'HI"TANKVENT COMMAND LH2 TANK-== ru1i1AND LH2 TANK ~ i VENT VALVE OPEN & LATCHING RELIEF LATCHING RELIEF LATCHING RELIEF ti , , VALVr BOOST CLOSE VALVE LATCH VALVE OPEN 'I i ON OFF ON OFF Oil OFF ON OFF II ; 55 061 S5 106 tF=""""'"' 55 146 55 166 55 072 55 122 l;::::t = 55 126 55 132 s- IVB t!
iq.~~61~:~~!.. ~~fD1'<
SLV AS-S03N
. Co!.I:;NlD L~; WIK , COW~ArlD LH2 TANK, S-IVB I'j ~ Cmf-IAND LH2 TANK S-IVB 1'1
I corm~;IJOUS VENT RELIEF CONTINUOUS VENT SWITCH, 4015 • CONTINUOUS VENT SY/ITCH • OVERRIDE ~OV. OPEN ORlfIC,~;S:V OPEN SELECTOR'l ..,;t--:::"'-';7 ~ VALVE CLOSE . SELECTOR:,,:
I ON suv OFF ON OFF' l. ON • OFF_ b I ,S5 H5 SS 105 SS 012 SS 113 r:=====::== H SS 131 SS 011 II
I ,~~~~7.. CHI C¥~T_!j ~ [I CH~ c:r ~i
. I~~~!.\ K6-~---------li-}j K56 /". I LWJ IlllJ KS&-2 . _ -:: . . -
• MECHANICALLY LATCHED
ORIFICE BYPASS OPEN PILOT VALVE
1..----
Ll
-::-
VENT
ESE ~ES_E
LI RELIEF OVER- ~ I RIDE, - I
CLOS~ SOL: I I
PNEUI.lATICS SUPPLY
ORIFrCE"BYPASS CLOSE PILOT VALVE
~======e- TO'LH2 TANK
Commands LH2Tank Continuous Vent Valve Open And Close FIGURE 2-24
2-38
K25
4Dll ..)---.~--J
f- .H-·_·T 28 VDC
MOTOR Ell
'X
4D41 .).---;1
l- sf VDC
I .:.;,.-~~ ............ -.... ~--~.;..~- "::Co.:.!
Command Auxilfary Hydraulic Pump Flight node
SLY AS-50311
Figure 2-25 2-39
I! § -. '0-: . .';"'-~ r;"'" """"""'_""_"=' .. =.O, __ ,'._"'~LC'''''_='=~=~-_ .......... r-='-~'~===~~."~~--~' ~i
.t ('.'I .... r~· f, ~. • :: ... ~ t\...:~ ~~ \ • ..J •• , ... ,1 C f', "'_1 -('-r,~ .• i' SCI ECTO" 11 '! ~::._~".v-, 'j. "
: ~ - ".j :1: \ iI COI·::':;;.'W CO~·::':A~D [I ;; COMMAND. COi~t~AND Cor~;'.AND CO;',iWiD ). . Ii CHA'\GE ULLAG~. ~j tj CHARGE FI RE FI RE ULLAGe l' \ i ULL~GE CHARGING .. 4D15. il ~LLAGE ~LL~GE ULL~GE FIRING- \1 .J IGNI, ION j .- ._, 'j J.:.TTISON J~ TT ~SON IGNI, ION "
!' /I • :. !l Iii
ON RESET i' j--.., Ii ON ON ON RESET ) t ·SS 164-- SS 134 . ~ 28 VDC;:) SS 144 SS 032 SS 124 SS 053 [: k:d 54 C~A~~_.-J,~f> II CH~"~~ 57 CHA~ 56 C~:~ •• :.~ Ii ;- " ,
K40-1 ,
CLOSED Q I. Il IN FLIGHT" 01 © ®'I
® C0 IK22-1 ®¢ I. ~I <'- K23 -> 1'0 ~24-1 ~ WvL,~v-
<:--
V CHARGE ALL
UR IGNITION FIRING UNITS
CHARGE ALL UR JETTISON
FIRING UNITS
iT TO TRIGGER
INPUT-ULLAGE JETTISON
Commands Ullage EBW's Ignition And Jettison
,1 •
K23-1 -
. TO TRIGGER INPUT-ULLAGE
IGNITION
FIGURE 2-26 2-40
[i' '1 ~j COMMAND
t ~ 1\
ENGINE READY-BYPASS I' ,1 '1
11 r'
S-IVB I~ . SWITCH ~ . SELECTOR fl
-~---.J
t~ SS 143 ~ C~10 I..o..:!:lZL££LL2), • .,....-
4015 ,z----'''' '--'--1'
28 VDC
~~LJUJI~ Ii- -- -- -- t1 ~ ,; I) COMMAND S- I VB t1 t: ENGINE CUTOFF ;i J ~l :-1 !.i t 1 ; .~
H ON OFF S-IVB H n ss 115 SS 162 . SWITCH :J 11 CHAN 12 CHAN 13 SELECTOR Ii
\'-~61:~_~~--I±-~d~~-'~ d
1~r. *RELALSWITCH K61-2 is SHOWN IN FIGURE 2.49 ~~- COMPONENT TEST LOCKOUT (ENG.SEQ)
~,...,.<- POINT LEVEL SENSOR VOTER OUTPUT. ll""'R """"""",-=~====::===~=.~.-~-- - -=--==~-=_=:,c.;.-=- .. ,,-- ..
I·:' ~6~N~C~ORS );. I ENGINE I
=11 I, "
, INSTALLED . INITIATED CUTOFF
q ~j "
,) ENGINE •. I (; READY GATE n.:-r1 ~ i I~ , • f\./\I\., . ft P..L~, N TO ENGINE 1 ~ CUTOFF I
ji :! II
;j
;1 ~ DISARM
rj .) _ -:.:: :' 11 -. J-2 AREA i:
1'1 ' .~
ri
~=. 4 --=:l~-:"-"'-' -.------.-..--------. "--~-". .._.j
Kll Kl1- 2 :t ~ TIM K-.12 11;:J-J.:.k)--------.- ENGINE READY
-=: 28 VAC r ~': -.-- ~., <----'
4011
CommandS Engine Ready Bypass And Cutoff
FIGURE 2-28 2-41
,
I i
," "
~ ~~ ' .. 'I 1 C:1 ;: ~ cn"~""'r\;'~J !i 5-!Vl.l ENGINE " "
SELECTOR ,'; START l' ~~
•• ., #
~ ON ~~ r ;,-'. " '-1--1 OFF
i.~ ') ~~ 0:') 5S 135 :: I 28VOC , l'~ I" \ l) .1 ,I ,.".'~ • CH,'\" "7 i.: ,i -r- .........!, ,I' I -r- 'r,t __ ,::: ... L ........ ~~-·.':";._.d-.. _ e::L!'?C_._.. ..... --~j
~L KG3 ® /(,.- ---
- - I ...: -l,jj---:...,--\ 0
K53-1
DC 1 o D K57 I
en a . =------t «57-1 S-lI' 0 [l ~ -i:
, , (J D ' o 0 .. ,. ) ___ -, . >1:> TO ENGINE ELECTRONI'C rJ 0 ,S-IVB I 28VDC CONTROL PACKAGE
~'----..., D El r r 4D11
K-57-1,IS SHOWN IN DE-ENERGIZED POSITION. K-57-1 WILL REMAIN OPEN AS LONG AS STAGING HAS NOT OCCURRED. AT STAGING, THE S-l1 JUMPER OPENS, CLOSING K57-1 AS THE RELAY RELAXES. THE ENGINE START COM~D NOW HAS CONTINUITY TO THE ENGINE SEQUENCE CONTROLLER.
Commands S-IVB Engine Start
\
FIGURE 2-29 . 2-42
I j
i I I ,
COfv\l'tl\ND PU FUEL BOILOFF BIAS CUTOFF
OFF ON SS 117 SS 036
CHAN 34 CHAN 35 S-IVB
I I SWITCH
SELECTOR
4D21 <.~-- .. -- --j
(-.- _. ··-·r 28 VDC
~~T~~~ ~J.~~~,c::":=:::.:;
bitd J,-lliJ - - - - - -KU-l
-
.... ""J __ .. ).::.:.tt~.", ... '*Ot:C..~:.t::: .. =:r"";-·--~~=~-'~~~.::::.:·.I5~Z'~· ,.~.-:z.~J:.ili_:!:L__:''''''''»-, 1. r.71:::"~
f PU BOI LOFF
PU ELECTRONICS ASSEt~BLY
K5-1
j:---:- -----;a ,:.....:-~-=r
SUMMING NETWORK
BIAS (M10)
PU BOILOFF BIAS ADJUST
SLV AS-503N
L---______________ -----l
Command PU Fuel Boiloff Bias Cutoff
FIGURE 2-30 2-43
~M ,;> ~=;:;r s = __ ) ~ !)
~ CQY,"M'D PU VALVE fl h HARDOVER POSITION II I M .~ ON OFF f~ r il
II SS 037 SS 063 S-IVB;' CHAN 17 CHAN 18 SWITCH!j .. T ---r- SELECTOR 1[:
r y! . I . J
C0 K8 ® ~.--
lU i,S-S03;~
r-= - ~~-"~~-' -"::::::::::.::::"='::.:'.::.:::=:==.:'="'-.;.::.:::'::.-"::~":'::'.:-==':':"::::':"'::"~~::-'=':':::-=:' .. -:::.:;=:..:. .. 'j
n STATIC ltNERTER-CCWERTER ~1
i1 11 117 VDC 28 \!DC 44.5 VDC
~~: ',. . -- _ ..
o )
f-4D21_j
<...~ "> f--I" ~C o b
K8-2 6 K8-""! 0
K131 0 tJ \' -='= O:.r:u- - - 313-1 _ ~13-2
r"I "" ~L'" \""
I ~~~b~~~ -. 2 ~ ~, 1:1
, FWD : SHAPING
NETWORK
.:.. _____ :t: .~
SYS n SHAPING H NOISE t!
~j H f~ !; f! _.: t, .
. ADJUST H I '\ BYPASS r,
;'1 PU ELECTRONICS ASSY
t ~
"", i ., " f1
--':~
Command PU Valve Hardover Position FIGURE 2-31
2-44
4D11 ~ ..... --.~ -j
<'., ~
f- ··---1 28 VDC
SLV AS-503N
ENERGIZED BY PASSIVATIOfl
ENABLE (S5 CH 1)
.~:. 7_C,=----.:::c::."'=-::c:::O;==.::=.,~===::: :.:C':::::-::-;-:..--:::; ::.;.~;.: ~ ~~Sl-l
11 C0i1MAfW ENGINE IGilITION PHASE
CONTROL VALVE
OPEN CLOSE SS 057 SS 116 CH 40 c~f 41
~
K91-1 K9i::~- -l'HiK91
-:>- <}--- ----- K92-1
K105N
'-, IGN I TI ON :::: PHASE -- CONTROL VALVE
SOLENOID
ESE
~~ ~1 --
.
Command Ignition Phase Cant Valve
FIGURE 2-32 2-45
COMMAND FUEL INJECTION TEMPERATURE O~ BYPASS
4D15 t· - ____ j ON RESET S- IVB
"'" > SS 163 SS 021 SWITCH f--- "'1" ~i CHAN 11 CHAN 16 28VDC --r-- SELECTOR
"-:::7.:":;:"':.':.~' . '.::::;:-:=:;: .:b .. ....:~T"._~-.~" .. ::.~~.:::= ":::C'::,: J..::.==':')?::J r .~(L) K55 ® .~
'K5S:':j ----- ~-
START TANK DISCHARGE
DELAY TIMER 0.5 SEC
-
KI01
K105N
J-2 CONTROL PACKAGE
IGN cp TIMER
Command Fuel Injection Temperature OK Bypass
SLY AS-503N
FIGURE 2-33 2-46
1
SLV AS-503N
... --------------'--------------,
CD K48® <- J,> K48- 1 '{ -- ------------_.,.
.7
LOX TANK
LH2 TANK
I-----\< ~ ESE
CHILLDo\.JN SHUTOFF PILOT VALVE
PNEU~lATI C SUPPLY
TO J-2 LOX AND LH2 PUMPS
""'E!i CHANNEL 91 IS ACTUATED, BOTH LOX AND LH2 CHILLDOWN VALVES CLOSE.
t. __ ----------------------____________ --J
Command Chilldown Shutoff Pilot Valve Close
FIGURE 2-34 2-47
i ==::::::r.:: -'-'::';'";=:'C:::'-""-=='='CC·:;""'" C::=:::;",-_.'r::cr"';"l
I' COt:1MAND POINT LEVEL SENSOR
I '
I ' ARMING
I SS 006 SS 104 S-IVB I CHAN 97 CHAN 98 SWITCH;
DISARMING
CD K62 ® K62-1
L.-T
t" ;C~7:="~_-"=--"'::;_.''-:'~:-:'' ". ._;:;,Z~,~E ~~2c~J
-'-l':"r--r==t~:~- ( I
4011 ':.Ur-~~----~~ . --------------
~-.-. -"---J
F,· , .. - --.,::j>
SOUD STATE VOTING CIRCUIT
RC TIME DELAY
0.558 SEC
I
DRY
DRY SIGNALS
I--
SIGNALS r-I--
TO ENGINE CUTOFF LOGIC (SEE FIGURE 2.36)
Command Point Level Sensor'
RELAY VOTING CIRCUIT
SLV AS-503N
4011 f,-, .--.. -.- -j . <.,
r·,-- ···r
I---
FIGURE 2-35 2-48
ill AS-503N
Cor~MANO f: TIM C.'\LI!3RATE a"
ON OFF !.1 S - I VB SS 112 SS 00 7ij Ij SWITCH CH 62 CH 63
IlsLECTOR' -,- , --r-_:,
4015
t
1)-'-= Ii 1\ (j COMr~ANO INFLIGHT , \1 i,' CALIBRATION r10DE- 11' fJ . ,
4015 tJ ON OFF [1 j-.---< H 55 054 S5 014 5-IVB. ~,J
I, " fl c, H 48 ,C,H 49 SWIT,CH,' h,' l=--r. -r----.-.s.El,.E..C_T.OR fj
-----{ -~ \ K68-1· ~,K~8 ~® I ---- T -1-1_ _ -LA
I OP1BO
270 MUX
, (
-l 1
CP1BO TIM 270 MUX CALIBRATOR
I TIM
OSCILLATOR
I VIBRATION
MUX
.Commands TM Calibrate and Inflight Relays FIGURE 2-36
2-49
-".- . ~ {"" ,..."" ...... , I~.,)·-"..,)'J...;.t
· ... ~ ~""'===. =-=-~"'==-===
11 " 11 COMMAND S-IVB APS COMMAND S-IVB APS il II ULLAGE ENGINE RELAY NO. ULLAGE ENGINE RELAY NO. 2 ~:
~n \\ , 'j ij ON OFF ON OFF f: '.1 SS 136 SS 176 SS 066 SS 046 S-'IVB :~ !1 CHAN 42 CHAN 43 CHAN 101 CHAN 102 SWITCH r: " -r -r -.- -.- SELECTOR :, , . . .. r~ K12~~._C;~~D;:c=C~
~ I -- K121 ~ -'- <:-
r -':T l
I lU __ I j"
- I
~ ~.
,~Ll ~l2 ~; : ~ I -: I -= I
FROM· I FROM I FUEL I NC OXI DI ZER . I NC
FROM I FROM. I
TANK+~~· TANK~~~.
I TO TO
FUEL I NC TANK->~->.
TO
OXIDIZER I NC TANK->~->
ENGINE ENGINE
APS MODULE 1
Commands S-IVB Ullage Engines No.1 And No.2
.. ENGINE
APS MODULE 2-
TO ENGINE
FIGURE 2-37 2-50
lWN
~~ 'il 1.J .1 • I !l COMMAND ;, }) ENGINE MAINSTAGE CONTROL ii
TO PASSIVATION [I VENT OPEN fl ENABLE \1 ON OFF II
1, ·-1' t COMMAND ~ ENGINE PNEUMATIC SYSTEM ~ ~ VENT OPEN M
·U ~ CIRCUITS I: ss 015 SS 157, S~IVB II
'J CHAN 14 . CHAN 15 SWITCH 11
l ON OFF (1 4D15 55156 SS101 S-IVBUl.-···--;'l
CHAN 20 CHAN 21. SWITCH ~j f..--f· .;>
~=I I· SE.~.EC~~.Rj 28 VDC t, I I SELECTOR :\ . :"=~0 K:= ®~ .. ~-' ... .::.::.=-: ..
o ~..;__:> K93-1{--- -- + ~+ ,\7
~ ,'ESE TO MAIN !' . LOX VLV & .. ~-()-:t TO MAIN
PURGt VLV ~' 'LOX !/VLV
li~ L1 " NO Y1- -l:it - - - -fY NC
j SPJ K96 fR\ ~~ K96-1 ------------\,
r ~.,.
ESE I i>l ~
HE TANK EMERG VENT VALVE
ENG NC PNEU /~ SOURCE /' ~ \ .
ENG HE CNTRL VLV
ENG PNEU SOURCE
Commands LOX Chilldown Pump Purge Control and Dump Valves FIGURE 2-38
2-51
----,
1~1! ,.~r.:':C=:::::"';"''-''-;'~~::;::':-c: ,'",",::~:=",=c'l
ENGINE PUMP PURGE '
)
' CONTROL VALVE ENABLE
ON OFF 1 55 022 S5 075 5-IVB
CHAN 24 CHAN 25 SHITCH d -"""==t,,,;:-.;:,,-,,::.-..'" =r=.~ 1='c,=<~:~~~:c,J~~J
C0 ® <:_ K47 -..-'"
,..---{)--,
SlV AS':'503N
4011 !,_.- ,. 'j <--. --,....
),.- ,I" ~,_1DJ 5.-J
<~'------, .. -t 28VDC
130 PSI --m 105 PSI
REGULATOR K47-1 PRESSURE 5H
28 VDC
---------------
nJ----->;Z1:L f -=- K72 ~
rill -=- I
I
TO lH2 AND LOX _ ~ TURBOPUr.1P PURGE ~
NC
ENGINE PUMP PURGE CONTROL VALVE
PNEUMATICS SOURCE
Command Engine Pump Purge Control Valve Enable
FIGURE 2-39 2-52
COMMAND PREVAL YES CLOSE
ON OFF S-IVB SS 026 SS 151 SWITCH CHAN 82 CHAN 83
~E~~E:l-9.~_ --, '7"":;:.J'C=~==-:_,.")~- -'~,"::'-=~":C::-k 4D15 ,J----------j
K46~F-;fc
CLOSED --¢--l1--f ES E BY
SWITCH SELECTOR
CHANNEL 12 (ENGINE CUTOFF ON)
.:'3 K3-1 CLOSED BY I1AINSTAGE OK PRESSURE SWITCHES
LOX AND LH2 PREVALVE
I PILOT VALVE I
- I I
I NC
n~=;r=t~= .... PNEU~lATIC SUPPLY
LH2 TANK .:::l~§=~TO J-2 LOX AND LH2 PUMPS NO
WHEN CHANNEL 82 IS ACTIVATED, BOTH LOX AND LH2 PREVALVES CLOSE
SLY AS-503N
Command Preva1ves Close FIGURE 2-40 2-53
.1
4D~ ;"'--J
...r... ' ..
56 VDC
TO LH2 CHILLOOWN
!INVERTER
f1 COMMAND COMMAND 11 ,] FUEL CHILLDOWN PUMP LOX CHILLDOWN PUMP t1 ~ ~ ~ U f1 ON OFF ON OFF Ii R SS 071 5S 153 SS 121 SS 042 S-IVB }j fi. CHAN 58 CHAN 59 CHAN 22 CHAN 23 SWITCH t! ~1 I I I I SELECTOR I! F==""""""""= - --. :C.'::: .. J
CD ® <- K6 ->
® CD <_ K5 -{>
SLY AS-503N
4041 1-- --j
<-- '"> f---I-"--;
56 VDC
K5-1
i : i
T~~---------------
Commands Fuel and LOX Chilldown Pump.
I V
TO LOX CHILLDOWN INVERTER
FIGURE 2-41 2-54
t "i1. I " !1 COMMAN D ;J
II SSB/H1 TRANSMITTER ~;
~ ON . OFF S-IVB tl ,j SS 102 . SS 155 . SWITCH ii f1 CHAN 46 ~N 47 • SELEC!_O~~
K5 ®
*COMMANDTM RF SILENCE ON (CLOSED DURING FLIGHT)
4031 . -::J -:--- (--.r 28 VDC
K1S-1*
K5-1
. ~~:lJij
4031 '. __ .. .._1 ~ -"->-
~. -====-.......... --:--"""=:===--=:..::::-.=.::----::=::::::...-=---::::-.:..-:. r • .:.:....=.:. "1 .' COMMAND .
f '~I-- ~ ... :
128 VDC i
> I~
;j
:; :1
.FM/FM TRANSMITTER
-:; ON' OFF. S-IVB .
.i
SS!lll .SS 067 . SWITCH CH· 66 CH-6Y- SELECTOR.: --=:::r--.. -. -. -T -_._. --, :::_c:.~=~
CD K6 ® i () 1-> ~ <"-1 , . - --. ,I.
K6-~---- "'bb-r~'"
K15-2'*
~ ., ~ FM/FM [] !J TRANSMITTER !i ,. tl
~ iJ , .~
Command Single Sideband FM Transmitter
FIG!:WE 2-42 2-55
COMMAND PU ACTIVAlc t
ON OFF SS 002 SS 055 S- IVB I CHAN 5 Ct-WJ 6 SWI TCH
!.-~- I~:_ :.~=_=:;:J:;:_~~~~.c~~~~~~~~~: ~ ~_. ~4?2 ~_ .. -J <....~ r -- -... _.j
CD ® 28 VDC KID KIO-l <j-- r, _~,.
±JIB.li-~ ------~
ESE Cfv1D GMD POS IT lONER
VALVE TEST
PU ACTIVATE REMOVES THE DISABLING GROUND AND ALLOWS THE PU TO OPERATE AS A SELF COMPENSATIVE SERVO SYSTEM.
Command PU Activate
K3-2
o
SLY AS-503N
FIGURE 2-43 2-56
* SLV AS-503
2.4.3 S-II Switch Selector Functions (Octal)
CH Code Function Figure No.
000 37 001 SPARE
5 002 COMMAND S-II/S-IVB SEPARATION 2.54 30 003 COMMAND START PAM-FM/FM CALIBRATION 2.55 74 004 SPARE 81 005 SPARE 97 006 SPARE 63 007 SPARE
010 87 011 SPARE
111 012 SPARE 94 013 SPARE 49 014 COMMAND ENGINES READY BYPASS RESET 2.47 14 015 SPARE 51 016 SPARE 39 017 SPARE
020 16 021 SPARE 24 022 COMMAND S-II ULLAGE TRIGGER 2.54
9 023 COMMAND STOP PAM FM/FM CALIBRATION 2.68 75 024 SPARE
109 025 SPARE 82 026 SPARE 71 027 COMMAND START DATA RECORDERS 2.45
030 68 031 SPARE 57 032 SPARE 96 033 SPARE 33 034 COMMAND S-II ENGINE START 2.49
7 035 COMMAND S-II LH2 STEP PRESSURIZATION 2.48 35 036 SPARE 17 037 SPARE
040 53 041 SPARE 23 042 COMMAND S-II SECOND PLANE SEPARATION 2.54 31 043 COMMAND S-II ENGINES CUTOFF RESET 2.59 61 044 SPARE 93 045 SPARE
102 046 SPARE 90 047 COMMAND MEASUREMENT CONTROL SWITCH 2.43
NO. 2 ACTUATE 050
69 051 SPARE 65 052 SPARE
2-5"(
* SLV AS-503
CH Code Function Figure No.
73 053 SPARE 48 054 COMMAND S-II LH2 RECIRCULATION PUMPS 2.49
OFF 6 055 COMMAND S-II START PHASE LIMITER 2.46
CUTOFF ARM RESET 52 056 SPARE 40 057 SPARE
060 38 061 S-II LH2 TANK HIGH PRESS VENT MODE 44 062 SPARE 18 063 COMMAND CUTOFF S-II ENGINES 2.46
110 064 SPARE 92 065 SPARE
101 066 SPARE 67 067 SPARE
070 58 071 SPARE 64 072 SPARE 95 073 SPARE 29 074 SPARE 25 075 COMMAND S-II START PHASE LIMITER CUTOFF 2.46
ARM 36 076 SPARE
8 077 COMMAND S-II/S-IVB ORDNANCE ARM 2.54 100
21 101 SPARE 46 102 SPARE 32 103 COMMAND ACTIVATE PU SYSTEM 2.56 98 104 SPARE
108 105 SPARE 76 106 SPARE 89 107 SPARE
110 66 III COMMAND START RECORDER TIMERS 2.45 62 112 SPARE
112 113 SPARE 105 114 SPARE 12 115 COMMAND S-II HYDRAULIC ACCUMULATORS 2.50
UNLOCK 41 116 SPARE 34 117 SPARE
120 22 121 SPARE 19 122 COMMAND PREVALVES LOCKOUT RESET 2.46 45 123 SPARE
2-58
* SLV AS-503
CH Code Function Figure No.
56 124 SPARE 91 125 SPARE 99 126 PREVALVES CLOSE ARM 86 127 SPARE
130 84 131 SPARE
100 132 SPARE 60 133 SPARE 88 134 COMMAND CHILLDOWN VALVES CLOSE 2.4~ 27 135 SPARE 42 136 COMMAND S-II LH2 DEPLETION SENSOR CUTOFF 2.46
ARM 2 137 SPARE
140 4 141 SPARE 3 142 COMMAND S-II LOX DEPLETION SENSOR 2.46
CUTOFF ARM 10 143 SPARE 55 144 SPARE
107 145 SPARE 77 146 SPARE 85 147 SPARE
150 83 151 SPARE 79 152 SPARE 59 153 SPARE 70 154 SPARE 47 155 SPARE 20 156 COMMAND ENGINES READY BYPASS 2.47 15 157 SPARE
160 50 161 SPARE 13 162 SPARE 11 163 COMMAND S-II ORDNANCE ARM 2.54 54 164 SPARE
106 165 SPARE 78 166 SPARE
104 167 COMMAND STOP DATA RECORDERS 2.45 170
103 171 SPARE 80 172 SPARE 72 173 SPARE 28 174 SPARE 26 175 SPARE 43 176 SPARE 1 177 SPARE
2-59
C<HW<O S-II ORtNANCE
ESE (M) SEPARATION CONTROLLER l>til B IT
~ , g;
K4 20GA31A2A2
C<HW<O S-II SEOOND "PI..'/'E SEPARATION
S-IC/S-II ORllNPNCE· ARM
!XH'W<D S-II lJLLlGE TRIGGER
SEOOND SEPARATION TRIGGER
FIGURE 2-43
CIM1.'HD S-II/S-IVB SEPARATION
w..oGE TRIGGER
ALL E.C.O. (M)
TO SEPARATION SYSTEM •
[SEE FIGLRE 2.48] Pi'GE 2-63
2DI48 TRIGGER
;aMWI) OS-II/S-IVB 0RtNANCE
SEPARATION SYSTEM RELAYS
S-II/S-IVB R£TRO ROCKET FIRI'" lI-IlTS
S-II/S-IVB SEPARATIOI
FIRI'" lI-IlTS
S\oI sa 206A31A1
ESE RESET
cffiI1
!~ 5:
'" I
'" ~
ESE CQ"MP.ND PREVALVE & LOX RETURN LI NE VALVES CLOSE
C<M'1AJ\D CHILL DOWN
VALVES CLOSE
SS 134 CHAN 88
T K63 -
l:Utr±----ESE CCl"MAND LOX RETURN LINE VALVES OPEN
~------•
SW SEL 206A31Al
ESE CHILLDOWN RELAYS RESET
SOLENOID VALVE LOX RETURN LINE VALVES
FIGURE 2-44
SOLENOID VALVE lJ-i2 PLMP VALVES & lJ-i2 RETURN LINE VALVES
SLV AS-503
~ ACTIVATE P. U. SYS~
55 103 <l2f'I~2
J2 LL 5W SEL 206A31Al
, P. U •. ELECTRCNIC
PACKPGE
FIGURE 2-45
2-62
~~ R
s
~
~~ "
I I "
I "v
I
~~~ ~ i:i ~~o
.~ ~
i I-
~ ~
~; ~
~
~
~~ g~
~~
-R.
~ : I I I I 1
53
I-~
~
:; m ~
;! 1 •
. ~ ,
i"s ~ v
~ -J~
~ ~ <Iv
I-~~
~ ,
-J .5
~ ~
m~
p
" ~ ~
f ~ I-
. j
~ • "
~ :.
~
i; v<l
m~
" ~ ~!I-+-----++--*----------::=-=
2-6J
r ~~ ;~ =
I-
I~ u~ @~ ~@
1 ~
~ i~m~ ~ ~~S":i
~ , ~
"'"
ESE RESET
COfotW.iD ENGI/'IES READY BYPASS
ESE Cot+W<O ENGINE f\K). 1 READY BYPASS
156
SW SEl 206A31Al
~ESE ~ESE Cot+W<D Cot+W<O ENGINE NO. 2 ENGINE NO. 3 READY BYPASS READY BYPASS
C/oJ RESET
C/oJ RESET
C/oJ RESET
BPl-60-24-R-8-10 ---- BPI-BO-24-R-S--9 ----
VDC
FIGURE 2-47
~ESE ~<>E ' CCMW<o - CCHWl) ENGI/IE NO.4' ENGII'E 11«). 5 READy BYPASS READY BYPASS
CIO ~ -Cia RESET RESET
j\;~ ,<
8
..., I
'" '"
ESE RESET
CCM'1AND S- II LH2 STEP PRESSURIZATION
SS 035 DiAN 7
SW SEL 206A31Al
2D11
FUEL PRESSURE REGULATOR
FIGURE 2-48 ~V1
'f!< '" o ""
'1 7~ •
H ~~i>--l---~
u~
11-S " .. om
::.
2-66
~ , ~
ESE CJ10 "'" ..:J. HY[RAULIC ACCLMULATOR SOLENOID LOCKUP
J2DI:8VDC ~2DI:8VDC KJ8 KJ8
.. .. ..... .... , , ..... l .. '
-
EI<i ..:J. 1 E'G ..:J. 2
CCf+\AI\ID 5=.1 I HYDRAULIC ACClMJLATORS·
WLQCK 55 115 CHAN 12
SW SEL 206A31Al
ESE CMD HYDRAULI C ACCLM.JL.A TORS LOCKUP
ESE RESET
l2DI:8VDC l2DI:8VDC - .
ESE (M) EI<i ..:J. -HYDRAULiC
; ACCl.MJL.ATOR . SOLLI\O JD -LOCKUP
ESE eM) Et-.G ~. HYDRAULIC ACCLMJL.ATOR SOLEf'.DID LOCKUP
FIGURE 2-.50
KJ9 KJ9
~ . ~
, ..... ..-.J , ..... l .. ' -
E'G ..:J. J E'G 1\0. 4
ESE' CJ10 ENG 1\0. 4 HYDRAULIC ACCLMULATOR SOLEmID LOCKUP
,.'" "'r ,< ~ o ~
'" 1
'" '"
E5E
NO.1 55 011 0iAN 87
202l
~'" . 28VDC
K122
•
CC:t+W<O CA"ERA EJECT
NO.2 55 127 0iAN 86
2021
~'" ___ .- Kl2l
FIGURE 2-51
NO.3 55 031 0iAN 68
5W 5EC 20631Al
2021
~ ___ ._ K120
:.-" V>r 1< '" o '"
.., • '" ...,
C9':I"\4J'ID _CA/'IO.RA _LIGHTS_
LIGHT POWER· BOX
FIGURE 2-52
a.J .
55067 CHAN 6~
S~ SEL 206A31Al
2BVDC
l>uo uor .< ~
S
'" • " o
K1I9
C(MWID CAMERA MOTOR-
ON SS 147 CHJIN 85
CJlMERA CAPSULE POS NO. 3
FIGURE 2-53
C(MoW.I~U:Af"ERA E\£NT Jo'ARK
SS 051· CHAN 59
TIME CODE . GENERATOR
CJlMERA CAPSULE
POs.m. 1
SW'SEL 205A31Al'
G;~ .< ~
o ~
ESE 010 SEPARATI~ CO'ITROLLER It.t1IBIT
" . ~
Co+IcND S-l\ OR~CE
ARM' SS 163
C<M1I'ND S- I I SEOONO pl..A'£ SEPARATION,
K88
S-II OROANCE ARM
C<M1I'ND S-I I ULUGE TRIGGER
SECOND SEPARATION TRIGGER-
FIGURE 2-54
CCt+\CNo S-I1/S-IVB SEPARATION
ULUGE TRIGGER
ALL E.C.O. CMJ TO SEPARATION SYSTEM
[SEE FIGURE 2.48] Pi'GE 2-63
RETRO ROCKET FIRI~ LNITS
TRIGGER
TRIGGER
COMMAND'S-II/S-IVB OR~CE
S-II/S-IVB. RETRO ROCKET FIRIN;; LNITS
S-II/S-IVB SEPARATICN
FIRIJ'li !..NITS
ESE RESET
206A31AI
K92
ARM '
ARM
l>~ ~,..
.< ~ a ~
'" I ..... '"
2D21
START PAM FM/FM
CALIBRATION
C<M-IAND PAM-FM/FM CALIBRATION
START
SS 001-Qi/>J\I 30
FIGURE 2-55
STOP
SS 023 Qi/>J\I 9
S\;' SEI, 206A31A1
ESE
• ,. t RESET/SEPARATION , I I'J-iI BIT
»VI VIr-1< '" @
'" o >
'"
-,' Vl~
>: ~
Vl
>-Vl
:; a: IU
;i~ f-~ f-U
« " ~ u
~
« ~ '" ~ C
N
-' IU
V
l
'"' Vl
-
u ~ f-U
--~
IU
:; a: L
.
2-73
lU
~ U
it
'" '" , N
IU
gj <
!)
u.
* SLV AS-503
2.4.4 S-IC Switch Selector Functions (Octal)
CH Code Function Figure No.
000 37 001 SPARE
5 002 COMMAND FUEL PRESSURIZING VALVE 2.60 NO. 2 OPEN AND TAPE RECORDER RECORD
30 003 SPARE 74 004 SPARE 81 005 SPARE 97 006 SPARE 63 007 SPARE
010 87 Oll SPARE
III 012 SPARE 94 013 SPARE 49 014 SPARE 14 015 SPARE 51 016 SPARE 39 017 SPARE
020 16 021 SPARE 24 022 SPARE 9 023 COMMAND OUTBOARD ENGINE CUTOFF 2.59
ENABLE 75 024 SPARE
109 025 SPARE 82 026 SPARE 71 027 SPARE
030 68 031 SPARE 57 032 SPARE 96 033 SPARE 33 034 SPARE 7 035 COMMAND FUEL PRESSURIZING VALVE 2.60
NO. 4 OPEN 35 036 SPARE 17 037 COMMAND TWO ADJACENT OUTBOARD 2.59
ENGINES OUT CUTOFF ENABLE 040
53 041 SPARE 23 042 SPARE 31 043 SPARE 61 044 SPARE 93 045 SPARE
102 046 SPARE 90 047 SPARE
2-74
*
CH Code
050 69 051 65 052 73 053 48 054 6 055
52 056 40 057
060 38 061 44 062 18 063
110 064 92 065
101 066 67 067
070 58 071 64 072 95 073 29 074 25 075 36 076
8 077
100 21 101 46 102 32 103 98 104
108 105 76 106 89 107
110 66 111 62 112
112 113 105 114
12 115 41 116 34 117
120 22 121 19 122 45 123
Function
SPARE SPARE SPARE SPARE COMMAND FUEL PRESSURIZING VALVE NO. 3 OPEN SPARE SPARE
SPARE SPARE SPARE SPARE SPARE SPARE SPARE
SPARE SPARE SPARE SPARE SPARE SPARE COMMAND INBOARD ENGINE CUTOFF ENABLE START OF TIME BASE NO. 2
SPARE SPARE SPARE SPARE SPARE SPARE SPARE
SPARE SPARE SPARE SPARE COMMAND SEPARATION CAMERA ON SPARE SPARE
SPARE
SLV AS-503
Figure No.
2.60
2.54
2.60a
COMMAND S-IC/S-II SEPARATION (NO.2) SPARE
2-75
* SLV AS-503
CH Code Function Figure No.
56 124 SPARE 91 125 SPARE 99 126 SPARE 86 121 SPARE
130 84 131 SPARE
100 132 SPARE 60 133 SPARE 88 134 SPARE 27 135 SPARE (
42 136 SPARE 2 137 COMMAND S-IC TELEMETER CALIBRATE ON 2.5B
140 4 141 COMMAND LOX TANK STROBE LIGHTS OFF 2.60a 3 142 COMMAND MULTIPLE ENGINE CUTOFF 2.59
ENABLE 10 143 COMMAND SEPARATION AND RETRO EBW 2.60
NO. 1 ARM 55 144 SPARE
107 145 SPARE 77 146 SPARE 85 147 SPARE
15C 83 151 SPARE 79 152 SPARE 59 153 SPARE 70 154 SPARE 47 155 SPARE 20 156 COMMAND SEPARATION AND RETRO EBW
NO. 2 ARM 15 157 COMMAND S-IC/S-II SEPARATION (NO. 1) 2.60
160 50 161 SPARE 13 162 COMMAND S-IC TELEMETRY MEASUREMENT 2.57
SWITCH OVER 11 163 SPARE 54 164 SPARE
106 165 SPARE 78 166 SPARE
104 l67 SPARE 170
103 171 SPARE 80 172 SPARE 72 173 SPARE 28 174 SPARE 26 175 SPARE 43 176 SPARE 1 177 COMMAND S-IC TELEMETER CALIBRATE OFF 2.58
2-76
'" I .... ....
IISA8ASKS
SS 162 CH!'N 13
llSA2A3K2
llSA201AS
I KI - KS I
COMMAND TELEMETRY MEASUREMENT SWITCHOVER
ESE.
llSA202AS
I K3 K4 KSI
FIGURE 2-S7
ESE CMD TM TRANSFER RELAY INFLIGHT POSITION
llSA203AS
fKI K2 -K3 1
:pv> f!< ~
o '"
'" • ..... 00
ENERGIZED CLOSED ll'lTlL LIFTOFF 115A2K4
ESE. RESET
COMMAND S-IC TELEMETRY CALIBRATE
OFF '55 177, CHANi
115A2A5
K1
a-I
55131' 'cHAN2
SW' SEt. 115A5
Qt-POWER' ISOLATOR
TM CACfBRATOR
FIGURE 2-58
O;~ .< '" o VI
SLY AS-50~
LOX LEVEL
Ef\G I NE CUTOFF
SENSOR NO. 5
1D11
LOX LEVEL ENGINE
CUTOFF SENSOR
NO. 4
1011
LOX LEVEL ENG I NE
CUTOFF SENSOR
NO. 3
FUEL BILEVEL CUTOFF SENSOR
FIGURE 2-59 (1 OF 2)
1011
LO~_L~VEL ENGINE CUTOFF SENSOR
NO. 2
1011
LOX LEVEL ENGINE
CUTOFF SE~SOR
NO. 1
'" J..~-I-------.r:-----+--J _1_011 -8
2-79
115A3A6
COMMAND OUTBOARO ENGINE CUTOFF
ENABLE
SS 023 CHAN 9
1011
1021
COMMAND MULTIPLE ENGINE CUTOFF ENABLE
SS 142 CHAN :3
1iSVOC
ESE 120A7K4-2 RANGE SAFETY
l '"''''
120A7K2 ESE POWER TRANSFER
COMMANO INBOARD ENGINE CUTOFF ENABLE START OF TIME BASE
NO 2
SS 077 CHAN B
1011
28VDC
115A:3A7 llSA3A3
CMO LOX LEVEL LOGIC RELAYS LOCK IN ENABLE
COMMAN~ TWO ADJACENT OIJTBOARO ENGINES OUT CUTOFF ENABLE
S5037 CHAN 17
1011
SW SEL 115A5
1011
____ 1oc
_______________________ ~oc r • ENGINE NO 5
1011
MEASUREMENT OUTBOARD ENGINE CUTOFF AND STAGE SEPARATION
~ CONTROL VALVE S~lI (STOPl INTERFACE CMO ENGINES EOS CUTOFF
<2, I ---~--
K39~2
FIGURE 2~59 (2 OF 2l
1011
ESE CMO ENGINE NO 2 CUTOFF
•
llSA3
-~:;M;-I--------ENGINE NO 4 CUTOFF
ESE CMO ENGINE NO 1 CUTOFF
ESE CMO ENGINE NO :3 CUTOFF
USA3 K37
ESE POWER TRANSFER
1021
115A4K6
S-J[ INTERFACE CMO ENGINES EOS CUTOFF
WY---115A9
1021
NOTE 1
lOU E5ECMO ENGINE PREVALVES CLOSE
28VDC
FULL PREVALVE CONTROL VALVE (TYPICAL S PLACES)
Jioc 1021
28VDC
$LV AS~50::
LOX PREVALVE CONTROL VALVE (TYPX;AL 5 PLACES)
!!QID ENGINE 1 ENGINE 2 ENGINE :3 ENGINE 4 ENGINE 5
115A4Kl 115A4K2 115A4K:3 115A4K4 115A4KS
C~D SEPARATICN AND RETRO EBW FIRIt-G IJ'.IITS ARM
LIFTOFF
L~: ~
ARMING
TRIGGER
SEPARATICN EBW FIRING l.J'.IIT
NO.2
ARMING RETRO ROCKET EBW TRIGGER FIRING LtHT
1\0 I
C<A'+1AND S-IC/S-II SEPARATION
Kl
SS 157 Q-i/lN 15
K2
sW SEL 115A5
ARMING
SEPARATICN EBW FIRING UNIT
NO I
TRIGGER
COJ+1AND FUEL PRESSURIZING VfJJ...VE NO 2 OPEN & TAPE RECCRDER RECORD
SS 002 CHAN 5
ESE
ESE RESET
"---I CMD He FLOW CONTROL VfJJ...VE NO. 2 OPEN
C~D FUEL PRESSURIZING VfJJ...VE ~JO 3 OPal
SS,055 CHAN 6
ESE "---I CMD He FLOW CCX\ITROL
VALVE NO. 3 OPEN
f- ----------s -1 ~ 7' I I I I I I I I
I
ARMING RETRO ROCKET EBW TRIGGER L ______________ --.:.:::::.:::.:.::!..../ FIRING <NIT ~:!!!~-------------l
NO. 2 ESE .... --{ESC ~O~~f---·
CMD TAPE RECORDER
r---.L-'---,RECORD
PLAYBACK
FIGURE 2-60
PLAY BACK RECORD
TAPE RECORDER
TO __
HIGH PRESSURE He OODLES
N.C.
,C~D FUEL PRESSURIZING VfJJ...VE NO 4 OPEN
SS 035 CHAN 7
SW SEL 115A5
ESE
ESE RESET
"---I CMD He FLOn' CONTROL VALVE NO.4 OPEN
~ _.(WX
(
SLV AS-503
.... TO ENGINES HEAT EXCHANGERS
2-80
~ , ~
~
120AIl K2
1021
CI)"MAND SEPARATION CAMERA ON
SSIIS
CHAN 12
~----------}-;- .
CAMERA EJECT CIRCUITRY
ESE CMD STROBE
120AIl Kl
LIGHTS PO.-IER ON 12041J KII
1022
IISA2Al
ESE
IDlO
CI)"MAND LOX TANK STROBE LIGHTS OFF
55141
CHAN 4
PWR SUPPLY
120AS79
FIGURE 2-60 A
•
IISA2AS
PHOTO TIMER -----
120AS80
PWR SUPPLY
120A578
2i.SEL IISAS
1011
r .!!.5.A. l.Ai KI
----6±tJ • SEE
FIG 2.72
•
<II
~~ ,< ~ ~
*
2.5 SWITCH SELECTOR CROSS··REFERENCE TABLES
SLY AS-503
This section is included in the handbook to facilitate the
translation of the switch selector channel identifications
from whatever form in which they may be obtained into the
form desired.
A switch selector channel may be identified by the channel
number, the octal code corresponding to that channel number,
or the complement of that octal code.
Some peculiarities in the downlink or ground transmission of
downlinked information, may cause the flight controller to be
presented with the switch selector bit pattern in inverted
order. Correspondingly, the complement of the inverted order
may appear, should the onboard system reject the true code.
Three tables are presented on the following pages. Each table
gives channel; true, complement forward; true, complement
reverse.
Table 2-1 lists by channel number. Table 2-11 lists by forward
octal true. Table 2-111 lists by reverse octal true. It should
be noted that complements increase ordinally from the bottom of
the page and can be read from the true octal list with minimum
difficulty. Table 2-111 includes an underscore beneath the
principal form corresponding to the normally expected bit
pattern.
2-81
* SLY AS-503
TABLE 2-1.- SWITCH SELECTOR CROSS-REFERENCE TABLE (IN SEQUENCE BY CHANNEL NUMBER)
FORWARD REVERSE Cha=el Octal Octal Octal Octal Number True ComE True ComE
1 177 200 376 001 2 137 240 372 005 3 142 235 106 271 4 141 236 206 171 5 002 375 100 277 6 055 322 264 113 7 035 342 270 107 8 077 300 374 003 9 023 354 310 067
10 143 234 306 071 11 163 214 316 061 12 115 262 262 115 13 162 215 116 261 14 015 362 260 117 15 157 220 ·366 011 16 021 356 210 167 17 037 340 370 007 18 063 314 314 063 19 122 255 112 265 20 156 221 166 211 21 101 276 202 175 22 121 256 212 165 23 042 335 104 273 24 022 355 110 267 25 075 302 274 103 26 175 202 276 101 27 135 242 272 105 28 174 203 076 301 29 074 303 074 303 30 003 374 300 077 31 043 334 304 073 32 103 274 302 075 33 034 343 070 307 34 117 360 362 015 35 036 341 170 207 36 076 301 174 203 37 001 376 200 177 38 061 316 214 163 39 017 360 360 01'( 40 057 320 364 013 41 116 261 162 215 42 136 241 172 205 43 176 201 176 201 44 062 315 114 263 45 123 354 312 065
2-82
,
* SLY AS-503
TABLE 2-1.- SWITCH SELECTOR CROSS-REFERENCE TABLE - Continued (IN SEQUENCE BY CHANNEL NUMBER)
FORWARD REVERSE Channel Octal Octal Octal Octal Number True ComE True ComE
46 102 275 102 275 47 155 222 266 III 48 054 323 064 313 49 014 363 060 317 50 161 216 216 161 51 016 361 160 217 52 056 321 164 213 53 041 336 204 173 54 164 213 056 321 55 144 233 046 331 56 124 253 052 325 57 032 345 130 247 58 071 306 234 143 59 153 224 326 051 60 133 244 332 045 61 044 333 044 333 62 112 265 122 255 63 007 370 340 037 64 072 305 134 243 65 052 325 124 253 66 111 266 222 155 67 067 310 354 023 68 031 346 230 147 69 051 326 224 153 70 154 223 066 311 71 027 350 350 027 72 173 204 336 041 73 053 324 324 053 74 004 373 040 337 75 024 353 050 327 76 106 271 142 235 77 146 231 146 231 78 166 211 156 221 79 152 225 126 251 80 172 205 136 241 81 005 372 240 137 82 026 351 150 227 83 151 226 226 151 84 131 246 232 145 85 147 230 346 031 86 127 250 352 025 87 Oll 366 220 157 88 134 243 072 305 89 107 270 342 035 90 047 330 344 033
2-83
~I
* SLY AS-503
TABLE 2-1.- SWITCH SELECTOR CROSS-REFERENCE TABLE - Concluded (IN SEQUENCE BY CHANNEL NUMBER)
FORWARD REVERSE Channel Octal Octal Octal Octal Number True ComE True ComE
91 125 252 252 125 92 065 312 254 123 93 045 332 244 133 94 013 364 320 057 95 073 304 334 043 96 033 344 330 047 97 006 371 140 237 98 104 273 042 335 99 126 251 152 225
100 132 245 132 245 101 066 311 154 223 102 046 331 144 233 103 171 206 236 141 104 167 210 356 021 105 114 263 062 315 106 165 212 256 121 107 145 232 246 131 108 105 272 242 135 109 025 352 250 127 110 064 313 054 323 111 012 365 120 257 112 113 264 322 055
2-84
* SLY AS-503
TABLE 2-11.- SWITCH SELECTOR CROSS-REFERENCE TABLE (IN SEQUENCE BY BINARY CODE FORWARD)
FORWARD REVERSE Octal Octal Octal Octal Channel True Comp True ComE Number
001 376 200 177 37 002 375 100 277 5 003 374 300 077 30 004 373 044 337 74 005 372 240 137 81 006 371 140 237 97 007 370 340 037 63 010 Oll 366 220 157 87 012 365 120 257 III 013 364 320 057 94 014 363 060 317 49 015 362 260 ll7 14 016 361 160 217 51 017 360 360 017 39 020 021 356 210 167 16 022 355 110 267 24 023 354 310 067 9 024 353 050 327 75 025 352 250 127 109 026 351 150 227 82 027 350 350 027 11 030 031 346 230 147 68 032 345 130 247 57 033 344 330 047 96 034 343 070 307 33 035 342 270 107 7 036 341 170 207 35 037 340 370 007 17 040 041 336 204 173 53 042 335 104 273 23 043 334 304 073 31 044 333 044 333 6l 045 332 244 133 93 046 331 144 233 102 047 330 344 033 90 050 051 326 224 153 69 052 325 124 253 65 053 324 324 053 73 054 323 064 313 48 055 322 264 ll3 6
2-85
* SLV AS-503
TABLE 2-11.- SWITCH SELECTOR CROSS·REFERENCE TABLE - Continued (IN SEQUENCE BY BINARY CODE FORWARD)
FORWARD REVERSE Octal Octal Octal Octal Channel True Comp True ComE Number
056 321 164 213 52 057 320 364 013 40 060 061 316 214 163 38 062 315 114 263 44 063 314 314 063 18 064 313 054 323 110 065 312 254 123 92 066 311 154 223 101 067 310 354 023 67 070 071 306 234 143 58 072 305 134 - 243 64 073 304 334 043 95 074 303 074 303 29 075 302 274 103 25 076 301 174 203 36 077 300 374 003 8 100 101 276 202 175 21 102 275 102 275 46 l03 274 302 075 32 104 273 042 335 98 105 272 242 135 108 106 271 142 235 76 107 270 342 035 89 110 111 266 222 155 66 112 265 122 255 62 113 264 322 055 112 114 263 062 315 105 115 262 262 115 12 116 261 162 215 41 117 260 362 015 34 120 121 256 212 165 22 122 255 112 265 19 123 254 312 065 45 124 253 052 325 56 125 252 252 125 91 126 251 152 225 99 127 250 352 025 86 130 131 246 232 145 84 132 245 132 245 100
2-86
* SLY AS-503
TABLE 2-11.- SWITCH SELECTOR CROSS-REFERENCE TABLE - Concluded (IN SEQUENCE BY BINARY CODE FORWARD)
FORWARD REVERSE Octal Octal Octal Octal Channel True Comp True Comp Number
133 244 332 045 60 134 243 072 305 88 135 242 272 105 27 136 241 172 205 42 137 240 372 005 2 140 141 236 206 171 4 142 235 106 271 3 143 234 306 071 10 144 233 046 331 55 145 232 246 131 107 146 231 146 231 77 147 230 346 031 85 150 151 226 226 151 83 152 225 126 251 79 153 224 326 051 59 154 223 066 311 70 155 222 266 111 47 156 221 166 211 20 157 220 366 011 15 160 161 216 216 161 50 162 215 116 261 13 163 214 316 061 11 164 213 056 321 54 165 212 256 121 106 166 211 156 221 78 167 210 356 021 104 170 171 206 236 141 103 172 205 136 241 80 173 204 336 041 72 174 203 076 301 28 175 202 276 101 26 176 201 176 201 43 177 200 376 001 1
2-87
* SLY AS-503
TABLE 2-111.- SWITCH SELECTOR CROSS-REFERENCE TABLE (IN SEQUENCE BY BINARY CODE REVERSE)
REVERSE FORWARD Octal Octal Octal Octal Channel ComE True True ComE Number
001 376 177 200 1 002 375 003 374 077 300 8 004 373 005 372 137 240 2 006 371 007 370 037 340 17 010 367 011 366 157 220 15 012 365 013 364 057 320 40 014 363 015 362 117 260 34 016 361 017 360 017 360 39 020 357 021 356 167 210 104 022 355 023 354 067 310 67 024 353 025 352 127 250 86 026 351 027 350 027 350 71 030 347 031 346 147 230 85 032 31i5 033 344 047 330 90 034 343 035 342 107 270 89 036 341 037 340 007 370 63 040 337 004 373 74 041 336 173 204 72 042 335 104 273 98 043 334 073 304 95 044 333 044 333 61 01i5 332 133 244 60 046 331 144 233 55 047 330 033 344 96 050 327 024 353 75 051 326 153 224 59 052 325 124 253 56 053 324 053 324 73 054 323 064 313 110 055 322 113 264 112
2-88
* SLY AS-503
TABLE 2-111.- SWITCH SELECTOR CROSS-REFERENCE TABLE - Continued (IN SEQUENCE BY BINARY CODE REVERSE)
REVERSE FORWARD Octal Octal Octal Octal Channel Camp True True Camp Number
056 321 164 213 54 057 320 013 364 94 060 317 014 363 49 061 316 163 214 11 062 315 114 263 105 0b'3 314 063 314 18 064 313 054 323 48 0b5 312 123 254 45 066 311 154 223 70 Ci67 310 023 354 9 070 307 034 343 33 071 306 143 234 10 072 305 134 243 88 073 304 043 334 31 074 303 074 303 29 075 302 103 274 32 076 301 174 203 28 077 300 003 374 30 100 277 002 375 5 101 276 175 202 26 102 275 102 275 46 103 274 075 302 25 104 273 042 335 23 105 272 135 242 27 106 271 142 235 3 107 270 035 342 7 110 267 022 355 24 111 266 155 222 47 112 265 122 255 19 113 264 055 322 6 114 2b'3 062 315 44 115 262 115 262 12 116 2bl 162 215 13 117 260 015 362 14 120 257 012 365 111 121 256 165 212 106 122 255 112 265 62 123 254 065 312 92 124 253 052 325 65 125 252 125 252 91 126 251 152 225 79 127 250 025 352 109 130 247 032 345 57 131 246 145 232 107 132 m 132 245 100
2-89
* SLV AS-503
TABLE 2-III.- SWITCH SELECTOR CROSS-REFERENCE TABLE - Concluded (IN SEQUENCE OF BINARY CODE REVERSE)
REVERSE FORWARD Octal Octal Octal Octal Channel Comp True True ComE Number
133 244 045 332 93 134 243 072 305 64 135 242 105 272 108 136 2Iil 172 205 80 137 240 005 372 81 140 237 006 371 97 141 236 171 206 103 142 235 106 271 76 ill 234 071 306 58 144 233 046 331 102 145 232 131 246 84 146 231 146 231 77 147 230 031 346 68 150 227 026 351 82 151 226 151 226 83 152 225 126 251 99 153 224 051 326 69 154 223 066 311 101 155 222 111 266 66 156 221 166 211 78 157 220 Oll 366 87 160 217 016 361 51 161 216 161 216 50 162 215 116 261 41 163 214 061 316 38 164 213 056 321 52 165 212 121 256 22 166 211 156 221 20 167 200 021 356 16 170 207 036 341 35 171 206 141 236 4 172 205 136 241 42 173 204 041 336 53 174 203 076 301 36 175 202 101 276 21 176 201 176 201 43 177 200 001 376 37
2-90
SLV * AS-503
2.6 SWITCH SELECTOR NOTES
A. The switch selectors are used by the Launch Vehicle
Digital Computer to control, initiate, or terminate func
tions in each stage. The switch selector is a series of
low power transistor switches individually selected and
controlled by a coded signal from the digital computer
through the data adapter.
B. An 8-bit code for a particular output set by the data
adapter appears at each switch selector. The stage select
is a specific line to a specific switch selector and its
presence is necessary to operate a particular register.
Prior to operating any switch selector, a check is made
of the complement code return lines. The presence of
28 Vdc on all of the lines indicates that all stage select
relays were properly reset on the previous switch selector
operation. The computer addresses the switch selector
from which an output is desired with the stage select line.
The 8-bit code is then set into the selected register. The
eight complement lines return to the computer via the data
adapter, and the transmitted code is checked. In the event
of error detection, the computer pulses the reset line,
resetting all registers to all zeros, and then transmits
the complement code. Either the code or its complement
operates the same relay driver. This gives the switch
selector the ability to work around an inoperative rel~
in the register. With the complement check passed, the
computer gives the read command to all selectors at the
desired time. This read command allows the switch selector,
(or selectors) that have been given a stage select, to drive
the addressed output. Addresses in the switch selector
registers are automatically reset to zero after the read
command. The register may also be reset by the LVDA over
the reset line without giving an output.
2-91
J I I I H I G I F • E \ I D I C I B 1 A
". ,. "'" DATE APPROVAL
: ,
8 8
- -~ ISWSEL STAG I
I SELECT LAUNCH VEHICt.£ DATA ADAPTER (lVDA)
>~ I [3> NOTE 1
7 7
ru;, ru;, S-lVB SWSEl S-{vBSW ENA8'-F. \ ENABLE 2 EIlABLEl m
EN ... BLE2
- I-
rm SWSEl I INSTRUMENT UNIT
I OtlTPtlT I I I I I I I I I I I I I I I I I I I I I I I
~O I SWITCH SElfCTOR
6 o~oo
L "',"''''' 6
IU IU ................................•.. ..... ~ ..... . ........ ~ .... . .... ..... . ... ..... . .... ..... ......... ..... . .... ..... .......... ..... ...... ..... ..... ..... ..... ..... . ........................... . ... . .......... ..... ........... ...... . ............. - •...................•.••••......... ..... ~ ..... .•....... ..... ..... ..... .... ..... ..... ~ .... ......... ~ .... ..... . .... . ....... ..... ...... . .... ..... ~ .... ..... ..... ......•..................... . ... . .......... . .... ........... ..... . .............. r-
S-IVB S-IVB
~ EVENT SW J S-IVS SWITCH
I SEL OUTPUT MONITOR I I I I I I I I I I I I I I I I I I I I I I I 5 D~ L SELECTOR 5
= L """"""
.... ~ l J l J ,
S-IC son, S-lVB s-lC,s-n, S-lC son, IU S-IC S-I1 IU S-IC Son S-IC S-D H ,-, s_nSWITCH S-DSWITCH S-ICSWITCH S-lC SWITCH SUPPLY 2BVDC ,-<". S-lVS S-lVBREAD S-lVB READ S-lVe ,-<", SELECTOR SELECTOR SELECTOR SELECTOR SW SEL VERIFICATION COMIl&ANO COMMAND COMMAND 1 COMMAND 2 REGISTER REGISTER s-re S_I1 S-IVBCOMMANO ENABl..E 1 ENABLE 2 ENABLEl ENABLE 2
RETURN 1 RETURN 2 S-lC, son SolVe COMMANO RESET 1 RESET 2 SWITCH SELECTOR ADORESS SWITCH SELECTOR ADDRESS VERIFICATION
4 4
, , ( 1 ( 1
8TH BIT 7TH BIT /.>TH BIT 5TH BIT 4TH BIT 3RO BIT 2ND BIT 1ST BIT BTH BIT I 7TH BIT /.>TH BIT 5TH BIT 4TH BIT JRD BIT 2ND BIT 1ST BIT
S-IVB S-IVB - .......••.......................... ..... ~ ..... . ........ ..... ..... . .... .... ..... . .... . ... ......... ~ .... . .... ..... ........ ..... .... ..... ..... ~ .... . .... ..... ..............•....................•......... .... . .......... . .... . ............. -.....•............................ ..... ..... ......... ..... ..... ..... ..... ..... ..... .... .....•... ..... ·····t····· . ....... ..... . ... . .... ..... ..... . .... . .... . ...............•......................•.... ····1··········· . ... . ............. S-II
~ s-rr
SWSEL TM I S-lI SWITCH
I OUTPUT I I I I I I I I I I I I I I I I I I I I I I I 0-5WC I SELECTOR
3 ~
L """'~" 3
S-II S-II ~ ....•............................. ..... ..... 1-•••••••• ..... 1-•••• ..... ..... ..... ..... .... ......... ~ .... . .... . .... ........ . .... . ... . .... ..... ~ .... . .... . .... 1-••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••• . .... . .............
- ~ ..................•......•...•...• ..... ········t···· . .... ..... .... . .... ..... ..... ..... . .... ~ .......•....................•..•............................. -..... ..... ..... ..... ......... . .... ..... ........ . .... ..... ..... . ... . ......•...... S-IC ~ S-IC
g~T~~~ ..J S-IC SWITCH SELECTOR I ~ I APlBO-25
L '" '"""" 2 [l>
2 NOTE DPIAO_l:3GOO-<ll
DPlAO-l:3GOO-<l2 DPIAO-l:3GOO-03 DPIAO-l:3GOO..()4
- -
~""O"" """""" • "'" """,,,.,,,,, OR MANNED SPACE¢RAFT CENTER I<lUSTON TEXAS
1 ~ SEQUENTIAL SYSTEM 1
i INTERFACE
I ~, '-u '" SLY Sllj rWG NO ,"n< ,
AS503i J 261 55)( 34 PAGE 2_92 SHEET " t
SECTION 3
ELECTRICAL POWER SYSTEMS
3.1 GENERAL NOTES
SLV AS-503
A. Electrical power for the Saturn launch vehicle is provided
by batteries in each stage to operate the functions of
that stage. In this manner, complete power isolation is
maintained between stages. Grounds are also isolated
except for a single point interconnection.
B. All batteries on the Saturn launch vehicle are 28 volts
except those used for chilldown inverters and auxiliary
hydraulic pumps which are 56v.
C. All power distribution is at 28 Vdc (except auxiliary
hydraulic pump and chilldown). Where ac or voltages other
than 28 Vdc are re~uired, the conversion is within and as
a part of the using e~uipment.
3-1
3 ELECTRICAL POWER SYSTEMS
SLV AS-503
3.2 IU ELECTRICAL SYSTEM
....
A. Electrical power for the IU stage is provided by four
silver oxide/zinc primary cell batteries located in the
stage. The batteries are designated as follows:
BATTERY VOLTAGE CAPACITY
+6DlO 28 ± 2 Vdc 350 ampere-hours
+6D20 28 ± 2 Vdc 350 ampere-hours
+6D30 28 ± 2 Vdc 350 ampere-hours
+6D40 28 ± 2 Vdc 350 ampere-hours
Each battery contains 19 active and 1 spare cell. The
electrolyte is potassium hydroxide (KOH).
B. At approximately T-50 seconds, all power distribution in
the IU is transferred from ground power to the IU batteries.
The transfer switches are disabled at umbilical release.
3-2
TABLE 3-1.- IU ELECTRICAL LOAD DISTRIBUTION
Total Total 28 Vdc 28 Vdc 6D10 6D20
Item Current Current Current Current
LVDA/LVDC - Boost 17.54 491.12 5.85 - Orbit 17.52 490.56 5.84
Switch Selector 0.07 1.96 0.07
Flight Control Computer S-IC Burn 2.37 66.36 0.79 8-II Burn 3.16 88.48 1.05 8-IVB Burn 2.13 59.64 0.71 Orbit 1.50 42.00 0.50
Control Signal Processor 3.00 84.00 1.00
Total Platform Requirement 11.14 311.92 11.14
5-Vdc Converter 0.46 12.82
Command Decoder 0.08 2.24 0.08
Q-Ball (S-IC Burn Only) O.5G 14.00 0.25
245 Multiplexer 0.15 4.20
S8 Telemetry Assembly Q.57 15.96
S8 RF Assembly 3.72 104.16
Fl Telemetry Assembly (B-1) 0.58 16.24
Fl RF Assembly 3.72 104.16
270 Multiplexer (F2) 0.10 2.80 0.10
F2 Telemetry Assembly (A-3) .70 19.60 .70
F2 RF Assembly 3.72 104.16 3.72
410 Multiplexer (J, 603A599) 0.30 8.40
410 Multiplexer (K, 603A594) 0.30 8.40
270 Multiplexer (PCM) 0.10 2.80
PCM/DDAS (301) Assembly 0.89 24.92
PCM RF Assembly (VHF) 3.75 105.00
PCM UHF Assembly 5.96 166.88
CIU 0.30 8.40
CCS Transponder & Power . 4.13 115.64 4.13 Amplifier
3-3
I
SLY AS-503
6D30 6D40 Current Current
5.85 5.85 5.84 5.84
0.79 0.79 1.05 1.05 0.71 0.71 0.50 0.50
1.00 1.00
0.46
0.25
0.15
0.57
3.72
0.58
3.72
0.30
0.30
0.10
.89
3.75
5.96
0.30
SLV AS-503
TABLE 3-1.- IU ELECTRICAL LOAD DISTRIBUTION- Concluded
Total Total 28 Vdc 28 Vdc 6DlO 6D20 6D30 6D40
Item CUrrent Current Current Current Current Current
TM Cal PCU 0.45 12.60 0.45
Tape Recorder 1.25 35.00 1.25
C-Band Transponder #1 0.89 24.92 0.89 (603A635)
(50% Standby, 50% 2000 prf)
C -Band Transponder #2 0.89 24.92 0.89 (602A634)
(50% standby, 50% 2000 prf)
Measuring Rack
#60lA401 1.16 32.48 1.16 #60lA402 1.21 33.88 1.21 #602A403 1.28 35.84 1.28 #602A404 1.09 30.52 1.09 #602A405 1.27 35.56 1.27 #602A406 1.22 34.16 1.22 #602A407 1.28 35.84 1.28 #602A408 0.38 10.64 0.38 #602A409 1.15 32.20 1.15 #603A669 0.93 26.04 0.93
ECS Temperature Control 0.34 9.52 0.34
Unit
Water S/O Valve (S-IC 1. 75 49.00 1. 75 Burn Only)
Pump 18.96 530.88 18.96
Heater #60lA69 5.00 35.00 5.00 #603A75 5.00 35.00 5.00 #603A76 5.00 35.00 5.00 #603A77 5.00 35.00 5.00 #60lA66 5.00 35.00 5.00 #60lA67 5.00 35.00 5.00 #60lA68 5.00 35.00 5.00
Totals
S-IC Burn 139.49 3905.72 32.57 33.19 37.88 35.86 S-II Burn 138.03 3864.84 32.83 31.19 38.14 35.87 S-IVB Burn 137.00 3836.00 32.49 31.19 37.80 35.53 Orbit 136.35 3817.80 32.27 31.14 37.58 35.31
3-4
III GJ ~ ., a. 1ij
Lo> .= I "0 cr- ..
.£ ,., ~
~ ~ .. OJ
40
35
30 32.57A
25
20
15
10
5 S-IC burn
,2.8,31:,31 32.2:S: '2.:,~ 32.:7Y:3 I 32.27A~
s-n burn
I I I I I I I I I I . . I U '1 nd First Second Second ntl e
First S-IVB burn / orbital coast S-IVB burn / orbital coast I Third S-IVB burn I of lifetime
I I I I '-----'----'-................ ~II I I II I I I III 1/1 II III/I I /
L.O. 1 2 3 8 9 11 12' 275 277 278 372 374 375 376
Elapsed time reference (to lift-off) in minutes
Figure 3-1.-IU battery no. 1 composite load profile.
>VI VIr"' u,< o Lo>
<II
f! OJ a. E
'" 1>1 .!: I
-.J -c
'" .£ >-~ OJ =: '" a:J
40 I I I I '
35 I I I I
30 11\ I 11\ I~~)\I \ I \ 33.19A-l 31.19A~ I 31.19A....l 31.19A~ I 31.19A~ I 31.19A~1 31.19A....l I 31.19A~
I I I 25 I I I
I I I I I I I I I
15 I I I I I I I I I I I I
5 I First Second I Second I Until end
S-IC burn S-II bum I First S-IVB bum I orbital coast S-IVB burn I orbital coast Third S-IVB burn I of lifetime
I I I 1--_-L-_--'---'----I.~11 I I I I I I J I I I I I I I I !I I I I I
L.O. 1 2 3 8 9 11 12 275 277 278 372 374 375 376
Elapsed time reference (to lift-off) in minutes
Figure 3-2.- IU battery no, 2 compOSite load profile.
>VI VIr-~< o 1>1
III
'" .. (IJ 0-E
Vl '" I .s O:l
.."
'" ~ >-.. ~ ;;; aJ
I
, ~, I -" , I ~I ~ V I ~ ! 1\ II \1
38.14A~ 137.80A~ :37.58A~ '37.80A~ '37.58A~'37.80A~'37.58A~ 35 37.88A
30
25
20
15
10
. Second 'Second orbital'Third S-IVB I Until end S-II bum , First S-IVB burn' Orbital coast S-IVB burn 'coast 'bum , of Ji.fetime 5 S-IC burn
I' 'I' L....-_....L--_.....L.--L---'-~!l I I I I I I I I 1 1 I I II I I 1 I I " I I L. O. 1 2 3 8 9 11 12 275 277 278 372 374 375 376
Elapsed time reference (to lift-off) in minutes
Figure 3-3.- IU battery no. 3 composite load profile.
>VI VIr-~< o Vl
'" .. ~ .. Cl. E
'" .: U) -a , '" -0 2 ,..
~ .. ... ... ~
35
35.86A
15
10
5 S-IC burn
I I I
35'.7A1l35'5~An:A IC~~ 35.31ji35.53A~i35.31A~ I I I I I I I , I 'I I , " , I I' , , " I , " , , 'I , , I I ,
, " I , , ISecond orbital' Third S-lVB 'coast I burn
Second S-TI bum I First S-NB burn I Omltal coast S-NB burn
I I , Until end of lifetime
L...._--I1..-_......L.---J1..--'-~1I II I II I !I' I II I' I I L.O. 1 2 3 8 9 11 12 275 277 278 372 374 375 376
Elapsed time reference (to lift-off> in minutes
Figure 3-4.- IU battery no. 4 composite I~ad profile.
>Vl Vlr ,< U1 o U)
3.3 S-IVB ELECTRICAL SYSTEM (Drawing 3.3.1)
A. Electrical ~ower for the S-IVB stage
batteries located in the forward and
stage. The battery descriptions and
as follows:
Batter;t Location Volta~e CaEacitil
Fwd #1 Fwd Skirt 28 +2 Vdc 300 ampere-hrs
Fwd #2 Fwd Skirt 28 +2 Vdc 25 ampere-hrs
Aft #1 Aft Skirt 28 +2 Vdc 300 ampere-hrs
Aft #2 Aft Skirt 562=.4 Vdc 78 ampere-hrs
*Does not include SSB/FM and FM/FM kit loads.
3-10
is
SLY AS-503
~rovided by four
aft skirts of the
expected usage are
EXEected Usas;e
82* ampere-hrs
9 ampere-hrs
24 ampere-hrs
63 ampere-hrs
SLV AS-503
TABLE 3-11.- S-IVB ELECTRICAL LOAD DISTRIBUTION
FORWARD BATTERY #1 (Figure 3.5)
FUNCTION
PCM/FM System Group
PCM RF System Group
Fwd 5V Excit Mod #1
Aft 5V Excit Mod
Fwd Battery #1 Heater
Fwd Battery #2 Heater
Range Safety System #1
02-H2 Burner Voter Regulator
Switch Selector Power
SSB/FM Transmitter Group
FM/FM Transmitter Group
CURRENT AMPS
5.85
5.00
0.21
0.01
15.0
3.0
0.34
0.095
0.04
4.5
4.0
FORWARD BATTERY #2 (Figure 3.6)
Range Safety System No.2 0.34
PU dc and Inverter
Fwd 5V Excit Mod No. 2
4.0
0.005
AFT BATTERY NO.1 (Figure 3.7)
LOX Chilldown Pump Purge Control Valve
Battery Heater Aft 1
Battery Heater Aft 2
Prevalves
LOX Flight Press System
Charge Ullage Ignition
Fire Ullage Ignition
Chilldown Shutoff Valves
J-2 Engine Cont Power (Coast)
J-2 Engine Cont Power (Start)
3-11
0.3
14.0
13.8
1.5
3.0
1.5
1.5
1.5
0.75
13.2
SLV AS-503
TABLE 3-11.- S-IVB ELECTRICAL LOAD DISTRIBUTION - Concluded
FUNCTION
J-2 Engine Cont Power (Burn)
Ignition Power
Ignition Power (Start Sequence)
LOX Tank Flight Press
First Burn Relay
Charge Ullage Jettison
Fire Ullage Jettison
LH2 Cont Vent Open
Eng Pump Purge Valve Open
LH2 Cont Vent Close
Eng Burn No. 2 Relay On
Coast Period
LH2 Repress Valve Open
LOX Repress Valve Open
Auxiliary Propulsion System*
02-H2 Burner Exciters
CURRENT AMPS
5.7
0.01
21.4
3.0
6.00
4.00
1.5
1.5
1.5
1.5
4.95
0.10
3.0
3.0
20.0
2.5
AFT BATTERY NO.2 (Figure 3.8)
LOX Chill down Inverter
LH2 Chill down Inverter
Aux Hyd Pump Flight Mode
18.0
25.0
45
(max)
*Includes operation of No. 1 and No. 2 70 lb ullage engines
3-12
~.
~. ::E: ct:
Cl ct: 0-...J
-IZ w cr: cr: ~ u
'" ~ o. ~
SLV AS·503N
;- 200 r-- I I I
- T M0019 FULL SCALE READING;
1991 r-:'--POWER~T~ANSFER -rr.jTERNA~ _
21 :1 / RANGE S~FETY SYSTEM NO: 1 OFF -
II f Ii' fl--; '-l ~-, !
I ' ' , " III I , :
I . i
! I "I f. : i I _ _ I '
- END OF S- IVB MISSION :\: II I 1 - l ;
I I I
o
8 I I '
61 II I 1 tJ 4 I 1/
2 I II
" L 1\ RO 1 ~~--~4--------~1--------
MISSION TIME (HOURS FROM RANGE ZERO)
Forward Battery No.1 - Current Profile
I
FIGURE 3.5 3-13
- ~ VI
~, 5
i ~ '-', 4
~ l ~ ~
3
> o
I v: PU ACTIVATE I . I r PU DEACTUATE I 5.4 "
,¢ i~~~:NrE"NSFER I ; /1---';"11 CPU BOILOFF_ BIAS, CUTOFF ON
2 OFF
SL, AS-503N
I ~ '/ r RANGE SAFETY SYSTEM NO.
L.o ' 4.4 f l "Ii I PU INVERTER AND DC POWER QFF~
I ... \1 4.0
i
'-{} !~: '" I I' I I I I , RO RO +08:46.9 TB5 TB5 +01:40.0 TB5 +03:20.0
MISSION TIME (TIME FROM RANGE ZERO/TIME BASE - MIN:SEC)
Forward Battery No.2 - Current Profile (Sheet 1 of 2)
TB5 +05:00.0
FIGURE 3.6 3-14
~I Vl' 0..
:fi ~
Iz W 0:: 0:: . ::>: u
o N o ~
2 ) f-M0020 FULL, SCALE READING
I- ~CONTINUED FROM FIGURE 2 •• 10-6 (SHEET 1)
I-I I
SLY 'AS-503N
~ , I- PU VALVE HARDOVER POSITION ON
(/U INVERTER AND DC POWER DN
\ ~ PU VA~VE HARDOVER POSITION OFF I-
)
l-
I '\ \, ~ V'lVE H'RDOVER, POSITIDN DN. ' r-
.. \ ~ VAlVE HARDOVER
I- POSITION OFF '\. PU INV. AND
l- I I DC pm~ER OFF
~ " , ~ -"1 ,f..: ~ n
TJ II I END OF I l-
I-
l-i S-IVB 1
l- I MISSION ~I
?' 1 J,
LLl. . , 'J. ! (l- ff. T {: . TB5 +00:05:00.0 TB6 +00:07:30.1 TBB +00:03:20.2 TB9 +00:30:00.0
TB5 +03:30:00.0 TB6 +00:09:43.0 Ta8 +00:07:43.0 TB9 +01 :03:40.2
MISSION TIME (TIME FROM TIME BASE - HRS:MIN:SEC)
Forward .Battery No.2 - Current Profile (Sheet 2 of 2) FIGURE 3.6a
3-14a
200
~
50
~
~ 40 ::E: <l; ~
l-z lLJ c:r: c:r: :::> u 3D
I
~
N 0 o. ;:';'
20
10
0
.,
I"-M0021 I FULL SCALE hADING I I I I-POWER TRANSFER INTERNAL I
f--I I FIRST BURN RELAY ON I I I I 39.10 I . FUEL .INJECTION
36. 1 ~ I I TEMP OK BYPASS ON---
SPARKS OFF
I l-CHARGE ULLAGE
JETTISON ON I
,.....FIRE ULLAGE·
I
SLV AS-503N
;i' JETTISON ON
I I 1/ ULLAGE I ~CHfRGING RESET S-IVB ENGINE START ON---, I I
I I IVULLAGE FIRING-I 25.65
RESET
: FIRE ULtGE IGNITIOt ON:\.
__ ..r-_
23.70
I LOX TANK FLIGHT . I PRESSURE SYSTEM ON~ I I I I PRE VALVES CLOSE OFF .
I I \\ I CHARGE ULLAGE \ \' I IGNITION ON-- . L 8 81
: \ \ :r -~-I 3.22 4.72 ' -..J r' :f=-i,\ A A • I I I • I I • I , I • • •
RO RO +8:00 RO +8:38 MISSION TIME (TIME FROM RANGE ZERO - MIN:SEC)-
Aft Battery No.1 - Current Profile (Sheet 1 of 9)
• • I
-,
I
RO +9:00
FIGURE 3.7 3-15
~
VI CL ::E: c.: ~
I-z: w 0:: 0:: :::J u
I
~
N 0 o· ::E:
SL~ AS-503N
2001~MOO:~"'F~LL SCALE 'READING
•
50 ~CONTINUED FROM
FIGURE 2.10-10 (SHEET 1)
40 ENGINE PUMP
PURGE CONTROL POWER ON
7 30
~;c25 ~'J2-
20
10
0 A A
RO +9:00
RO +1·1 :21.9
~ENGINE CUTOFF ON ~LH2 TANK CONTINUOUS VENT RELIEF OVERRIDE SHUTOFF VALVE OPEN ON .
S-IVB APS ULLAGE ENGINE II RELAY NO. ,1 ON I
/ ~LH2 TANK CONTINUOUS VENT !oS-IVB APS ULLAGE ENGINE ORIFICE SHUTOfF VALVE· .
OP~N OFF RELAY NO. 2 ON
/ / I /; V LH2 TANK CONTINUOUS VENT ~FIRST BURN I;J RELIEF OVERRIDE SHUTOFF
i;j RELAY OFF I VALVE OPEN OFF ,
I: I Ij I S-IVB .APS UlLAGE I .:'. ,..LOX TANK FLIGHT ENGINE RELAY' "~I PRESSURE SYSTEM OFF IV NO. 1 OFF I I I i LH2 TANK ': S-IVB lAPS ULLAGE
.,1 CONTINUOUS VENT ORIFICE A /~)r-ENGINE RELAY I SHUTOFF VALVE OPEN ON~ NO. 2 OFF .
j,_ I 8.87 ,8.87 r ENGINE PUMP
~RGE CONTROL POWER OFF 2.87 I .f--'H32
, ,,1---5 TB5 TB5 , TB5 T85 T85 T85 v T85
+00:20.0 +00:40.0 +01 :00.0 +01 :20.0 +01 :40.0 +10:02.6 T86
MISSION TIME (TIME FROM RANGE ZERO/TIME BASE - MIN:SEC) . Aft Battery No.1 - Current Profile (Sheet 2 of 9)
FIGURE 3.7a 3-15a
M0021 FULL SCALE READING
I I . . CONTINUED FROM FIGURE 2.10-10 (SHEET 2)
~
SLV AS-503N
,
LH2 TANK CONTINUOUS VENT VALVE CLOSE ON
I I BURNER LH2
~' 40 \ \ '; I / PROPELLANT VALVE ::E: co:
I-' z: W 0::: 0::: => u 30
N 0 0 ::E:
20'
LOx' TANK VENT AND NPV VALVES BOOST CLOSE ON
I I I LH2 TANK VENT AND LATCHING
RELIEF VALVE BOOST CLOSE ON
OPEN OFF I r ' BURNER LOX SHUTDOWN VALVE OPEN OFF I
~Et~~1 ~6~ ~L~~Gr ENGINE L~~: \ ~ I U{ S-IVB APS ULLAGE ENGINE Ii I I
10 RELAY NO.2 ON . I-i . '-t---t-;.;==f---t----t-H'---1 I" U ';;j
7.32 V r 0,1-1 ' TB6 TB6 +00:30.0 TB6 +00:40.0
MISSION TIME (TIME FROM TIME BASE - MIN:SEC)
'Aft Battery No.1 - Current Profile (Sheet 3 of 9)
TB6 +00:50.0
FIGURE 3.7b 3-15b
SLV AS-503N
200 - ,
~Md021 FULl SCALEiREADINl r-S-hB APS IULLAGE
ENGINE RELAY·
< I I I I I NO," 2 OFF I I~FUEL INJECTION
50
CONTINUED FROM FIGURE 2.10 -101 (SHEET 13)
" TEi~P OK BY,PASS O~
S-', VB APS' ULLA" ENGI" RELAY NO. 1 OFF ~ I' I LOX TAJK
': !rPRESSURIZATIm , SHUTOFF VALVE I!. OPEN I
~ 40 ,til"-.J-SPARKS OFF_
! . S-IVB ENGINE START ON~ '/!!'n I , ~}j
!5 'Uj" LN'r"0PEL)"T VAl" CLOSIE OFF i ti I ' ENGINE ~ I PUMP PURGE i3 30 . BURNER LOX L-' CONTROL VALVE' , LN' TANK CONTINUOUS VENT VALVE CLOSE OFF~ VSNUTOOWN -; l'-tENABLE ON--
~ I I I I I I ! ON I I N LN' ,'ANK CONIINUOUS'VENT V!LVE CUisE ON~ , VALVE CLOSE I'T7 - 00'07.0\
BUTER LH2, PROPELlANT VALVE CLOSE ON , . . I '-- . 20 I -, h'rBURNER LOX .
I I I . I I I; /1 VALVE CLOSE S-IVB APS ULLAGE ENGINE RELAY NO. 2 ON~ri/! SHUTDOWN
S-IVB APS ULLAGE ENGINE RELAY NO. 1 ON 1\ L i OFF I I : , I' I'· I SECOiD BURN RELAYS ON\ I /7-I11. . .£? . .
10 J . 8 27 I I V"'VALVES CLOSE ON ., I LS;'VB EN~INE CUTOFF OFF I r-PREVALVES CliSE OFF
o~i- I I TB6 v TB6 TB6 TB6 TB6 TB6 TB6
+00: 50. 0 +04: 19.0+05 :00. 0 +06 :00.0 +07 :00.0 +08:00.0 +09 :00. 0 MISSION TIME (TIME FROM TIME BASE - MIN:SEC)
Aft Battery No.1 - Current Profile (Sheet 4 of 9)
TB6 +10:00.0
TB6 +11 :00.0
(Tn
FIGURE 3.7c 3-15c
....... til "-:ti: Iz w c:: c:: ::::> u
~
'" o o ::;;:
1~Mo0211 FULL SC4LE READINb I I I
<'--CONTINUED FROM FIGURE 2.10-10 (SHEET 4) , I I' I ) _S-IVB ENGINE CUTOFF
I~S-IVB APS ULLAGE ENGINE RELAY NO.1 ON '~S-!VB APS ULLAGE ENGINE 'RELAY NO.'2 ON II1-LH2 TANK CONTI'NUOUS VENT ORIFICE III SHUTOFF VALVE ,OPEN ON
) 11 ,,' VLH21TANK CONTINUOUS., VENT RELIEF ,II
OVERRIDE SHUTOFF VALVE OPEN ON III I I
ii' I ~SECfND BURN RiLAY OFF
) '" "'~ LOX'TANK FLIGHT PRESSURE SYSTEM OFF III F-
IJI / II' ) 'r ,-LH2 TANK CONTINUOUS VENT ORIFICE
r /.- SHUTOFF VALVE OPEN OFF , , , . LH2 TANK CONTINUOUS VENT RELIEF
l OVERRIDE SHUTOFF VALVE OP~N OFF ,
) 9.02 I ,
I
TB7 TB 7 +00: 1 0 . 0 MISSION TIME (TIME FROM TIME BASE"- MIN:SEC)
Aft B.attery No. 1 - Current Profi 1e (Sheet 5 of 9)
SLV AS-503N
.S-IVB APS ! Ul~GE ENGINE RELAY NO. 1 OFF
;- S-IVB APS ULLAGE -V ENGINE I RELAY I NO. 2 0 FF
1-,,\,
I
I
TB7 +00:20.0": TB7 +10:80.0
FIGURE 3.7d 3-15d
200
G-I .. I I M0021 FULL SCALE READING
I I I CONTI NUED FROM FI GURE 2.10 - 10 501 (SHEET 5)
I I
SLY AS-503N
40 "-- BURNER LOX
~ V~~
'
SHUTDOWN -
§: OPEN ON ~
!2: BURNER LH2 ~ 30 PROPELLANT g§. VALVE--U OPEN OFF
~ LOX TANK VENT AND NPV N VALVES BOOST CLOSE OFF . I BURNER LOX
~ I I LH2 TANK VENT AND LATCHING SHUTDOWN 20 LOX TANK VENT.AND NPV RELIEF VALVE BOOST CLOSE OFF VALVE OPEN
VALVES BOOST CLOSE ONl OFF
I LH2 TA~K VENT BURNER AND LATCHING RELIEF EXCITERS
VALVE BOOST CLOSE ON OFF
10 I~\ I I !L44-,
I I "(BURNER ) PRE VALVES I. EXCITERS ON CLOSE ON 0
~; BURNER LH2 1.47 q f-'r I PROPELLANT
o VALVE OPEN ON TB7. TB7 TB8 TB8 TB8 Tlltl TB8 Tll8
+ 10: 00.0 +10: 02.6 +00: 30.0 +00: 40.0 +00: 50.0 +02: 19.0 +03: 20.0 +04: 06.0 +04: 16.0 MISSION TIME (TIME FROM TIME BASE; MIN:SEC)
Aft Battery No. 1 - Current Profile (Sheet 6 of 9) FIGURE 3.7e
3-15e
V)
":E: q:
fZ W 0:: 0:: => U
N o o :E:
2 --
00
<~ M00211
FULL SCALJ READING I I
~CONTINUED FROM FIGURE 2.10-10 (SHEET 6)
LOX TAN1K PKESSURIJATION SHUTOFF VALVE OPEN~ I I
FUEL INJECTI~N TEMP OK BYPASS~ I\.
SLV AS-503N
50
S-IVB APS UiLA" ENGIN) RELAY NO.1
, OFF ~ ~ .. SPARKS I ~ ·OFF
ENGINE START ON~I. . '""r 40 r--BURNER LH2 PROPELLANT VALVE CLOSE ON
I 1-. \ I
I I I l ' ~BURNER LH2 PROPELLANT VALVE CLOSE OFF
Is! I VB ~S .
I I I
30
r--BURNER LOX SHUiDOWN VALVE CLOSE OFF
, ,.... LH2 TANK CONTINUOUS ULLAGE I
;; VENT VALVE CLOSE ON ENGINE I RELAY j
~LH2 TANK CONTINUOUS I NO .. 2 OFF L, VENT VALVE CLOSE OFF
20 i I • , ,
J~ ~BURNER LOX SHUTDOWN VALVE
I , I
I I ~U I
I 1\ CLOS~ ON I . PREVALVES CLOSE OFF /1'-Df--!""'~ S-IVB APS ULLAGE ENGINE
I
RELAY NO. 12 ON I ENGIN~ CUTOFF OJF~ S-IVB APS ULLAGE ENGINE, I I 0L-../\. RfLAY NO. 1 pN
I
TB8 TB8 TB8 TB8 TB8 T138 TB8 T138 TI313 TIl8 +04:16.0 +06:20.0 +06:30.0 +06:40.0 +06:50.0 +07:00.0 +07:10.0 +07:20.0 +07:30.0 +07:40.0
MISSION TIME (TIME FROM TIME BASE - MIN:SEC)
Aft Battery No.1 - Current Profile (Sheet 7 of 9) FIGURE 3.7f 3-15f
SLV AS-503N ~
M0021 FULL SCALE READING START BOTTLE VENT CONTROL VALVE 9PEN ON I I . I
CONTINUED FROM FIGURE 2.10-10 (SHEET 7 START BOTTLE VENT CONTROL VALVE OPEN OFF
501 I I I I I I T ( I ENGINE PUMP PURGE CONTRO VALVE ENABLE ON '
I ENGINE MAIN'STAGE ~ , I {I', CONTROL VALVE OPEN OFF , VI 40 r } r , I a. ,~
. ENGINE HELIUM LH2·TANK CONTINUOUS [CONTROL VALVE VENT ORIFICE SHUTOFF OPEN OFFI
~ idVALVE OPEN ON LOX TANK NPV z: I I . w LH2 TANK CONTINUOUS VALVE LATCH ON ~ I ~ VENT RELIEF OVERRIDE LOX TANK NPV u 30 7 SHUTOFF VALVE OPEN ON rVALVE LATCH
I { OFF ;:;:; I .- I( / rSECOND BURN ~ELAY OFF / ENGINE g 22·Ll / lLOX TANK FLIGHT HELIUM ::;: f--(.I PRESSURE SYSTEM OFF CONTROL
!~VALVE OPEN ON
VAL VE OPEN OFF I I I PHASE I I CONTROL
LH2 TANK CONTI NUo'7U, / /1 I ENGINE VENT ORIFICE SHUTOF I IGNITION
I r- LH2 TANK CONTINUOUS. . ~8 64_.1 . VALVE OPEN 10f-1 ---l--t--f.-/ii-rVENT RELIEF, ~!--f ~. f-i,i ~ I, LOX TANK
OVERRIDE J~ ~ r--r iL\ i ~ NPV VALVE ~~~J~FF !~ENGINE HELIUM CONTROL . ~ Lt OPEN OFF OPEN OFFr, VALVE PPEN ON I \.LOXTANK1·
TB9
Aft Battery No.1 - Current Profile (Sheet 8 of g)
NPV VALVE OPEN ON TB9,
+11 :50.0
FIGURE 3.79 3-15g
M0021 FULL SCALE READING
CONTI~UED FROM I 1 FIGURE 2.10-10 (SHEETS)
50 I I
END DF S-IVB MISSIDNJ
LOX TANK PRESSURIZATION SHUTOFF VALVES CLOSE
~401 1 . I' 1\ <n ":::;: q:
Iz
ENGINE PNEUMATIC SYSTEM VENT CLOSE
I LH2 TAJ REPRESS CONTROL VALVES OPEN OFF
~3°1 ), \/ \ I u LH2 TANK LATCHING
RELIEF VALVE LATCH ON LH2 TANK
~ 1 I·· " LATCHING ~ LOX TANK PRESSURI ZATION RELIEF VALVE ~ [SHUTO~F VALVES OP~N OPEN OFF
20 I LH2 TANK LATCHING _ LH2 TANK LATCHING RELIEF VALVE OPEN ON RELIEF VALVE , 14 • 64! LATCH 0 rF 1------1" ~.
; 1 h U' 1----;1 f-1 . ENGINE IGNITION I '-ENGINE .. ___ H f--l '
VALVE CLOSE VENT OPEN ~ ~r
I LH2 TANk REPRESS ENGINE PUMD I
SLV AS':503N
PHASE CONTROL I' PNEUMATIC SYSTEM I 8.64
1 . I ENGINE HELIUM CONTROL V/ILVES PURGE CONTR~L L CONTROL VALVE OPEN OFF OPEN ON
i VAL VE ENABLE OFF-./~
B9 TB9 T139 TB9 T139 TS9 +00:13:00 +00:30:00 +00:30:10' +00:30:20 +00:33:35 +00:36:56 +01 :03:40.2
MISSION TIME (TIME FROM TIME BASE - HRS:MIN:SEC) .
Aft Battery No.1 - Current Profile (Sheet 9 of 9) FIGURE 3.7h 3-15h
~
til a. ~ ~
I-z w· 0::: 0::: ~ U
N N 0 0 ::::
SL} i\~.,-C;('l~" . __ ".;..J.'
20 1"'-~M0022 I FULL StALE REkDING " I
I 12 )
) 100
8 )
6 )
40 )
I 20
o
I ~LOX CHILLDOWN PUMP OFF
V
88.4 I LLH2 CHILLDOWN Pirt,POFF ~I I I
~POWER TRANSFER INTERNAL ! V ! I 70.4
RO
1- - -A~X. HYD. PUMP
I
+2:00 +4:00 +6:00 +8:00
MISSION'TIME (TIME FROM RA~GE ZERO/TIME BASE - MIN)
Aft Battery No.2 - Current Profile (Sheet 1 of 4)
ftT. MODS OFF~
45.41 I, . , I
I A
+10:00
<.
: I
I 0.4 r ----r
TB5 +4.1 SEC
FIGURE 3.8 3~16
--. Vl a. ~ ~
20
12
10
I- 8 z w or: or: => u
N N o o ::;:
6
4
2
U~MOO)2 FULL sclLE READIN~ )
)
)
)
)
I )
CONTINUED FROM FIGURE 2.10-14
)e I 0.4 I I TBS TB5 +1 +4.1 SEC
~AUX. HYD. PUMP FLT. MODE ON
II (300 AMP SPIKE)
,
,~AUX. HYD. PUMP '! . FLT. MODE OFF . /. !i , 45.4 . 1-, ----I !
I I I
iSh'" 1 o~ I I
I 0.4 i TB5 +2 TBS +3 TB5 +4
MISSION TIME (TIME FROM TIME BASE-HRS)
. Aft Battery No.2 - Current Profile (Sheet 2 of 4)
I
.-, ' ~~.
;,5-S0 3:;
'-TB6
FIGURE 3.8a 3-16a
~
V'l a.
~ I-z w 0:: 0:: ::::> u
N N 0 0 :E:
S' '!. -' {,S':S03:;
2001\.-- I I I l "--M0022 FULL SCALE READING
120r!----~----~----+_----+_----t_----~--~----~----_+----_+----~~~~ AUX. HYD. PUMP
FLT. MODE ON (300 AMP SPIKE)~
J'... 100
" BO
60
40
20'CONTINUED FROM FIGURE 2.10-14 (Sheet 2 of 4)
Oi .. I 0.4
r-LOX CHILLDOWN PUMP ON
I I I LH2 CHILLDOWN ItLH2 CH~DgWN P~/o1P~ _ . / pUMP OFF,
Z·· I - I as.4·1 T· IT ~CHLoWN , I I _ I, _ L I PUMP OFt
--
63.4 ._- /~~'i
AUX. HYD
45.4, .I....J __ .... I
45.4 PUMP I FLT. , MODE-
OFF
TB6 TB6 +1 TB6 +2 TB6 +3 TB6 +4 TB6 +5 TB6 +6 TB6 +7 TB6 +B TB6 +9 TB6 +10 TB7
MISSION TIME (TIME FROM TIME BASE - MIN)
Aft Battery No.2 - Current Profile (Sheet 3 of 4) FIGURE 3.Bb
3-16b
-..
<
...... en 0-
~ ---I-2!: uJ cr: cr:
.' . ::> t..>
'" '" 0 0 ::;::
"-;'
' ... , ,." ...... _, .... ., SLY
'. AS-503N "';if
20 DC\- ,I I" I •
END bF S-IVB JISSION-J' •
~ M0022 FULL SCALE READING .
I I .'
DI--AUX. HYD. I PUMP FLT. I
MODE ON (300" I AMP SPIKE)\ ~LOX CHILLDOWN PUMP ON I , "' . I
D ~LH2 CHILLDOWN PUMP ON ~LH2 CHILLDOWN PUMP OFF
7 V • SS.4 I I
I
12
10
;r--LOX CHILLDOWN PUMP OFF I 0 I I
/ I
l-I
63.4 " , 63.4 " I --- --- I ) I
S
6
IrAUX •. HYD. PUMP I- _4§.:'L 45.4 FLT MODE OFF
;1-I
I "~ )
I 4
I I I .
) CONTINUED FROM . •
FIGURE 2.10-14 I
(Sheet 3. If 4) I ~ 0.4 L-.rA~ I~ A
2
TB7 TBS TBS +2 TBS +4 TBS +6 TBS +S TBS +10 TB9 TB9 TB9
MISSION TIME (TIME FROM TIME BASE - MIN)
Aft Battery No.2 - Current Profile (Sheet 4 of 4)
+30 ;'06 "+01 :03: 40.2
FIGURE 3.Se 3-16c
"-J
SLY AS-503
therefore, receive a constant flow as system sphere
pressure changes.
F. Electrical/electronic equipment in the S-lVB forward
skirt area is thermally conditioned by a heat transfer
subsystem using a circulating coolant for intermediate
heat transport. Principle components of the subsystem,
located in the S-IVB stage forward skirt area, are a
coolant distribution subsystem and cold plates, figure
4-3. In the flight configuration, thermally conditioned
coolant is supplied to the S-IVB thermo-conditioning
system by the lU environmental control system. The
electrical/electronic equipment is attached to the cold
plates and dissipates heat by conduction through the
equipment's mounting feet to the cold plates and coolant.
The coolant consists of a,60 percent methyl-alcohol and
40 percent distilled water solution that contains a
corrosion inhibitor. It is supplied through quick dis
connect fittings at the lU/S-lVB interface at a flow_ rate
of 3,500 ±175 pounds/hour and is maintained within tempera
ture limits of +40 to +60oF. Operating pressure
at the supply interface is 42 psia, and the nominal subsystem
differential pressure is 14.25 psi at the given flow rate.
4-3
8~-----H-------L-I----~G~----~I------r=F======~I========E=======.~==~~D~::::=~I~~~c~!======~I~ ____ ~B ______ l~ul.~"~,~~.~A~~,~,~",~.~~,, ~
19-601 AUXILIARY POWER DISTRIBUTOR
6041 8US 602A34
CONTROL DISTRIBUTOR 6OlA2 8
-
7
-
6
-
4
~20-601
60408AT CURRENT
~OTS'Ll.O':!~.J
~ I
BATTERY 6040 601A10
~17-&Ol
6020 SAT CURRENT
\ OTOlOOA]
Y -I" ----
3
BATTERY 6020 601A8
~16-601 6010 BAT CURRENT
OTO 100A
_ '7
-
BATTERY 6010 601A7
~12-601 6011 BUS VOLTAGE
~
+60)0
24 TO 32 Vat 01>1AO-18-03
~14-601 &131 BUS VOLTAGE
~ O~4
POWER DISTRIBUTOR 601Al
POWER TRANSFER SWITCH
~ .+6M2 I +60211 I'
VOLT4GE
OPlA - -08
T""'''OC
lc " .... : ESE.
~'.o""'--1I---\...J-ll LYDA/LVDC l ~- .. 603A29
AUXILIARY POWER DISTRIBUTOR 6OlA33
+(.011
I'-------''';:-i"', :.-~-_!__ll MEA$URI'IG RAn ~ 1 601A401
K9-1'~~----lI---I 1 MEASURING Met:; ~ L 601A402
I C-SANO
~11 ~~-o-----ll--j [ TRAII~~~~~~~ NO 1
K12 ~:-~---1f--I CCS TRANSPONDER _ I 603.0.631,
+6021
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"' ~ I--{ COOLING SYSTEM .. ELECCOrITROLASSV
55, ESE 60)A40
L----fi +602111' +6032
.'-__ -'--___ ~ : ::E •
+6010
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4 l ~~r:t~ : +60111 I ESE
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[ HEATER 601A66
.-----~ : F2 1,-----V-' ~----_I____I COOLING PUMP
~.~~----ll---II MEASURING RAn -... L 602A405
~ l NO 1 601A37
0+60111
• _____ ~: ESE
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+6011
~':-~---lf--1 I MEA.SURING RACK -.. I 6021\406
~':-~----ll---I I MEASURING RAC/( - ... 6031\669
~,~-o-----ll--j [I MEASURING RACK .- 6021\407
~.~~----ll---II MEASURING RACK ... L 602A4D9
~ ____ ~_--I_--I 1 MEASURING RACK .. l 602A408
1
L HEATER 601A67
,., ... "n (~i'-'''.'-.::''.::n;::'::''---t-------------I-----.?.~ +6011 1:1 ..
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L HEATER 601A69
+6D41
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+60110 m
SWITCH SELECTOR l 603A17
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K7 ~ I ~~;~~~ I
l TMCAlASSV ~' 602A602 J .,,"
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~." .--"-----I-IIL
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.--~,;;,~ ~ . .-&---JL1- FI RF ASSV I .. 60ZAS89
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" ... ~~----t--II PMC ODAS Assvl - L 602AS95
1
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1 K28-3..- l
I K28-3 .. l
PI RF ASSV 602A600
HEATER 603A76
HEATER 603A77
I
I
I
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K10~ 1
1
l
F2 TM ASSV 602A590
F2 RF AS5V 602.0.591
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If-------------.l.--- TO s-rc STAGE (28 YOC)
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ASSV 603A20 I
DR -r:;;;-.... MANNED SPACECRAFT CENTER HOUSTON TEXAS
S POWER DISTRIBUTION
5
4
f-
3
f-
2
I--
•
IGNATURES ~ NATIONAL AEROI'IAUTICS & SPACE AOMINISTRATION
?" ... , IU 1 ~,
no AUTH ....
44X 34 PAGE 3-5 SHEET OF
8
7
6
5
4
3
2
B> Rb
H
.: ~
'" .0 bOll
~
~~E[~
" ~ '"
H2
0 ,
VAPOR . . VENT ,
0; ~ 3000 tBS/HR
METH/H 20
"~ ------n---------- ,'" " ---M, "'",' u: '" lOGIC INHIBIT 6021
28 VO<:
G
~ -1 - -@-;-®
+bD21 28 YO<: "" ----------M"", -J © - ®
ESE I---- - ESE ESEI-- ~ESE
~-~
CHI09 SS 025
CldD SENSOR BIAS ON
ESEt---
CHllO SS 064
CMD ECS HON CONTROL POWER OFF
SWITCH S£lECTOR
c;~ cliic7 SS 105 SS 145
CMO"20 CMDHlO
VLVCLOSEO VLVQPEN
•~
601 PRESS, COOLANT MANIFOLD INLET
METH/H 2 0
<-LVOA
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FLOW RATE IU EXIT COOLANT 1 5 TO 25 GP
'1' co
D c
t •
I · t-~· t
PRESS JrrCH FILL CUTOFF AT 3000
PSI'" ESE '}_.
PREFLIGHT PRESS SWITCH 5T_124 SHUTOONN AT 925 PSIA ESE N
1 • t {--1'
,
METH/H 2 0
8
--fi -::- ESE FILLAND
EMERGENCY VENT
A
~ IEMP CONTROL ( COMPUTER -100' TO 200' C DPlAO-V18-10-00
NOTES f'l-.. EACH COLO PLATE IS CAPABLE OF DISSIPATING l7' APPROXIMATELY 420 WATTS
SIGNATURES DATE NATIONAL AERONAUTICS & SPACE ADMINI$TRAT
DR .$ 73'_ '7"'1$ MANNED SP~CRAFT CENTER I<lUSTON T ----j
~~GN~..f'UZ- ::: ENVIRONMENTAL CONTROL ENGR7, ,I' SYSTEM
41.1 SHEET 1
8
7
6
5
4
3
2
SECTION 4
ENVIRONMENTAL CONTROL SYSTEM
4.1 ENVIRONMENTAL CONTROL SYSTEM NOTES
SLV AS-503
A. The Environmental Control System (ECS) controls the
thermal environment for the IV and S-IVB electronics
equipment and also conditions the GN2 supplied to the gas
bearings of the ST-124 stabilized platform. The main
components of the system are an inflight sublimator,
a water accumulator, a methanol/water accumulator, cold
plates and GN2 storage spheres. The coolant solution
used in the ECS is 60 percent methanol/40 percent water.
B. During preflight operation the coolant pump begins
operating as soon as internal battery power is applied
4 ENVIRONMENTAL
to the stage. The methanol/water accumulator provides
a constant pressure at the pump inlet. As the coolant
circulates through the system it absorbs heat from the
cold plates, the ST-124 platform, LVDA and LVDC. The
absorbed heat is transferred to GSE equipment through
the preflight heat exchanger. The temperature sensor
(thermistor) senses the coolant temperature and transmits
a signal to the Electronic Control Assembly (ECA). The
ECA actuates the flow control valve so that part of the
coolant flow bypasses the heat exchanger. Through the
action of the sensor, ECA and the valve, coolant temperature
is maintained at 59 ± 1°F.
C. At liftoff Tl + 5.0 seconds the LVDC/LVDA commands
"Sensor Bias ON," driving the flow control valve to the
full sublimator flow position. At Tl + 75.0 seconds the
LVDC/LVDA commands "Cooling System Electronic Assembly
Power OFF" disabling the flow control valve electronics
leaving the flow control valve in the full sublimator
flow position for the remainder of the mission.
4-1
CONTROL SYSTEM
SLY AS-503
At T3 + 29.8 seconds, liftoff + 180 seconds, the LVDC/
LVDA program commands the water valve open allowing water
flow from the water accumulator to the sublimator. The
water absorbs the heat from the circulating methanol/water
coolant and the vapor from the sublimation iJ vented
overboard. The LVDC/LVDA "program control" of the water
valve is later enabled allowing the operation of the
thermal switches sensing the temperature of the coolant
to cause the temperature of the coolant to cause the LVDC/
LVDA program to cycle the water valve open or closed to
maintain proper environmental temperature of the IU and
upper S-IVB electrical components.
D. GN2
is utilized to pressurize the methanol/water accumulator
(15 psia) and the water accumulator (5 psia). GN2
pressure
within the methanol/water accumulator assures that the
coolant pump will not cavitate in the rarified atmosphere
of space. The water accumulator is pressurized with GN2 to insure that the water will flow from the accumulator
to the sublimator.
E. The ECS supplies conditioned GN2 to the gas bearings of
the ST-124 platform during preflight and inflight operations.
GN2
is supplied from a sphere through the pressure
regulator and flows to a heat exchanger where the GN2 is conditioned by the methanol/water coolant. The conditioned
GN2
then flows to the ST-124 platform gas bearings. A
reference pressure line routes gas bearing pressure from
the platform back to the pressure regulator. The reference
pressure causes the pressure regulator to increase its
output when the platform bearing pressure falls below rated
pressure and to decrease the output when the bearing pres
sure rises above the rated pressure. The gas bearings,
4-2
.::. , IJ1
3000
2500
2000
1500
1000
500
300
o
Acceptable liftoff pressures
Marginal liftoff pressures
Pressure eXpected for minimum usage
AS-503 GN
2 flowrate 0.066-0.079 Ib/hr
165 cubic inch sphere 7 smim-max leakage
+ 503 predicted
Average expected pressure
Pressure expected for maximum usage
Marginal usage pressure for normal 6.8 hr mission
1 2
Marginal usage pressure for 3:27 mission
Marginal regulator performance area
3 4 5 6
Figure 4-1.-TCS GN2
usage,
7
Note: XD25-601 measurement accuracy ±175 psia Measurement range o to 3500 pSia
8 9 10 l>c.n c.nr ,< IJ1 o I.>l
3000
~
'" '" '" ~ c.
./> a;
• c:: 2000 0-
~
0 ~
'" '" '" ~ N
;2
t!>
1000 mission
o o 1 2 3
Measurement off scale limit
Marginal area during flight
Average expected pressure
Note: XDI0-603 measurement accuracy ±1 75 psia Measurement range o to 3500 psia
Minimum usage pressure expected
. + 503 predicted
Maximum usage pressure for 6.8 hr mission
Marginal regulator performance area
4 5 6 7 8 9 10 1l
Time after liftoff (hours)
Figure 4-2 .-XDl 0-603 gas bearing GN2
usage.
»Vl Vlr .< U1 o
'"
~ 1
-...I
Electronic equipment
Heat transfer sheet
o 0 r----olC-o ---o I ______ ~-\;}_~-o 0
I C------------ ) o I ---------~ 0 0-
1 ,---- 0 ---, 1 ,--~ ___ o ________ J 0
I ------
r-- --0
1 '-..,;:._ 0 -=--=--0------)
1 ----- 0
I '-0------- 0 --0-) '- 0 ----
01 ----- -0-------IC---------~--O)O
0 0 --o-7---~ o 60
Coolant passage
Coolant passage
Honeycomb core
Figure 4-3.- S-IVB environmental control system.
Environmental control plates
IU supply
Electri cal! electronic modules
~
»Vl Ulr 1< \J1 o \)l
5.1
5.1.1
5.1. 3
SECTION 5 INSTRUMENTATION/COMMUNICATION SYSTEM
DIGITAL COMMAND SYSTEM
Purpose
SLV AS-503
The purpose of the Saturn instrument unit (IU) command system
is to provide a radio frequency/digital transmission link
from various Manned Space Flight Network (MSFN) stations to
the onboard Launch Vehicle Digital Computer (LVDC). This
input data will be used to update guidance information, to
command certain vehicle functions such as stage switch selec
tor operations, and to review data in certain locations of the
LVDC memory.
General
The command is transmitted in the S-band using a carrier
frequency of 2101.8 MHz. The command is FM modulated on a
70 kHz subcarrier, which in turn is PM modulated on the
2101.8 MHz carrier. The signal from the ground station is
received through the S-band transponder of the Saturn
command and communications system in the IU. The receiver
portion of the transponder separates the transmitted message
from the carrier and subcarrier and feeds the resulting
baseband signal to the IU command decoder where decoding is
accomplished. From the decoder, the data is sent through
the Launch Vehicle Data Adapter (LVDA) to the Launch Vehicle
Digital Computer (LVDC).
Modulation Techniques
The technique employed by the ground stations for base line
modulation is phase-shift keyed (PSK). A stable 1 kHz tone
'5 tNSTRut COMMUNICA TlON SYSTEM
is generated in the modulator and used as a phase synchronizing
signal. A coherent 2 kHz tone is biphase modulated so that
5-1
5.1.4
5.1. 5
SLY AS-503
the binary digits are phase analogous. The 2 kHz is modulated
at a 1 kHz rate. ~ binary one is being transmitted during
the 1 millisecond period when the 2 kHz tone is in phase with
the 1 kHz reference starting at the point where the 1 kHz
waveform is crossing zero and has a positive slope. The 1 kHz
tone and the phase modulated 2 kHz tone are algebraically
summed to produce the composite waveform. This composite
waveform is then modulated on a 70 kHz subcarrier which in
turn is PM modulated on the 2101.8 MHz carrier for transmission
to the vehicle.
MSFN Command Loads
It is planned that MCC will be responsible for origination
and transfer of all vehicle messages to the ground installations.
In normal operation this transfer is made by way of a high
speed data communication system. A 100 word-per-minute
teletype will serve as a backup for the HSD system. In
addition, data via communication satellite will be provided
for later missions.
Decoder Bit Coding and Timing
The first three bits of the word are called vehicle address
bits and are 111 for the IU command system on all Saturn
flights. The 14 decoder address bits are distributed throughout
the word. These bits are compared with a prewired address
in the decoder and are used to perform error checking.
The 18 information bits are used to convey binary data to
the LVDC. (All data for the LVDC are processed by the LVDA,
which is the input-output device for the LVDC.)
The LVDC data bits are divided into functional groups. The
first two bits are called "interrupt" bits and the next two
5-2
5.1. 6
SLY AS-503
are called "mode/data" bits. The remaining 14 bits are data
to the LVDC. The interrupt bits are always binary "ones" and
are combined in the LVDA to produce a single interrupt bit
from the LVDA to the LVDC. The mode/data bits are binary
"ones" or "zeros" depending on whether the particular command
message is a mode command word or a data word. The other
14 bits represents the binary coded data within the message,
and will be presented in the "true" and "complement" form.
Each of the 35 updata bits of the command word is encoded into
five sub-bits (total of 175 sub-bits per command word). Each
sub-bit is 1 millisecond in duration, which is exactly the
period of the 1 kHz waveform. Each updata bit, consequently,
is 5 milliseconds in duration because the system operates
NRZ with no dead time between sub-bits. Each sub-bit, as it
leaves the sub-bit demodulator, is 200 microseconds in
duration. The leading edge of this 200 microsecond waveform
is differentiated and used as the shift pulse for the five-bit
shift register. The bits are written into the register by
the differentiated trailing edge. The total time for a 35-bit
message transmission is 5 x 35 = 175 milliseconds since there
also is no dead time between updata bits. The updata bit rate
is, therefore, 200 bits per second. During the intervals when no
messages are being transmitted, all sub-bit "l's" are transmitted;
however, the comparators have no output.
Data Verification
The IU command system requires a high probability that a
correct command will be received by the vehicle. This high
probability is obtained by the use of several different
techniques.
5-3
SLY AS-503
A. To transpose a "1" bit to a "0" bit, everyone of the
five sub-bits must be complemented in multiples of five
in sync with the bit rate.
B. The 17 address bits must be correct or the message is
rej ected.
C. The 18 information bits must be present.
D. The LVDC checks and comparisons must be verified and a
computer reset pulse originated to signal the ground
station for transmission of the next command.
To complete the verification loop, the ground command system
must receive an indication of successful acceptance by the
LVDC within a specified time, depending upon processing and
loop delays or the command is considered to be rejected.
TM Data for Command System Analysis
Selected TM data from the onboard and from the ground system
is returned to MCC to assist in system performance predictions.
Sense points for the TM pickup of onboard data is shown in
figure 5.7 and figure 5.11. For ground generated data, points
of origin are shown in figure 5.6.
5-4
5.2 TELEMETRY SYSTEMS
SLY AS-503
A. Each stage of the launch vehicle has an independent
measuring and telemetry system with flight control
measurements on redundant lines between the IU and
S-IVB stages. Before launch, coaxial cables from each
stage telemetry system supply digital data to the
checkout facility. During flight, the telemetry data
is radiated from separate antenna systems on each
stage.
B. The Saturn vehicle contains the following telemetry
systems:
LINK MODULATION USE POWER OUTPUT
Iu/s-IVB composite PCM flow diagram (see Drawing No. 5.2.1)
IU (see Drawing No. 5.2.2)
DP-l PCM/FM
DF-l FM/FM DF-2 PAM/FM/FM DS-l SS/FM
DP-lA PCM/FM DP-IB CCS
Operational and Digital information
Engineering data Engineering data Vibration and
Structure data Parallel to DP-l Parallel to DP-l
S-IVB (see Drawing No. 5.2.3)
CP-l PCM/FM CS-l SS/FM
Engineering data Vibration and
Structure data
S-II (see Drawing No. 5.2.4)
BF-l BF-2 BF-3 BP-l
BS-l BS-2
PAM/FM/FM PAM/FM/FM PAM/FM/FM PCM/FM
SS/FM SS/FM
Engineering data Engineering data Engineering data Operational and
Digital information Engineering data Engineering data
5-5
255.1 MHz 250.7 MHz 245.3 MHz
259.7 MHz 2277.5 MHz 2282.5 MHz
20 W 20 W 20 W
20 W 20 W 20 'vI
258.5 MHz 20 W
253.8 MHz 20 W
241. 5 MHz 234.0 MHz 229.9 MHz
248.6 MHz 227.2 MHz 236.2 MHz
20 W 20 W 20 W
20 W 20 W 20 W
LINK MODULATION USE
S-IC (see Drawing No. 5.2.5)
AF-3 PAM/FM/FM Engineering data AF-2 PAM/FM/FM Engineering data AF-l PAM/FM/FM Engineering data AS-l SS/FM Engineering data AS-2 SS/FM Engineering data AP-l PCM/FM Operational and
Digital information
5-6
231. 9 MHz 252.4 MHz 240.2 MHz 235.0 MHz 256.2 MHz
244.3 MHz
POWER OUTPUT
20 W 20 W 20 W 20 W 20 W
20 W
SLY AS-503
4
-
3
2
-
1
o
IU
c
IU DIGITAL FLIGHT CONTROL DATA
{
DIRECT DIGITAL (G) CHANNEL (M)
DIGITAL MUX(2) 410J rAND
IU ANALOG FLIGHT CONTROL DATA
ENGINEERING DATA
410K
ANALOG MUX I------t
DPIAO
ANALOG MUX
CPIAO
B
PCM
ASSY
LTIli DR ~ ENGR I I I .1
VHF (225 1 MHZ)
UHF (2277 5 MHZ)
CCS TRANS PONDER (2282 5 MHZ)
A DATE I APPROVAL
~ ................................................................................................. . ~ ................................................................................................. . S-,IVB S-IVB ANALOG DATA II'
• S-IVB ANALOG DATA
S-IVB DIGITAL DATA
REMOTE ANALOG SUB-MUX
REMOTE DIGITAL SUB-MUX
ENGINEERING AND PROPULSION DATA
ANALOG MUX c
DPIBO
ANALOG MUX ~----~
CPIBO
BI-LEVEL DATA
PCM ASSY 1-----__ VHF
SIGNATURES DATE NATIONAL AERONAUTICS • SPACE ADMINISTRATION DR~,e~~ ¢,/c.p MANNEO SPACECRAFT CENTER • HOUSTON, TEXAS
DSGN 1!J."..J,.;;t:.£~ W"ft,...,
4
3
2
QC.6.uz.;" kh. ,M.·.' TELEMETRY COMPOSITE 1 ENGRM-u/A'ff.6w f·l.J.t.I S-IVBI IU PCM FLOW DIAGRAM APP ~ 1.J~ LL
FEC /f7Z. ~ Af:. AUTH.L_ lb-
MSC Form 1616 C (REV OCT GIS) • ~ SLV SlZE NO
~8-6B AS 503 C 22 X 17 PAGE ~-7
5.2. I lSHEET 1 OF 1
4
---
3
2
---
H
TRANSDUCERS
I VIBRATION I ACCELEROMETERS
l FORCE J ACCELEROMETERS
I FLOWMETERS I
l PRESSURE J TRANSDUCERS
I TEMPERATURE J SENSORS
SIGNAL CONDITIONING
MODUlER
I DC AMPLIFIERS I
i • • • • • •
•
I At AMPLIAERS I 1----------'1
l SERVO J ACCELEROMETERS
I FREQUENCY TO I DC CONVERTERS
1 I
• • • VARIOUS L • EQUIPMENT 1---.-.-to"! OUTPUTS I -
TO PCMlooJ ASSEMBl. v
~ L "EASURING \
VOLTAGE \ OT05VDC
DP~-OO
TRANSDUCERS AND SIGNAL CONDITIONING
•
I
MEASURING DISTRIBUTORS
G I F
CHANNEL A (9 MEAS) ..
CHANNEL B (13 MEAS)
i • • • • •
1 E
TELEMETER
• i • • • • • •
D
i ASSEMBLY F-l
~ 2~~~/~~~ ~-------------~i-------------------~------~ ii (8 MEAS)
I
r~~:::::-~1·~C[HA~N~N~E~L~C __ ~~(:'4~'~1~7~A:R:E~F:M~3):J CHANNELS C AND P • (S AND 25 MEAS) MULTIPLEXER
RF A$SV F-1
250.7 MHZ T APE ~~~~RDER r------
---1-=====-'-------------1 5-1 MOD 245 • CHANNEL P 1
l~(S~L~0:W~S:P:EE:0~)~-ii:~(2~5~M~EA~S~)------t_----~~~::~:_l TELEMETER
~~C~H~AN~N~E=L~N~(~2~M=E~AS~)~--------------------!~:~~========~~====~ ASSEMBLVS-l~ ____ -i i--------~--+-----~--------l CHANNEL 0 no MEAS) RF ASSV
'-----'
• TELEMETER $-1 CHANNEL E (S MEAS) .. ASSEMBLY F2
COAX SWITCHING
BOX
TM RF COUPLER
c
POWER DIVIDER
COAX TERMINATION
UMBILICAL PLATE
AUX OUTPUT
B I A LTR DR i ENGR DATE ..l.. APPROVAL
A """.,.-68 I I
B> PCM COAXIAL SWITCH SHOWN IN THE "FAIL SAFE" POSITION
~ 10 DATA LINES, 12 ADDRESS LINES AND DATA REQUEST
B:> 40 DATA LINES AND SYNC
~ THIS IS TAPE RECORDER CONTROL SIGNALS WHICH ARE V HANDLED THROUGH THE SWITCH SELECTOR AND CONTROL
DISTRIBUTOR
B> THESE ARE CALIBRATION COMMANDS, AND CAL LEVELS
I» THESE ARE CALIBRATION COMMANDS
2 ALL CHANNEL NUMBERS ON THE FACE OF THIS DRAWING, e 9 , CHANNEL A (9 MEAS1, REFER TO CHANNEL DESIGNATIONS ON THE SUMMARY CHART (SECOND COLUMN) AND REFLECT
4
I-~~~~~~~---------------------!.~ MODA-3 CHANNEL F 2-15 AND (27 MEAS) 1». X 3 CHANNEL G MUL T~~LEXER 3 (CAL CMDl • jFM
TYPICAL CODES USED BY THE INSTRUMENTATION PROGRAM r-AND COMPONENTS (lP AND C) DOCUMENT NO SOM10670
(SS MEA$) MOD 270 PAM WAVE TRAIN ! P2 (CSO)
RFASSV ~ F-2 -
CHANNEL 0 OR E -J29-602 NOTES
~~--41~+~---------=~---+--~+---------------~.-----PAM~VOC i 545.3 MHZ I-_--<~
YSWR MEAS ASSY
I IIU PCM XMTR \ I---f PWR OUTPUT--.J
o TO 30 WATTS DP1AO-14-03-00
I"'i'- THIS IS THE TELEMENTRY CALIBRATOR COMMAND SIGNAL t..:>' AND IS HANDLED THROUGH THE SWITCH SELECTOR AND
CONTROL DISTRIBUTOR
PCM DIRECTIONAL
ANT£NNA
TO S-IVB • PCM =
CHANNEL H (13 MEAS)
(CAL CMD)
TM
i • •
B> B> B>
CHANNEL H OR L
TELEMETRY CALIBRATOR ASSEMBLY
PI TRANSMITTER
RF
r--'--__ __
TELEMETRY RF TRANSMISSION COMPONENT
<:::::::::7
PCM COAXIAL SWITCH
~BEAM
(P ;ll ~ &BEAM
255.1 MHZ LOW GAIN
,---------------------~~g-----~~~~~t=~======~~~==lr==~~ -- B> I HIGH GAIN I .----....
KlS3-603 ) ~3 ~3 CHANNEL L (36 MEAS)
MULTIPLEXER MOD 270 PI <DAO)
• • • • • • •
NRZ
1-72 __ .8_P_S--1~~t--I TRAN~~TTER SYNC
....... ·L SYNC RF
2277 5 MHZ
CCS TRANSPONDER AND AMP INHIBIT
\ DOR28YDC7 J UHF I UHF SWlleH \
SWITCH OM .. 1 OIRE~TIONALHlGH GAjN O""'DIRECTIONAL \ 0 TO 28 vac \ 0 OR 28 VDC J ANTENNAS
CONTROL
LVDCjLYDA
REMOTE DIGITAL MULTIPLEXER ii
TO S-JVB 270 l PAM
~
CHANNEL J (75 MEAS)
SYNC
MOD 410 CHANNEL J CHANNEL M
~ __ ~U~) ____ ~----if~----~ CHANNEL K
~6 r;;'~~~~1-__ ~~ ____ 4-__ +-~(l~M~E~A~S~) __ ~ ~ REMOTE DIGITAL ~ MULTIPLEXER
MOD 410 (K)
PAM SYNC
DIGITAL) DATA
~~¢ik~~~:~~~: 14 ____ -'P_A_RA-'L"L_E_L_O_AT_A _________ ~------------------3.4 KHZ AND 4PP$ SYNC.
UMBILICAL
PCMjDDAS MOD 301 CPU
: I I I I I I I I
• •
• • • • • •
(VOL TAGE .... _______ ...J COMMAND VERIFICATION ....i CONT OSC)
COMMAND DECODER • • • • •
DPIAO-17JOS-64 SWITCH
~ LVDC/LVDA ---.. SELECTOR 0"~-U1 D"~-O:f '\[7
CCS
~T~R~AN~S~PO~N~DrE~~R~~~~~~rl_NH_IB_I_T~~ ____ -. ____________ --"J HYBRID RING
-
~ ( AYP 1 \
OOR5vac J DP1AO-16GOO-01
Y
~ J AYP2 \
\ DOR5YOG} DP~-02
AUDIO
TRANSMIT SECTION
RECEIVE SECTION
~
KlSD-603
CCS TRANSPONDER AND LAMP PWRON I~ \.0 OR 28 VOCJ o 1AO-17J05-03
0::::::::::::;>
DOWNLINK 2282.5 MHZ
JA
RF ecs POWER AMPLIFIER
UPLINK 2101.8 MHZ
RF
~ II ~ (~~70~t~;~c~~C~0~~\-It-__ --" L----It--~1E'C~AR~R~~~~S~L~O~CK~\ \ 0 OR 5 YOC I \ "OR 5 YOC I DP1~-06 DP1~-05
-
Ki31-603 I I CCS
CONTROL H SWITCH OMNl 11-': \0"'0;';R:':2"'8C,y7.:OC=J-i
CCS COAXIAL SWITCH
"~~9
~3
·ccs DIRECTIONAL
ANTENNAS
(V ~ BEAll ~;> ~ & BEAll
HIGH GAIN
LOW GAIN
I CCS SWITCH \ CCS RECEIVING
DtRECTIONAl lOW GAIN ~ ]lAN.TENN ,\A 17 \OOR2BVIlC I DP1AO-17J06~10 ~
~---~------~------------o-J_ CCS
POWER DIVIDER
SIGNATURES DATE NATIONAL AERONAUTICS & SPACE ADMINISTRATION
DR ~ ~ ~ 1»>.JrfJ MANNED SPACECRAFT CENTER HOUSTON, TEXAS
OSG' &..£.."-.ef~ ~"" QC .<9JZ;; A .... R-/.<.(
3
2
M~LTIPLEXING AND DISTRIBUTION TELEMETRY TAPE RECORDER AND RF ASSEMBLIES ENGR ,,/~l- r",q
INSTRUMENTATION TELEMETRY SYSTEM,IU
i • APP r: It.. FEC AUTo' 1:)'; fh"..
u
SLY 5.2.2 AS503
34 X 22 PAGE 5-8 SHEET 1 OF 1
ANTENNA 1 ANTENNA 2
'\ 17 '\17 TELEMETRY
·1 l U .. POWER DIVIDER .............
IlL
COAXIAL -~
DUMMY SWITCH LOAb
t RF MULTIPLEXER
-. ,~ • TRANSMITTED
BI -DIRECTIONAL FORWARD B I -DIRECTIONAL REFLECTED POWER - . POWER - COUPLER
l"uwt:.K ... COUPLER . DETECTOR DETECTOR DETECTOR
~ .. FM/FM RF ASSY
TRANSMITTER' MO'O-II CCS TRANSPONDER PCM/FM
~
TELEMETRY SYNC SYNC PCM/DDAS ASSY
OS-CIU:.ATOR DATA MODEL 301 DATA ASSY . -... ...
+ j Il •
I Ir • , ANALOG
TELEMETRY TIATA CP1BO REMOTE DIGITAL CP1AO
CALIBRATOR MUL TI PLEXER SUB-=MULTI PLEXER MUL TIPLEXER
MODEL 270 r10DEL 270 I
I • TO SSB I
BI-LEkL DATA IU:
ANALOG DATA
Instrumentation - S-IVB Telemetry System
I
I
!
I
PCM/DDAS ASSY
'I' SYNC Ir DATA
DP1BO MUL TIPLEXER MODEL -270
j
SYNC DATA if
REMOTE ANALOG SUB-MUL tIPLEXER
LOW!EVEL ANALOGDATA
..
BI-DIRECTIONAL COUPLER
h
SINGLE STDEBAND
TRANSMITTER
,
SINGLE
I son¥i-8~-NRMP 'Il
.
SLV AS-503N
TRANSMITTED POWER
DETECTOR'
FROM CALiBRATOR
SINGLE SIDEBAND ~ TRANSLATOR
AIRBORNE
t VIBRATION
MUL TIPLEXER MODEL 245
!
-.... VIBRATOR
DATA
DRAWING 5.2.3 5-9
4
3
2
1
D c B A
'\ 7 '\ 7 \
I I I I I '\ 7 '\ 7 TO AUXILIARY TO I
RECEPTACLE + + UMBILICAL I
LTR APPROVAL DATE
l " ew. "'""" ~,,,"::.,,"~ ""'. "'''"'' COAX SWITCH COAX SWITCH
!
I I HYBRID JUNCTION MODE 600 KC DDAS DISCRETE
CONTROL OUTPUT TO ESE DATA
1-3 I RF MUL TlCOUPLER I RF MUL TICOUPLER J l RESISTOR ASSY
LINK S2 LINK SI LINK F3 LINK Fl LINK F2 1 LINK PI t t (236.2 MHZ) (227.2 MHZ) (229 9 MHZ) (241.5 MHZ) (2340 MHZ) (248.6 MHZ)
I FM RF ASSEMBLY I t FM RF ASSEMBLY J FM RF ASSEMBLY I I FM RF ASSEMBLY J I FM RF ASSEMBLY J PCM RF ASSY PCMjDDAS ASSEMBLY J MODEL 1 MODEL 1 MODEL 1 MODEL 1 MODEL 1 MODEL CT -198 MODEL 301
~ t t t t GROUND MOD 270 MUX RDSM RDSM CONTROL <STR) MOD 10 MOD ID
GROUND ~ 1 CONTROL
J t JJ TO EACH
JA
GR1ND
RF ASSY CONTROL r-. TAPE RECORDER TAPE RECORDER RELAY
NO 2 MOD 101 NO 1 MOD 101 RESISTOR RESISTOR ASSEMBLY ~ ASSY ASSY
, : CONTROL r .I., r .I., r.l, }-1 tc~j I 1 I 12 I 131 TIMERS
LTJ LTJ LTJ
.L -L -L DISCRETE CALIB RE'LAY DATA DATA AMPLIFIER ASSY ASSEMBLY AMPLIFIER ASSY
• ~ ; I I 1 i 1 I
CONVERTER TM SINGLE TOA ASSEMBLY
I MOD 270 TOA ASSE MBL Y MOD 270 TOA ASSEMBLY : MOD 270 MOD 270 ASSEMBLY - CALIBRATOR SIDEBAND
MODEL Al I MUX A3 MODEL A2 MUX A2 MODEL Al I MUX Al MUX (60) DC-DC MODEL 11 ASSY MOD 601 I
CAL i SSB JA DATA t • '1 DATA DATA t DATA t J DATA t 1 ~ . t DATA
DlA SINGLE
SIDEBAND SCO'S AND 270 MUX'S BF3-L2 l BF3-Ll J l BFl-Ll J l BFI-L2 I BFI-Ll ASSY MOD 601 l MOD 245 MUX RASM MOD 102 RASM MOD 102 RASM MOD 102 RASM MOD 102 RASM MOD 102
DATA t J 1 DATA t DATA t DATA t DATA t DATA
PATCH PANEL 1 BFI-Ll 1 RASM MOD 102
1 BPI-HI .1 RASM MOD 101
1----1 t DATA t DATA
DATA
SIGNATURES DATE NATIONAL AERONAUTICS & SPACE ADMINISTRATION t-:::DR;:--::.¢:;;~~:-:;~=a:;'t!::":-<--1-:~;-:/,,=,,,,::I MANNED SPACECRAFT CENTER
•
HOUSTON, TEXAS
S-II TELEMETRY SYSTEM -BLOCK DIAGRAM
SLV SIZE DWG NO.
AS'503C 5.2.4 22 X 17 PAGE 5-10 SHEET 1 OF 1
4
3
2
1
0 I c • B ! A LTRI DR I ENGR I DATE I APPROVAL
TO UMBILICAL i i 1 i i ANTENNAS
ANTENNAS
\[7 \[7 \V '\V 4 l RF POWER DIVIDER NO 1 L RF TERMINATION J RF POWER DIVIDER NO 2 J 4
j,"M""~'" Q I I Q COM'" ,~,~l + I
TO AUXILIARY RECEPTACLE
LINK Fl (240.2 MHZ) J }-- LINK F3 LINK PI (244.3 MHZ) I r- LINK S2 RF MULTICOUPLER NO 1 RF MULTICOUPLER NO 2 (256.2 MHZ)
I (231.9 MHZ) I LINK F2 LINK SI
- (252.4 MHZ) (235.0 MHZ) -
VSWR VSWR VSWR VSWR VSWR VSWR MONITOR MONITOR MONITOR MONITOR MONITOR MONITOR
POWER AND CONTROL
1 RF ASSEMBLY
TAPE RECORDER RF ASSEMBLY RF ASSEMBLY RF ASSEMBLY RF ASSEMBLY RF ASSEMBLY
3 Fl F2 F3 PI SI S2 3
t J t ~ • a> a> [9 ~ PC M/DDAS 1 1
D>l ASSEMBLY SS/FM SS/FM -t -t PI TELEMETRY TELEMETRY
~ ASSEMBLY ASSEMBLY SI S2
PAM/FM r-- SYNC PAM/FM
~SYNC PAM/FM
j.-SYNC l + SYNC AC dAL AND
f AC C!L AND • ASSEMBLY ASSEMBLY ASSEMBLY • F1 F2 F3
DATA
\1A
, DJA~ • OAt· i CONTROL CONTROL
CALIBRATION SIGNAL AND CONTROL
DIGITAL REMOTE 01 GlTAL DATA MODEL 245 MODEL 245
SUBMULTIPLEXER MUL TlPLEXER MUL TlPLEXER
I-- PI Sl S2 2 PREFLIGHT / INFLIGHT CDNT f f
DJA
2 SYNC
CAL COMMAND TM CALIBRATOR TO PAM ASSEMBLY MULTIPLEXER DIGITAL DATA
5V REF A1,A2,ANQA3 DATA
ISOLATED r-20V PWR DISCONNECT MODEL 270 G "~'''~H''''''," PANEL MUL TIPLEXER SYNC BUFFER LEVEL MEASURING
TRANS POSER , I-- DATA PI UNIT SYSTEM D> FOR INFORMATION ONLY + f NOTES AUXILIARY OUTPUT - FOR TM CHECKOUT r--
~
1£ CAL AND CONTROL DATA • MIlL TlPLEXED FLOW RATE DATA CAL CONTROL RELAYS DC POWER MEASURING ISOLATOR DISTRIBUTORS -
DJA
SIGNATURES DATE NATIONAL AERONAUTICS & SPACE ADMINISTRATION
DR&«.t~ ~ 11-22·68 MANNED SPACECRAFT CENTER HOUSTON, TEXAS
DSGN~-tI'~ ~';-1""8
QC 4.<Z. t1}, ~ j'/';-"I' S-IC TELEMETRY 1 1 ENGR 177.-.1 ,f a:w 1'.~.·lr
SYSTEM-BLOCK DIAGRAM APpa, It,,.,~.-'. f'-~~-IJ.
FEC /WfR~ ~/d SLV SIZE DWG NO
AUTHJ:J-l~ .£:Y-'6 AS-503 C 5.2.5 ~ I 22 X 17 PAGE 5-11 iSHEET 1 OF 1
MSC Form 111118 C (REV OCT .5) • I
0 1 c • B A
I TIll DR I ENGR I DATE I APPROVAL
I I I I I
ANTENNA MOD 713 SINGLE PULSE REPLY
INHIBIT NO ~ \ V ONLY IF CORRECT
\[7 ~ INTERROGATION CODE
t ANTENNA MOD 711 4 4 IS USED
TIM MEASURING INPUT PRF-TIM C-BAND
RFSIGNAL ~ RF TRANSPONDER NO 1 RACK • f INPUT SIG LEVEL-TIM
st GROUND RADAR
DOUBLE PULSE STATIONS INTERROGATION (AN/FPS-16 AND
+ 28 VDC AN/FPQ-6) PROVIDE AZUSA TRANSPONDER
WORLD-WIDE TYPE C
COVERAGE FOR RANGE ELEVATION INHIBIT NO 1
AUXILIARY POWER AND AZIMUTH r---- -DISTRIBUTOR DATA POWER KLYSTRON KLYSTRON HT KLYSTRON AUTOMATIC +28 VDC BEAM SK TEMP POWER GAIN CONTROL
VOLTAGE SAMPLE SAMPLE
+28 VDC ANTENNA MOD 713
\[7 C-BAND TRANSPONDER CONTROL
NO 1 NO 2 NO 1 AND 2
3 C-BAND INHIBIT INHIBIT ON AZUSA RI FILTER ASSEMBLY 3 CONTROL
TRANSPONDER NO 2 SS 144 SS 124 SS 164 DIS TRIBUTOR RF SIGNAL CHAN 55 CHAN 56 CHAN 54
- - SW SEL - - 603A17J3- r
t ~~ ~ ~,
f-
+28 VDC KLYSTRON HT KLYSTRON AUTOMATIC BEAM SK TEMP POWER GAIN VOLTAGE
SAMPLE CONTROL -. INHIBIT NO 2 • INPUT PRF-T 1M
TIM MEASURING INPUT SIG LEVEL-TIM
RACK INHIBIT NO 2
C-BAND SYSl£M AUXILIARY POWER TIM MEASURING DIS TRIBUTOR RACK
2 2 1 TRACKING STATIONS LOCATED AT
CAPE KENNEDY AND GRAND BAHAMA PROVIDE REAL TIME COVERAGE FOR INITIAL BOOST PHASE OF FLIGHT
2. AZUSA TRACKING INFORMATION IS PROCESSED TO PROVIDE IMPACT PREDICTION DATA TO THE RANGE SAFETY CONTROL OFFICER
- AZUSA SYSTEM r---
. SIGNATURES DATE NATIONAL AERONAUTICS & SPACE ADMINISTRATION
DR '}(_.,.id4'C /}'(~ tI!:!f§" MANNEO SPACECRAFT CENTER . HOUSTON. TEXAS
DSGN~£~~ ~/I?bS INSTRUMENTATION QC~...::b;"" 5'·/?-,:t
1 ENGR ..!!l....a-xu/ 1" ~ T'~ TRACKING SYSTEM 1
APP Je..~ ?-J.J .• SIGNAL FLOW FEC ~.~.i ~ SLY SIZE DWG NO
AUTH..&....L~ f::.'?-1,8
AS503 C 5.2.6 ,
22 X 17 PAGE 5~2 .lSHEET 1 OF 1
MSC Form 1616 C (REV OCT 65) •
,_.rr
90· II I '
ANTENNA LOCATIONS (AFT LOOKI~~ ,aRWARD)
FOR REFERENCE ONLY, NOT TO SCALE o·
TM AFI, ~FIN D AF3
ASI, AS2
Antenna Locations Aft Looking Forward (For Reference Only - Not to Scale)
<"' ·f. ~ :... . t;S~ 5.)3',
FIGURE 5.1 ~-13
5.3 DESCRIPTION OF THE S-IVB TAPE RECORDER
SLY AS-503
There is no tape recorder in the S-IVB stage.
5-14
*
MEASUREMENT
JEi9-Ei03
J70-Ei03
J71-Ei03
J72-Ei03
J7Ei-Ei03
J77-Ei03
J78-Ei03
FUNCTION
ADDRESS VERIFICATION PULSE PRESENCE/ABSENCE OF ONBOARD DECODER RESPONSE TO UPLINK COM'1MlD
COMPUTER RESET PULSE. PRESSURE/ABSENCE OF LVDC RESPONSE TO UPLINK COMMAND
CCS AGC
ON/OFF STATUS OF PRIME UP DATA CARRIER (2101.8 M-iz)
ON/OFF STATUS OF UPLINK COMMAND SUBCARRIER
SLY AS-503
INFORMATION OBTAINED
THE PRESENCE OR ABSENCE OF THEAVP IS REQUIRED TO DETERMINE IF THE COMMAND WAS ACCEPTED OR REJECTED BY THE ONBOARD DECODER.
THE PRESENCE OR ABSENCE OF THE CRP IS REQUIRED BY THE GROUND COMPUTER TO DETERMINE VALIDITY OF COMMAND LOADS. IF THE CRP IS ABSENT THE UPLINK WILL BE REPEATED.
THE LOCK/NO LOCK STATUS OF THE PRIME CARRIER IS USED TO DETERMINE THAT THE UPDATA LINK IS VALID (VEHICLE IN RANGE AND CAPABLE OF RECEIVING COMMANDS.
LOCK/NO LOCK STATUS OF 70 kHz SUBCARRIER. THE 70 kHz SUBCARRIER MUST BE IN LOCK PRIOR TO INITIATING A COMMAND. IF THE PRIME CARRIER OR THE SUBCARRIER IS NOT IN LOCK SIC REJECT WILL RESULT FROM AN ATTEMPTED UPLINK.
Figure 5-2.- Command TM data summary.
5-15
U1 1 ..... 0'
/'
Interrupt A
Interrupt BDecoder address-
~Decoder address
~Decoder address
VeII'.le add":'] !, J 1. J ! DeCod ... ddrOSSJ , Decod. ad~eSSl ,
111 101 I pOll Fixed bits Ix X Xl1 ° 1
35 bit command 11231456 word
718 9 1101I.*2~31.51617181192021 11 110111
2324k~26272829301313233343S
Variable bits 14 7J 11~1312
t t Information-
Mode/data-
Bit 1 transmitted first Bit 35 transmitted last
-T-I....-Information
1..... Mode/data
1110 9 8 7 6, 5 4 3 2 1
'" L Information ~Infonn.tion
Figure 5.3. - Command word format. >(1) (I), 1<
U1 o U)
"""""II
\J'I I
...... '-I
1 kc ref
2K modulation
Composite output
r l kc----1
r--Binary "1" t I- Binary "I" + Binary "0" t I- Binary "0" t I- Binary "1"
Figure 5.4 0 - PSK waveforms o. :>U'l U'lr 1<
\J'I o VJ
*
1
3
11
12
ITEM FLNCTION
UDL SUBC ON/OFF STATUS OF UPLINK 70 kHz COMMAND/BACKUP VOICE
SUBCARRIER
PRN UPLINK ON/OFF STATUS OF UPLINK MODULATION OF THE BASE-BAND.
PCM SUBC LOCK/NO LOCK STATUS OF LOCK (PM) PM DOWNLINK PCM SUB-1.024 kHz CARRIER DEMODULATOR.
PCM SUBC LOCK/NO LOCK STATUS OF LOCK (PM) FM DOWNLINK PCM SUB-
CARRIER DEMODULATOR.
SLV AS-503
INFORMATION OBTAINED
THE STATUS OF THE 70 kHz SUBCARRIER MUST BE KNOWN PRIOR TO INITIATING A COM-MAND OR UTILIZING IT FOR BACKUP VO I CEo
THE PRESENCE (ON)/ABSENCE (OFF) OF MODULATION ON THE UPLINK BASEBAND WILL REFLECT THE PRESENCE OF THE TRANS-MITTED PRN RANGING CODE. THE INFORMATION IS REQUIRED TO DETERMINE IF PROBLEMS ENCOUNTERED ARE ASSOCIATED WITH THE SIC OR THE GROUND SYSTEMS •
THE STATUS OF THE PM DOWN-LINK PCM SUBCARRIER DEMODU-LATOR IS REQUIRED IN ORDER TO DETERMINE QUALITY OF THE DOWNLINK DATA DUE TO MARGINAL LOOK ANGLES, CIRCUIT MARGINS AND TO FACILITATE SIC HANDOVER.
THE LOCK/NO LOCK STATUS OF THE FM PCM DOWNLINK SUB-CARRIER DEMODULATOR IS REQUIRED TO DETERMINE QUALITY OF DOWNLINK DATA.
Figure 5-5.- Ground generated events for command evaluation.
5-18
VI I ....
o,l)
70 KHz
Carrier generator
30 KHz
~
\ / 1
3 Modulator -
2
,~
\ /
Pre amp
4 ~ 5
Range PM Range code J
station receiver
Tape ~ recorder
9 Voice
~ demod ulator ,
Telemetry receiver
11 J PCM demodulator
13 j
Ground station
l : 642 B
Figure 5.6.- Schematic of ground generated events.
J FM
receiver
~
Telemetry receiver
L -"
6
7
8
TV demodulator
Tape recorder
Voice demodulator I
PCM demodulator I
10
12
»(J) (J)r J,< o VJ
'" . N o
Duplexer
TM xmitter (in lUI
CCS S-~nd xponder r--- ----------, I I
Xmittcr
ReIII' 70 KHz
FM demod
I I I I I I I I I I
I I ---.I
* ,-----, PCM DDAS
IU command decoder
TM xmitter
(in S-iVB)
*1 r _--JL-_,
Remote digital
multiplexer
LVDA
Vehicle system (lUI
LVDC
--------------------------------------~--------- .... -----------
Note: Heavy lines indicate components of the IU command system
*PCM DDAS references IU or NB. The NB multiplexer is an analogue MUX
S-band xmlr
2101.8 MHZ
70 KHz subcarrier
rcVl'
Ground station
computer ~
(CMDI
Figure 5.7.- S-V IU command system.
Ground station, MSFN
10-bit fonnat
PCM DO AS decom
(TM)
TM revrs
Ground ITo flight control station
computer
From night control
»VI VIr-J,< o
'"
'" , N ,..
o Sub-bits being received from
PSK sub-bit detector
• 5-bit counter inhibited • "1" & nOli comparators
inhibited
Shift and write into 5-bit shift register
• Reset 3-bit counter • Add 1 to 3-bit counter • Start missil1!l-bit clock
(5.4msl • Remove 5-bit counter
inhibit (and 1)
.Shift & write 5-bits into shift register
.5-bit counter counts to 5
No
c
B
) NO • I. Missing-bit clock stops • 3-bit counter reset
• Add 1 to 3-bit counter • Keep clock running
anoth er 5 Am s
NO c
• Reset 32 bit cOlJ:lter > 2 I I. Clear 32 bit shi ft reg ister • Remove data from 18
output lines
Figure 5.8:- Flow diagram - main decoder (part 1).
>'" "'r-J,< o
'"
'(' N N
• Add 1 to 3-bit counter <counter resets)
• Missing-bit clock stops
IIXII
• Shih and write into 5-bit shift register
• 5-bit counter counts to 5
• Shift and write one bit into 32-bit shift register
• Add 1 to 32-bit counter
Ves
• Missing bit clock stops • 3-bit counter resets
Add 1 to 3-bit counter (counter resets)
Missing -bit clock stops 3-bit counter resets
Figure 5.9.- Flow diagram main decoder (part ill.
• Present 18 bits of data to LVDA
• Send redundant address veri fitalian to telemetry (bOms)
• Reset 3-bit counter • Inhibit "1" & "011 comparators
• Send redundant reset signals to telemetry (bOms)
• Clear 32-bit shift register • Remove data from output lines
Missing-bit clock stops
No
lo'" "',... ,< Uo o
'"
'i' '" '"
5 lines from 5-bit shift register
Slines from S-bit shift register
"1" write
To comparators
5-bit shUt r~ister
"X" counter
5-bit S
Reset
--..., J: I . L.. Recognize
O.l.orX "L-__ S
--------------i r-- ---- I '"'''.''' ~: I :~. 'I'w .': '~ SAm, J .1 I S I I I
I I I I ____________ ...J
---r j j ~ '------L-------:-Address comparator (compare) _. -----'
Shift and write
Figure 5.10.- Block diagram main decoder (part D.
Reset shift reg and 32 bit ctr
>v> v>r ~<
'"
~
i!
From comparator
"all "I"
JL... 200 ~S
Address comparator
14 lines from 32-bit shift register
Ims
14 lines to 14-bit address comparator JL...
r---------_____________________ A~ __________________________ __
( 32-blt shift
Output gates and drivers ------------ ltypical18 placesl ---------
Count
18 bits
Figure 5.11. - Block diagram main decoder (part 11 I.
To reset From X bit "X" bit CTR CTR equal 2
Ims JL...
Up until LVDC reset CRP or 2X bits
Shift register
Clear
Gate enable
Counter reset
14 info bits
SLY AS-503
VI I
N VI
last sub-bit <l75th) out ---
of uplink equipment 0 20 40 60 80 100 120 140
I I
Ie (delay)
Jt gated to l VDA H I
PCM ~ I . . • • :-I I • •
~ Min ing
1 Max -f -.
Min ~ . • . . . ;L
PCM I f----I .-- --- ---Max
I I • I I I • • • • i I
I I
Min ~. •
) IU PCM I Max . r II
I • J I
* . --_. --_. _ ....... . ! fa AVP, J CRP or DCS EW Note: Time in mi IIi seconds * Increase propagation delay 1 MIS per 300 km increase in slant range
Figure 5.12.- On board processing timeline.
* SECTION 6
GUIDANCE AND NAVIGATION SYSTEM
SLY AS-503
6.1 BOOST PHASE GUIDANCE
A. During boost, the S-IC will be programed to. initiate a
roll maneuver to properly align the vehicle with the
flight azimuth. This maneuver is controlled by the LVDC
and begins at Ii ftoff + 12 seconds.
The roll maneuver is required to align S-IC location 1
(at LC39A, location 1 is aligned to 90°) to the flight
azimuth of 72°.
B. A pitch maneuver is also programed during S-IC boost
beginning at liftoff + 12 seconds. The pitch maneuver is
preprogramed in the LVDC and pitch angle is determined as
a function of time. When pitch attitude reaches the
required value, that attitude is held until approximately
40 secorids after S-II ignition.
C. Active guidance of the vehicle begins at about S-11
ignition + 40 seconds. The guidance system during S-II
powered flight will position the vehicle to a specified
velocity, flightpath angle and altitude. When these
conditions are satisfied, the guidance program is frozen
for staging and the S-II is cut off.
D. The attitude hold then continues until about 10 seconds
after J-2 ignition. The second active guidance period
directs the S-IVB/1U to the proper altitude, velocity
and attitude for the AS-503 mission orbit insertion
conditions.
E. LVDC/LVDA Operational Parameters
Meas No. H60-603, Channel No. DPlAO - 8KOO, 9KOO, lOKOO,
llKOO, and DPlAO - 23KOO, 24KOO,
25KOO, 26KOO
6-1
6 GUIDANCE AND NAVIGA TlON SYSTEM
TABLE 6-1.- LVDC TELEMETRY NOMENCLATURE, TAGS AND SCALING SLV AS-503
NAME MCC ABBR HOSC ABBR PIO MCC PCM HOSC PCM MCC SCALING HOSC SCALING --TIME SINCE GRR TAS TASEC 000 2000 0400 DATA BIT 11 = 1 SEC SIGN +15
X- COMPONENT OF SPACE-FIXED POSITION XS xs 044 2110 0422 DATA BIT 3 = 1 M SIGN +23
DATA BIT 3 = 16 M* SIGN +27
Y-COMPONENT OF YS YS 050 2120 0424 DATA BIT 3 = 1 M SIGN +23 SPACE-FIXED POSITION DATA BIT 3 = 16 M* SIGN +27
Z-COMPONENT OF ZS ZS 034 2070 0416 DATA BIT 3 = 1 M SIGN +23 SPACE-FIXED POSITION DATA BIT 3 = 16 M* SIGN +27
X-COMPONENT OF XDS XDS n4 2230 0446 DATA BIT 12 = 1 Mis SIGN +14 SPACE-FIXED VELOCITY
0\ Y-COMPONENT OF YDS YDS 120 2240 0450 DATA BIT 12 = 1 Mis SIGN +14 I SPACE-FIXED VELOCITY rI)
Z-COMPONENT OF ZDS ZDS no 2220 0444 DATA BIT 12 = 1 MiS SIGN +14 SPACE-FIXED VELOCITY
TOTAL SPACE-FIXED VELOCITY VS V 124 2250 0452 DATA BIT 12 = 1 MiS SIGN +14
TIME IN TIME BASE TBX TB 031 6060 1414 DATA BIT 11 = 1 SEC SIGN +15
TIME IN TIME BASE UPDATED TBXU TBB 030 2060 0414 DATA BIT 11 =1 SEC SIGN +15
TIME-TO-GO S-IVB CUTOFF TTG IGTSTR 460 2540 0530 DATA BIT 16 = 1 SEC SIGN +10
YAW GUIDANCE ANGLE XZ CHIZ 001 6000 1400 DATA BIT 26 = 180 DEG SIGN +0
ROLL GUIDANCE ANGLE XX CHIX 005 6010 1402 DATA BIT 26 = 180 DEG SIGN +0
PITCH GUIDANCE ANGLE XY CHIY 011 6020 1404 DATA BIT 26 = 180 DEG SIGN +0
SLY TABLE 6-I.- LVDC TELEMEI'RY NOMENCLATURE, TAGS AND SCALING - Continued AS-503
NAME MCC ABBR HOSC ABBR PIO MCC PCM HOSC PCM MCC SCALING HOSC SCALING
X-TOTAL ACTUAL ex TLTHTX 021 6040 1410 DATA BIT 26 = 180 DEG SIGN +0 GIMBAL ANGLE
Y-TOTAL ACTUAL ey TLTHTY 025 6050 1412 DATA BIT 26 = 180 DEG SIGN +0 GIMBAL ANGLE
Z-TOTAL ACTUAL ez TLTHTZ 015 6030 1406 DATA BIT 26 = 180 DEG SIGN +0 GIMBAL ANGLE
TIME OF TIME BASE TBXI TI 561 6740 1570 DATA BIT 11 = 1 SEC SIGN +15 INITIATE
TIME TO GO TO TLQl TTGO 101 6200 1440 DATA BIT 26 = 1.000 SIGN +0 RESTART PREP
0\ SECOND AND FOURTH TTG T2I IGT2I 171 6360 1474 DATA BIT 16 = 1 SEC SIGN +10 I w
DEVIATION IN S-IVB llT4 DT4 104 2210 0442 DATA BIT 18 = 1 SEC SIGN +8 CUTOFF TIME
GUIDANCE MODE WORD 1 GMW1 MC25 421 6440 1510 N/A
GUIDANCE MODE WORD 2 GMW2 MC26 401 6400 1500 N/A
GUIDANCE STATUS WORD GSW MC24 415 6430 1506 N/A
ORBITAL STATUS WORD OSW MC28 414 2430 0506 N/A
ORBITAL MODE WORD OMW MC27 420 2440 0510 N/A
ERROR MONITOR REGISTER EMR EMRR 435 6470 1516 N/A
SLY TABLE 6-I.- LVDC TELEMErRY NOMENCLATURE, TAGS AND SCALING - Continued AS-503
NAME MCC ABBR HOSC ABBR PIO MCC PCM HOSC PCM MCC SCALING
SECTOR DUMP HEADER WORD SDHW N/A 470 2561 0535 N/A
WORD 1 474 2571 0537
WORD 2 500 2601 0541
WORD 3 504 2611 0543
WORD 4 510 2621 0545
WORD 5 514 2631 0547
WORD 6 520 2641 0551
0\ WORD 7 524 2651 0553
I
"" WORD 8 530 2661 0555
WORD 9 534 2671 0557
WORD 10 540 2701 0561
WORD 11 544 2711 0563
WORD 12 550 2721 0565
WORD 13 554 2731 0567
WORD 14 560 2741 0571
WORD 15 564 2751 0573
WORD 16 570 2761 0575
SLY TABLE 6-1.- LVDC TELEMEl'RY NOMENCLATURE, TAGS AND SCALING - Continued AS-503
MEMORY LOCATION NAV UPDATE QUANTITY MCC ABBR HOSC ABBR MODULE SECTOR ADDRESS MCC SCALING HOSC SCALING
Z-COMPONENT OF ZDNU ZDS 4 15 371 DATA BIT 12 = 1 MIS SIGN +14, Mis SPACE-FIXED VELOCITY
X-COMPONENT OF XDNU XDS 4 15 372 DATA BIT 12 = 1 MIS SIGN +14, Mis SPACE-FIXED VELOCITY
Y-COMPONENT OF YDNU YDS 4 15 373 DATA BIT 12 = 1 MIS SIGN +14, Mis SPACE-FIXED VELOCITY
Z-COMPONENT OF ZNU ZS 4 15 374 DATA BIT 3 = 1 M SIGN +23, M SPACE-FIXED POSITION DATA BIT 3 = 16 M* SIGN +27, M
X-COMPONENT OF XNU XS 4 15 375 DATA BIT 3 = 1 M SIGN +23, M SPACE-FIXED POSITION DATA BIT 3 = 16 M* SIGN +27, M
0\ Y-COMPONENT OF YNU YS 4 15 376 DATA BIT 3 = 1 M SIGN +23, M J SPACE-FIXED POSITION DATA BIT 3 = 16 M* SIGN +27, M 0\
TIME OF NAV UPDATE TNU NUPTIM 4 15 377 DATA BIT 11 = 1 S SIGN +15, S
III.
TABLE 6-I.- LVDC TELEMETRY NOMENCLATURE, TAGS AND SCALING - Continued SLY AS-503
MEMORY LOCATION ORBIT TARGET UPDATE QUANTITY MCC ABBR HOSC ABBR MODULE SECTOR ADDRESS MCC SCALING HOSC SCALING
INCLINATION OF i INC 4 14 371 DATA BIT 25 SIGN +0, DEG TARGET PLANE = 90 DEG = .5 PIRAD
DESCENDING NODE OF eN THN 4 14 372 DATA BIT 25 SIGN +0, DEG TARGET PLANE = 90 DEG = .5 PIRAD
ECCENTRICITY OF eN ECC 4 14 373 DATA BIT 26 = 1 SIGN +0, DEG TRANSFER ELLIPSE (NO UNITS)
ENERGY OF C3 C3 4 14 374 DATA BIT 5 SIGN +21, ~/S2 TRANSFER ELLIPSE = 1 M2/S2
TRUE ANOMALY OF "'D ALPHAD 4 14 375 DATA BIT 25 SIGN +0, DEG
0'\ DESCENDING NODE = 90 DEG = .5 PIRAD
I -'J
TRUE ANOMALY OF <P' F 4 14 376 DATA BIT 25 SIGN +0, DEG INJECTION RADIUS VECTOR = 90 DEG = .5 PIRAD
TIME TO INITIATE TRP TRP 4 14 377 DATA BIT 11 = 1 SEC SIGN +15, SEC TB6
TABLE 6-1.- LVDC TELEMETRY NOMENCLATURE, TAGS AND SCALING - Concluded SLY AS-503
NAME MCC ABBR HOSC ABBR PIO MCC PCM HOSC PCM MCC SCALING HOSC SCALING
VEHICLE ALTITUDE ALT ONALT 534 2670 0556 DATA BIT 7 = 1 M SIGN +19
TIME TO GO IN TlI IGTlI 400 2400 0500 DATA BIT 16 = 1 SEC SIGN +10 FIRST IGM
DISCRETE INPUT DIN DI 465 6550 1532 N/A REGISTER
DISCRETE OUTPUT DOR DORSII' 425 6450 1512 N/A REGISTER
THIRD AND FIFTH T31 IGT31 464 2550 0532 DATA BIT 16 = 1 SEC SIGN +10 IGM TIME TO GO
ACCELERATION F/M FOVM 144 2314 2462 DATA BIT 20 = 1 M/S2 SIGN +6 0'\ I STEERING PITCH SMCP SMCY 564 2752 4572 DATA BIT 25 = 90 DEG SIGN +0 OJ
STEERING YAW SMCY SMCZ 560 2742 4570 DATA BIT 25 = 90 DEG SIGN +0
FLIGHT PATH ANGLE aT IGTHAT 550 2720 0564 DATA BIT 25 = 90 DEG SIGN +0
MINOR LOOP CHI Z MLXZ MLCHIZ 501 6600 1540 DATA BIT 25 = 90 DEG SIGN +0
MINOR LOOP CHI X MLXX MLCHIX 505 6610 1542 DATA BIT 25 = 90 DEG SIGN +0
MINOR LOOP CHI Y MLXY MLCHIY 511 6620 1544 DATA BIT 25 = 90 DEG SIGN +0
BEGIN TELEMETRY CYCLE BTC CCCNT 575 6770 1576 N/A
* The scaling on these items will be changed as indicated at second S-IVB cutoff. Uplink and downlink scaling in the ground system must be changed at this time.
* sw AS-503
6.2 ORBITAL PHASE GUIDANCE
A. The guidance system during parking orbit will provide
capability for various attitude maneuvers. The normal
configuration will point vehicle position 1 down and
the longitudinal axis perpendicular to the radius vector.
B. Orbit navigation will be accomplished by integrating the
equations of motions. The drag gravitation and venting
assumed characteristics are programed as a function of
attitude and position of the vehicle. For example, the
platform gimbal angles are sampled every 8 seconds to
resolve the vent acceleration from the body-fixed system
into the space-fixed system.
C. During times between the programed ground sites the
onboard system will perform the normal navigation functions
but will not telemeter real-time data. During the dark
periods the LVDC will perform checks in a self-test
routine and store the data for transmittal when over the
ground stations. The data that may be accumulated (in
addition to CIU data) during the self-test is radiated
in a manner to impose no restrictions on the real-time
data. There will be no loss of mission control data as
a result of compressed data operations.
6-9
-
3
2
-
1
D
ST-124M INERTIAL PLATFORM
= I I I I I I I I
1 LVDA
= COARSE CROSSOVER
= I
~: TO T ..iLACT1JALGIM'BAL I ANGLES (ex~ ey ez) I
\ 0-360' J I , / I
GIMBAL T ANGLE
I
= ,----l-__ ~._~(6~)-=~ DETECTORS
I AID CONVERTER ~l (3) DIGITAL I I I I I I I I
GIMBAL (3 AXIS)
__ ~N~E __ J~
PLATFORM ACCE LERA TIONS -------.
(3 AXIS)
MSC Form 1616 C (REV OCT 65)
2 SPEED
RESOLVERS
I I
= I I I
= FINE I __ (6) I CROSSOVER I (3)
I DETECTORS I AID CONVERTER I I I I I I I I I I I I I I
• I I I
1016 CPS I TIMING GEN AND
FILTER
I I I I I I I
I I
I I I I I
..1
OPTISYNS AND
SIGNAL CONDITIONER
• I I I I I • I I I • I I I I I I I
(6) i I I I I I I I I I I I • I I • I I
CROSSOVER DETECTOR SELECTOR
DELAY LINE (VELOCITY
ACCUMULATION)
-
(6)
! I I I I I I I I I I I I I I I I • I I I I I I I
= I I I I • • I I I
i I • I I I I I I I • I I I I • ~
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LVDC
~ 0Piib\l'i0ItAl'
I PAftAMf TEItS NOTE PARA 6.1 , / '-r-/
COMPUTATION -AND
PROCESSING
OUTPUT
SELECTION
INPUT SELECTION
a DPIAO-08KOO DPIAO-09KOO DPIAO-10KOO DPIAO-llKOO DPIAO-23KOO DPIAO-24KOO DPIAO-25KOO DPIAO-26KOO
SMALL NUMBER IN PARENTHESIS INDICATES THE NUMBER OF FUNCTIONS
: LT'!J.. DR I ENCR I DATE I APPROVAL
I ..1 1 , I
• I I I I I
~I PI TCM GUI&AllCE II
Melt: (Xyl \ 0-360' / I
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\ 0-360' ~ I \ 7 I
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DIGI TAL TO ANALOG CONVERTERS
.... LADDER NElWORK
LADDER
NElWORK
; I I I I I I I I I I I I I
i I I I I • I I I I I I I
=
~ ATTITUDE PITCH ("'Y)
LADD~R OUTPUT Gum ~OMP
\ ±15' J \ / DPIAO-02-08
1 TO CONTROL COMPUTER
~ A TTITUDE ROLL( '" X)
LADDER OUTPUT GUID COMP
\ ±lS' 7 \ 7
ATTITUDE ERRORS
~ I I I I
= ~ I ATTITUDE YAWNZ) I LADDER OUTPUT GUID COMP
• I: ±lS' I I \ 7 = ... .;:a, ___ .. I DPIAOi 02-09
I LADDER Hf--l---il------1--_ I NElWORK i I~--~~ I I I I I I I I I I I I LADDER I
H60-603
i SELECTOR = • I • I • I I I I I I I I I I I I 01
I I
1-::c::--;;;cSI,.G_NA..:.T:.oU,;,R~ESO--:-..-I_D~A7T_E:i NATIONAL AERONAUTICS & SPACE ADMINISTRATION DR "X.~ l1(;.iI~ .~~ MANNED SPACECRAFT CENTER HOUSTON. TEXAS
DSGN~/..,r~ 1!:<:-''''8 QC A' V=L r4'~r'
ENGR R. C .1._~ 8fzzl68 GUIDANCE
TELEMETRY IDENTIFIED BY THE CONNECTING LINE t-A-:-CP:-::P:-~/~'-. _761k.y--.... --+i~-:-c._-l.O.-.-!J"i
rF~E~C~~t:.~:.§;:~~,A~!l,{jZ0/~bj"Q-~~S~L~V~:ziSCIZE DWG NO. I-AUTH 1- 'h,u ,. He AS-503 6.2.1
22 X 17 PAGE 6-10 ISHEET 1 OF 1 • ..
3 ,
•
2
1
*
6.3 GUIDANCE AND NAVIGATION ALIGNMENT
SLV AS-503
A. During prelaunch, the ST-124M platform is held aligned
to the local geodetic vertical by a set of gas bearing
leveling pendulums. The pendulum output is amplified
in the platform, and then transmitted to the ground
equipment alignment amplifier. The alignment amplifier
provides a signal to the torque drive amplifier and then
to the platform gyro torque generator. The vertical
alignment system will level the platform to an accuracy
of ±3 arc seconds.
B. The azimuth alignment is accomplished by means of a
theodolite on the ground and two prisms (one fixed and
one servo-driven) on the platform. The theodolite main
tains the azimuth orientation of the movable prism and
the ground-based digital computer computes a mission
azimuth and programs the inner gimbal to its mission
azimuth. The laying system has an accuracy of ±20
arc seconds.
C. At approximately liftoff minus 17 seconds, the platform
is released to maintain an inertial reference initiated
at the launch point. At this point, the LVDC begins
navigation using velocity accumulations derived from
the ST-124M inertial platform.
6-11
*
6.4 GYRO AND ACCELEROMETER SERVOSYSTEM
SLY AS-503
A. The gyro and accelerometer servoloops use a 4.8 kHz
suppressed carrier modulation system with the signal
generator outputs being amplified and demodulated on
the gimbals of the inertial platform. The dc signal
from the detector output is transferred from the
platform to the platform electronic assembly. The
dc signal is shaped, remodulated at 4.8 kHz amplified"
and then demodulated prior to entering the dc power
bridge. This power bridge provides a current source
drive for the direct axis dc gimbal torquer.
6-12
* SW AS-503
6.5 ACCELEROMETER SIGNAL CONDITIONER
A. The accelerometer signal conditioner accepts the
velocity signals from the accelerometer optical
encoders and shapes them before they are passed on
to the LVDA/LVDC. Each accelerometer requires four
shapers; a sine shaper and cosine shaper for the
active channel and a sine shaper and cosine shaper
for the redundant channel. Also included are four
buffer amplifiers for each accelerometer; one for
each sine and cosine output.
6-13
F E
GYRO SP1Nr-- PICKOFF EXCITATION <lOV CURRENT 4.8 KC SQUARE WAVE) {26V
INNER ~ 400~
GIMBAL TEMP ST-124M PLATFORM
5 INTERNAL GI MBAL Y z
\35 TO 60 0 C J AXIS AXIS 30 DP,y'oo
MIDDLE OUTER GIMBAL GI M8AL
J Y h Y GYRO PRE ~ r-' I f TQ h
t IliESOLVER --, I -' I ~ ZGYRO Z
I PRE
Lpm: __ _TO: ..J
4 t ~ J I
X GYRO I I r-'
GYRO SPIN CURRENT TQ
------ 30 f 012-603"
~~~~:T ~~r~::AL Z ACCEL PR
\ 0 TO 35 PSIA
t Pl~
V l J PICKOFF J- ,-, b TQ
I /1'
o
PR
/XDlH03 t / /
ESSURE STl2~'fIR I~/- ENCODER I ,-, h I BEARING IMlEr
o TO 20 P51D f OPIA&-14-Ge-eO ~ I
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X ACCEL t V I I ENCODER h
f i h
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INTERCONNECTION
X ~ PLATFORM SERVO ~ AXIS t.. C31-603 ~ AMPLIFIER ASSM TEMP S1-124M AIR I y G;~l~~C;UP, FRAME BEARING INLET\
\ 0 TO 30 0 C \ ±P J DPIAO-OI-06-00 DPIAO-27-00-00 'C:7
B>l ~
,...,
"" L H40-603 ~
,Z G;~~l~~C~UP \
±P
B>l DPIAO-03-00-00 ~ ,...,
~
~
L H41-603 ~
IX GYRO PICKUP\ ST-124M
fY-\ ±P J
OPl 0-22-00-00 ~ ~
TQ
~ ,-,
~ Z, tCCELEROMETE
PICKUP STl24 I ,-, \ ±6° /
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~ ---LHl1-603~ X ACCELEROMETE
PICKUP STl24 1 \ ±6° J cp~-oo
~ ~
R
Y
VEHICLE FRAME
B
"
x
t
,~'"-'_ INERTIAL
GSE PtA TFORM ALIGNMENT THEODOLITE
GIMBAL
ST 124-M3 GIMBAL CONFIGURATION -
GIMBAL INNER MIDDLE OUTER
AXIS Y Z X
GIMBAL NOT ±45° NOT LIMITS LIMITED LIMITED
VEHICLE PITCH YAW ROLL AXIS
APPROVAL
5
4
t TQ
~ h J I V
~ '/ ~~gKEU\E~~~~JfR 2 2 Y ACCEL
L I ENCODER ,-, r, '" , J L.-
10>- -0~ -0~ -,-,
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(S V 400-)
~2Y- ~2X ~2X (20 vae)
PICKOFF EXCITATION (10 V 4.8 KG SQ WAVE)
,..., h ~ ~
•
\ ±6° J CPIAO-14-00-00
=:} «00 •••
'C:7
ACCELEROMETER SIGNAL
___ SIGNALS TO LVDA
CONDITIONER :: ACCEl INPUT
B~ ez COARSE GIMBAL ANGLES TO LVDA
BY
B~ 5Z FINE GIMBAL ANGLES TO LVDA
BY
RESOLVER EXCITATION VOLTAGE
f-~';:::7'-'7'-:.--,,,,*,::-DA,,,T,,E:-l NATIONAL AERONAUTICS & SPACE ADMINISTRATION MANNED SPACECRAFT CENTER HOUSTON TEXAS
34 X 22
GUIDANCE -INERTIAL PLATFORM
SIZE DWG NO
6.5.1 6-14 SHEET
* sm AS-503
C. Launch Vehicle Digital Computer, data adapter redundancy,
and triple modular redundancy (TMR) is used in the logic
portion of the Launch Vehicle Digital Computer and Launch
Vehicle Data Adapter. The three redundant circuit channels
are voted upon following selected stage's outputs. Thus,
even if one of the three outputs of a TMR stage is incorrect,
the input to the next stage will be correct.
D. Disagreement Detector
In TMR, each required circuit module is constructed three
times to give three channels of data flow. If anyone
of the modules M1A, M1B, or M1C should fail, one of the
module output signals will be in error. The disagreement
detector will note a disagreement among the three signals
and set an error indication latch. The outputs of the
three voters, however, will be the same as the majority
of the inputs, so with one input error, the voter outputs
will be identical and correct. By voting between stages,
the identical stage in two channels must fail before a
significant failure has occurred.
L-D __ ~_;_i_i_,~_·~_~_,~_·~_N_Jm_~-Jr----~
6-17
TO E~?O.1
~~O;;I~C:i
REGIS'I'ER
SLV AS-503
The Launch Vehicle Digital Computer memory system has two individual
memories which can be used in parallel (duplex). In the
duplex mode, information is read out of both memories from
cores and by means of a selection netwprk, just one memory
output will be used. If the selected memory should contain
an error (parity or timing), the information from the other
memory would be used with the correct information being
read back into both memories. Thus, the computer can
correct its own memory errors.
6-18
6.6 LAUNCH VEHICLE DATA ADAPTER
SW AB-503
A. The Launch Vehicle Data Adapter (LVDA) is the input-output
unit that accompanies the Launch Vehicle Digital Computer
CLVDC). The data adapter can perform a variety of input
output functions and is compatible with the information
rate and interface requirements of IU equipment with
which it must interconnect. The data adapter is divided
into the following distinct parts:
1. A digital section which buffers and manipulates digital
quantities.
2. An analog section which converts analog-to-digital and
digital-to-analog.
3. The power supplies which serve the data adapter, computer,
and memory are contained in the data adapter. These
power supplies are duplexed for reliability; thus,
each supply must be capable of supplying the full
current load for that voltage. Voltage sequencing
is provided where required, and power supply lines
can be switched to permit single channel computer
operation.
4. Communication with the Launch Vehicle Digital Computer
is carried out through 512 kbps serial transmission.
The process input-output instruction permits the
specification of either input or output operations,
and addresses the device to be affected. A single
26-bit word is transferred to the computer accumulator
or from the accumulator or memory.
B. Data Adapter Internal Functions
Although the routing of data is an important data adapter
function, the data adapter must also process much of the
data it transmits. The internal operation of the data
adapter is broken down into three main categories:
6-15
* SLV AS-503
1. The control of data flow, including temporary storage;
2. The transformation of data into a form which is com
patible with the characteristics of the receiving
equipment.
3. The performance of certain simple computational and
logical operations on the data.
The following functions are typical of those included in
the first category:
1. The storage of telemetry data from the computer and
data adapter in the buffer registers.
2. The temporary storage of telemetry scanner addresses
during orbital checkout.
3. The transmission of guidance data from the computer
to the analog co~trol computer.
Operations which required a change in the form of the
data include (typical of those in the second category):
1. Digital-to-analog, analog-to digital, and signal
level conversions.
2. The formation of 40-bit launch computer and telemetry
words from 26-bit computer words.
3. Buffering of communications between the computer and
the ground-based launch computer to reconcile the
difference in clock rates.
The data adapter contributes to the efficient operation
of the computer by performing many simple, though time
consuming, logical and computational tasks, such as
(typical of those functions performed in the third
category):
1. Keeping track of real time.
2. Decoding of operand addresses in process input-output
operations.
* S~ AB-503
6.7 LAUNCH VEHICLE DIGITAL COMPUTER
A. The LVDC is a serial machine using a random access magnetic
core memo~. It uses micro-miniature packaging techniques
and triple modular reliability. Glass delay lines are
used for the serial arithmetic registers and for~he
storage of the instruction counter.
B. Memo~ words are 28 bits in length which includes two
parity bits. The memo~ consists of eight identical
4096-word memo~ modules which are operated in duplex
pairs for high reliability.
C. The LVDC operates on a basic clock time of 512 kbps.
Standard machine cycle time of the LVDC is approximately
82 microseconds. This standard cycle time is based on
an add or subtract arithmetic function.
Six status words are telemetered from the LVDC through
the LVDA. The presence of a bit in the positions
identified will be interpreted in accordance with the
formats on the following pages.
6-20
*
LVDC 10 BIT OCTAL
S - - - -
1
2
3 - - - -4
5
6 - - - -7
8
9
10 - - - -
11
12
13 - - - -14
15
16
17
18
19
20
21
22
23 - - - -24
25
ERROR MONITOR REGISTER
FCO
SLY AS-503
8 BIT OCTAL BIT DESCRIPTION
D26
D25 - - - -D24
D23
D22 - - - -D21
D20
Dl9
Dl8
Dl7 - - - -Dl6
Dl5
Dl4 - - - -Dl3
Dl2
Dll
DlO
D9 - - - -D8
D7
D6 - - - -
,D5
D4
D3
D2
Dl
6-21
COMPUTER FAILURE
MEMORY "B" FAILURE
MEMORY "A" FAILURE
LADDER "A" FAILURE
MODE CODE 24 GUIDANCE STATUS WORD SLY AS-503
LVDC FCO 10 BIT OCTAL 8 BIT OCTAL BIT DESCRIPTION
S D26 ACCEL. REASONABLENESS FAILURE, Z (A) - - - -1 D25 ACCEL. REASONABLENESS FAILURE, Z (B) - - - -2 D24 ACCEL. REASONABLENESS FAILURE, X (A)
3 D23 ACCEL. REASONABLENESS FAILURE, X (B) - - - -4 D22 ACCEL. REASONABLENESS FAILURE, Y (A) - - - -5 D21 ACCEL. REASONABLENESS FAILURE, Y (B)
6 D20 GIMBAL ANGLE REASONABLENESS FAILURE, Z (BACKUP) - - - -7 Dl9 GIMBAL ANGLE REASONABLENESS FAILURE, Z (FINE)
8 Dl8 GIMBAL ANGLE REASONABLENESS FAILURE, X (BACKUP)
9 D17 GIMBAL ANGLE REASONABLENESS FAILURE, X (FINE) - - - -10 Dl6 GIMBAL ANGLE REASONABLENESS FAILURE, Y (BACKUP) - - - -11 Dl5 GIMBAL ANGLE REASONABLENESS FAILURE, Y (FINE)
12 Dl4 } GIMBAL ANGLE DISAGREEMENT (> ZERO) - - - - (= ZERO) 13 Dl3
- - - -14 Dl2 GIMBAL ANGLE DISAGREEMENT COUNTER "A" FAILED
15 Dl1 GIMBAL ANGLE DISAGREEMENT COUNTER "B" FAILED
16 DlO LADDER A FAILURE - - - -17 D9 SWITCH SELECTOR CHANNEL "B" SELECTED - - - -18 D8
19 D7
20 D6 COD MULTIPLEXER A BAD - - - - - - - -
21 D5 COD MULTIPLEXER B BAD
22 D4 Z ACCELEROMETER 0 READING
23 D3 X ACCELEROMETER 0 READING - - - -
24 D2
25 Dl
6-22
MODE CODE 25
LVDC 10 BIT OCTAL
S
1
2
3 - - - -4
5
6
7
8
9
10
11
12
13
14
15
16
17
18
19 20
21
22
23
24
25
GUIDANCE MODE WORD 1 SLY AS-503
FCO 8 BIT OCTAL
D26
D25 - - - -D24
D23
D22
D21
D20
Dl9
ms Dl7 - - - -Dl6
Dl5
Dl4
D13
Dl2
Dl1
DlO
D9
DS
D7 D6
D5
D4
D3
D2
D1
BIT DESCRIPTION
GUIDANCE REFERENCE RELEASE (GRR) (INT 7) (START TBO)
LIFTOFF (START TB1) (DIN 24)
START PITCH & ROLL
STOP ROLL
STOP PITCH
START (TB2)
S-IC OUTBOARD ENGINE CUTOFF (START TB3) (INT 5)
S-IC INBOARD ENGINE OUT (DIN 11)
S-IC OUTBOARD ENGINE OUT (DIN 14)
S-II SKIRT SEPARATION (DIN 15)
BEGIN FIRST PHASE IGM GUIDANCE (S-II FIRST BURN)
S-II ENGINE MIXTURE RATIO CHANGE (EMRC) (2ND PHASE IGM)
S-II CUTOFF (START TB4)
S-II OUTBOARD ENGINE OUT (DIN 21)
S-II INBOARD ENGINE OUT (DIN 13)
S-II/S-IVB SEPARATION (DIN 10)
FIRST S-IVB IGNITION
START 3RD PHASE IGM
START S-IVB TERMINAL GUIDANCE
FIRST S-IVB CUTOFF COMMAND
BEGIN TIME BASE 5 (T5
)
START S-IVB CHILLDOWN SEQUENCE (START TB6)
6-23
MODE CODE 26
LVDC 10 BIT OCTAL
S
1
2
3 - - - -4
5
6
7
8
9
10
11
12
13 - - - -14
15
16
17
18
19
20
21
22
23 - - - -24
25
-GUIDANCE MODE WORD 2 SLY
AS-503
FCO 8 BIT OCTAL
D26
D25
D24
D23
D22
D21
D20
D19
Dl8
Dl7
Dl6
Dl5
Dl4
Dl3
Dl2
Dll
DlO
D9
D8
D7
D6
D5
D4
D3
D2
Dl
BIT DESCRIPTION
START S-IVB REIGNITION (SECOND BURN)
S-IVB REIGNITION (THIRD BURN)
SECOND S-IVB CUTOFF COMMAND
START TB7
sic INIT OF S-IVB CUTOFF (DIN 17 OR 22)
CONTROL COMPUTER SWITCHED TO sic (DIN 9)
sic INITIATION OF S-II/s-IVB SEPARATION (DIN 17 OR 22)
STEERING MISALIGNMENT CORRECTION (SMC)
O2 - H2 BURNER MALFUNCTION 1 (T6A)
TLC - SIMULTANEOUS MEMORY FAILURE (INT 9)
GUIDANCE FAILURE (D04)
START S-IVB REIGNITION SEQUENCE (THIRD BURN)
START S-IVB REIGNITION SEQUENCE (THIRD BURN -NO SECOND BURN)
THIRD S-IVB CUTOFF COMMAND
BEGIN TIME BASE 9
PREFLIGHT ABORT
6-24
MODE CODE 27
LVDC 10 BIT OCTAL
S - - - -
1
2
3 - - - -4
5
6 - - - -7
8
9
10
11
12
13
14
15
16 - - - -17
19
20 - - - -
21
22
23 - - - -
24
25
ORBITAL MODE WORD SLV AS.,.503
FCO 8 BIT OCTAL
D26
D25 - - - -D24
D23
D22 - - - -D21
D20
Dl9
Dl8
D17 - - - -Dl6
D15
Dl4 - - - -
Dl3
D12
Dll
DlO
D9 - - - -D7
D6
D5
D4
D3
D2
Dl
BIT DESCRIPTION
POWERED FLIGHT DCS INHIBIT REMOVED
PCM & CCS ANT - LOW GAIN
PCM & CCS ANT - HIGH GAIN
PCM & CCS ANT - OMNI
NAVIGATION UPDATE RECEIVED
TIME BASE UPDATE RECEIVED
TRACK LOCAL HORIZ - POS I DOWN (MAN 2, 4, 6, 9, 10, 12)
TRACK LOCAL HORIZ IN RETRO ATT - POS I UP (MAN 5)
BEGIN ORBITAL SAFING SEQUENCE (SET AT TB9 + T19FS IN ORBITAL GUIDANCE)
INERTIAL ATTITUDE HOLD IN PROGRESS (MAN 1, 3, 7, 8, 11)
CONT RET FROM sic (ATT HOLD WIR TO LOCAL REF)
CONT RET FROM Sic (ATT HOLD wlR TO INERTIAL REF)
INHIBIT MANEUVER 3 (DCS INHIBIT #1)
INHIBIT MANEUVER 4 (DCS INHIBIT #2) PROGRAMED INITIALLY SET
INHIBIT MANEUVER 5 (DCS INHIBIT #3)
RESTART MANEUVER INHIBIT SET (PROGRAMED INITIALLY SET)
6-25
MODE CODE 28 ORBITAL STATUS WORD SLV AS-503
LVDC FCO 10 BIT OCTAL 8 BIT OCTAL BIT DESCRIPTION
S D26 ACCEL REASONABLENESS FAILURE, Z (A) - - - -1 D25 ACCEL REASONABLENESS FAILURE, Z (B) - - - -2 D24 ACCEL REASONABLENESS FAILURE, X (A)
3 D23 ACCEL REASONABLENESS FAILURE, X (B) - - - -
4 D22 ACCEL REASONABLENESS FAILURE, Y (A)
5 D21 ACCEL REASONABLENESS FAILURE, Y (B)
6 D20 - - - - GIMBAL ANGLE REASONABLENESS FAILURE, Z (BACKUP)
7 Dl9 GIMBAL ANGLE REASONABLENESS FAILURE, Z (FINE) A Dl8 GIMBAL ANGLE REASONABLENESS FAILURE, X (BACKUP)
9 Dl7 GIMBAL ANGLE REASONABLENESS FAILURE, X (FINE)
10 Dl6 GIMBAL ANGLE REASONABLENESS FAILURE, Y (BACKUP) - - - -11 Dl5 GIMBAL ANGLE REASONABLENESS FAILURE, Y (FINE)
12 Dl4 - - - -13 Dl3 - - - -14 Dl2
15 D11
16 DID - - - -17 D9 - - - -18 D8
19 D7
20 D6 COD MULTIPLEXOR A BAD - - - - - - - -21 D5 COD MULTIPLEXOR B BAD
22 D4
23 D3 - - - -24 D2
25 Dl
6-26
LVDC 10 BIT OCTAL
S - - - -1
2
3 - - - -4
5
6 - - - -7
8
9
10 - - - -11
12
13 - - - -14
15
16 - - - -17
18
19
20 - - - -21
22
23 - - - -24
25
FCO 8 BIT OCTAL
D26
D25 - - - -D24
D23
D22 - - - -D21
D20
Dl9
Dl8
Dl7 - - - -Dl6
Dl5
Dl4 - - - -Dl3
Dl2
Dll
DlO
D9 - - - -D8
D7
D6 - - - -D5
D4
D3
D2
Dl
LVDC TIME
BIT DESCRIPTION
32 768 SECONDS
16 384
8192
4 096
2 048
1 024
512
256
128
64
32
16
8
4
2
1
6-27
SLY AS-503
LVDC POSITIONS SLV AS-503
LVDC FCO 10 BIT OCTAL 8 BIT OCTAL BIT DESCRIPTION
SIGN D26 SIGN (0 = POSITIVE; 1 = NEGATIVE) - - - -1 D25 4 194 304 METERS 67 108 864 - - - -2 D24 2 097 152 33 554 432
3 D23 1 048 576 16 777 216 - - - -4 D22 524 288 8 388 608 - - - -5 D21 262 144 4 194 304
6 D20 131 072 2 097 152 - - - -7 Dl9 65 536 1 048 576
8 D18 32 768 524 288
9 D17 16 384 262 144 - - - -10 D16 8 192 131 072 - - - -11 Dl5 4 096 65 536 12 Dl4 2 048 32 768 - - - -13 Dl3 1 024 16 384 - - - -14 Dl2 512 8 192
15 D11 256 4 096
16 DlO 128 2 048 - - - -17 D9 64 1 024
- - - -18 D8 32 512
19 D7 16 256
20 D6 8 128 - - - - - - - -21 D5 4 64
22 D4 2 32
23 D3 1 16 - - - -24 D2 8
25 Dl 4 PARKING WAITING
ORBIT ORBIT
6-28
LVDC SPACE FIXED POSITIONS SLV AS-503
Conversion from octal to engineering units (kilometers). This conversion assumes a fill of one zero to left of LVDC MSB. The data provides for the eight MSB LVDC downlink bits.
OCTAL ENGR OCTAL ENGR OCTAL -ENGR OCTAL ENGR
+ K + K + K + K
000 000 0000 330 050 2621 260 120 5243 207 171 7930 377 001 66 327 051 2687 257 121 5308 206 172 7995 376 002 131 326 052 2753 256 122 5374 205 173 8061 375 003 197 325 053 2818 255 123 5439 204 174 8126 374 004 262 324 054 2884 254 124 5505 203 175 8192 373 005 328 323 055 2949 253 125 5570 202 176 8258 372 006 393 322 056 3015 252 126 5636 201 177 8323 371 007 459 321 057 3080 251 127 5702 370 010 524 320 060 3164 250 130 5767 367 011 590 317 061 3211 247 131 5833 366 012 655 316 062 3277 246 132 5898 365 013 721 315 063 3342 245 133 5964 364 014 786 314 064 3408 244 134 6029 363 015 852 313 065 3473 243 135 6095 362 016 918 312 066 3539 242 136 6160 361 017 983 311 067 3604 241 137 6226 360 020 1048 310 070 3670 240 140 6291 357 021 1114 307 071 3736 237 141 6357 356 022 1180 306 072 3801 236 142 6423 355 023 2294 305 073 3867 235 143 6488 354 024 1311 304 074 3932 234 144 6554 353 025 1376 303 075 3998 233 145 6619 352 026 1442 302 076 4063 232 146 6685 351 027 1507 301 077 4129 231 147 6750 350 030 1572 300 100 4194 230 150 6816 347 031 1638 277 101 4260 227 151 6881 346 032 1704 276 102 4325 226 152 6947 345 033 1769 275 103 4391 225 153 7012 344 034 1835 274 104 4456 224 154 7078 343 035 1901 273 105 4522 223 155 7143 342 036 1966 272 106 4588 222 156 7209 341 037 2032 271 107 4653 221 157 7274 340 040 2097 270 110 4719 220 160 7340 337 041 2163 267 111 4784 217 161 7406 336 042 2282 266 112 4850 216 162 7471 335 043 2294 265 113 4915 215 163 7537 334 044 2359 264 114 4980 214 164 7602 333 045 2425 263 115 5046 213 165 7668 332 046 2490 262 116 5112 212 166 7733 331 047 2556 261 117 5177 211 167 7799
210 170 7864 6-29
LVDC FCO 10 BIT OCTAL 8 BIT OCTAL
SIGN D26 - - - -1 D25 - - - -2 D24
3 D23 - - - -4 D22 - - - -5 D21
6 D20 - - - -
7 Dl9
8 Dl8
9 D17 - - - -10 Dl6 - - - -11 D15
12 Dl4 - - - -13 DB - - - -14 Dl2
15 D11
16 DlO - - - -17 D9 - - - -18 D8
19 D7
20 D6 - - - - - - - -21 D5
22 D4
23 D3 - - - -
24 D2
25 Dl
LVDC VELOCITY SLY AS-503
BIT DESCRIPTION
SIGN (0 = POSITIVE; 1 = NEGATIVE)
8 192 METERS/SECOND
4 096
2 048
1 024
512
256
128
64
32
16
8
4
2
1
.5
6-30
LVDC SPACE FIXED VELOCITY SLV AS-503
Conversion from octal to engineering units (meters/second). This conversion assumes a fill of one zero to left of LVDC MSB. The data provides for the eight MSB LVDC downlink bits also with a fill bit to left.
OCTAL ENGR OCTAL ENGR OCTAL ENGR OCTAL ENGR
+ M/S + M/S + M/S + M/S
000 000 0000 330 050 5120 260 120 10240 210 170 15360 377 001 128 327 051 5248 257 121 10368 207 171 15488 376 002 256 326 052 5376 256 122 10496 206 172 15616 375 003 384 325 053 5504 255 123 10624 205 173 15744 374 004 512 324 054 5632 254 124 10752 204 174 15872 373 005 640 323 055 5760 253 125 10880 203 175 16000 372 006 768 322 056 5888 252 126 11008 202 176 16128 371 007 896 321 057 6061 251 127 11136 201 177 16256 370 010 1024 320 060 6144 250 130 11264 367 011 1152 317 061 6272 247 131 11392 366 012 1280 316 062 6400 246 132 11520 365 013 1308 315 063 6528 245 133 11648 364 014 1536 314 064 6656 244 134 11776 363 015 1664 313 065 6784 243 135 11904 362 016 1792 312 066 6912 242 136 12032 361 017 1920 311 067 7040 241 137 12160 360 020 2048 310 070 7168 240 140 12288 357 021 2176 307 071 7296 237 141 12416 356 022 2034 306 072 7424 236 142 12544 355 023 2432 305 073 7552 235 143 12672 354 024 2560 304 074 7680 234 144 12800 353 025 2688 303 075 7808 233 145 12928 352 026 2816 302 076 7936 232 146 13056 351 027 2944 301 077 8064 231 147 13184 350 030 3072 300 100 8192 230 150 13312 347 031 3200 277 101 8320 227 151 13440 346 032 3328 276 102 8448 226 152 13568 345 033 3456 275 103 8576 225 153 13696 344 034 3584 274 104 8704 224 154 13824 343 035 3712 273 105 8832 223 155 13952 342 036 3840 272 106 8960 222 156 14080 341 037 3968 271 107 9088 221 157 14208 340 040 4096 270 110 9216 220 160 14336 337 041 4224 267 111 9344 217 161 14464 336 042 4352 266 112 9472 216 162 14592 335 043 4480 265 113 9600 215 163 14720 334 044 4608 264 114 9728 214 164 14848 333 045 4736 263 115 9856 213 165 14976 332 046 4864 262 116 9984 212 166 15104 331 047 4992 261 11 7 10112 211 167 15232
6-31
LVDC FCO 10 BIT OCTAL 8 BIT OCTAL
S D26 - - - -1 D25 - - - -2 D24
3 D23 - - - -4 D22 - - - -5 D21
6 D20 - - - -7 D19
8 Dl8
9 D17 - - - -10 Dl6 - - - -11 Dl5
12 Dl4 - - - -13 Dl3 - - - -14 D12
15 D11
16 DlO - - - -17 D9 - - - -18 D8
19 D7
20 D6 - - - -21 D5
22 D4
23 D3 - - - -24 D2
25 Dl
LVDC ANGLES SLV AS-503
BIT DESCRIPTION
180 DEGREES
90
45
22.5
11.25
5.625
2.812 5
1.406 25
.703 125
.351 562 5
.175 781 25
.087 890 625
.043 945 312
.021 972 656
.010 986 328
.005 493 164
.002 746 582
.001 373 291
.000 686 645
.000 343 323
.000 171 661
.000 085 831
.000 042 915
.000 021 457
.000 010 728
.000 005 364
6-32
SLY ANGULAR QUANTITIES SLY AS-503
Conversion from octal to engineering units (degrees). This conversion assumes a fill of one zero to the left of the LVDC MSB. The data pro-vides for the eight MSB LVDC downlink bits also with a fill of zero to left.
OCT DEG OCT DEG OCT DEG OCT DEG OCT DEG OCT DEG
000 000 060 68 140 135 220 203 300 270 360 338 001 1 061 69 141 136 221 204 301 271 361 339 002 3 062 70 142 138 222 205 302 273 362 340 003 4 063 72 143 139 223 207 303 274 363 342 004 6 064 73 144 141 224 208 304 276 364 343 005 7 065 75 145 142 225 210 305 277 365 345 006 8 066 76 146 143 226 211 306 278 366 346 007 10 067 77 047 045 227 212 307 280 367 347 010 11 070 79 150 146 230 214 310 281 370 349 011 13 071 80 151 148 231 215 311 283 371 350 012 14 072 82 152 149 232 217 312 284 372 352 013 15 073 83 153 150 233 218 313 285 373 353 014 17 074 84 154 152 234 219 314 287 374 354 015 18 075 86 155 153 235 221 315 288 373 356 016 20 076 87 156 155 236 222 316 290 376 357 017 21 077 89 157 156 237 224 317 291 377 359 020 23 100 90 160 158 240 225 320 293 021 24 101 91 161 159 241 226 321 294 022 25 102 93 162 160 242 228 322 295 023 27 103 94 163 162 243 229 323 297 024 28 104 96 164 163 244 231 324 298 025 30 105 97 165 165 245 232 325 300 026 31 106 98 166 166 246 233 326 301 027 32 107 100 167 167 247 235 327 302 030 34 110 101 170 169 250 236 330 304 031 35 111 103 171 170 251 238 331 305 032 37 112 104 172 172 252 239 332 307 033 38 113 105 173 173 253 240 333 308 034 39 114 107 174 174 254 242 334 309 035 41 115 108 175 176 255 243 335 311 036 42 116 110 176 177 256 245 336 312 037 44 117 111 177 179 257 246 337 314 040 45 120 113 200 180 260 248 340 315 041 46 121 114 201 181 261 249 341 316 042 48 122 155 202 183 262 250 342 318 043 49 123 117 203 184 263 252 343 319 044 51 124 118 204 186 264 253 344 321 045 52 125 120 205 187 265 255 345 322 046 53 126 121 206 188 266 256 346 323 047 55 127 122 207 189 267 257 347 325 050 56 130 124 210 191 270 259 350 326 051 58 131 125 211 193 271 260 352 328 052 59 132 127 212 194 272 262 352 329 053 60 133 128 213 195 273 263 353 330 054 62 134 129 214 197 274 264 354 332 055 63 135 131 215 198 275 266 355 333 056 65 136 132 216 200 276 267 356 335 057 66 137 134 217 201 277 269 357 336
6-33
LVDC 10 BIT OCTAL
SIGN - - - -1
2
3 - - - -4
5
6 - - - -7
8
9
10 - - - -11
12
13 - - - -14
15
16 - - - -17
18
19
20 - - - -21
22
23 - - - -24
25
TIME TO GO TO S-IVB CUTOFF
FCO 8 BIT OCTAL BIT DESCRIPTION
D26
D25 512 - - - -
D24 256
D23 128
D22 64 - - - -
D21 32
D20 16
Dl9 8
Dl8 4
Dl7 2 - - - -
Dl6 1
Dl5 .5
Dl4 .25 - - - -Dl3 .125
D12 .062 5
D11 .031 25
DlO
D9 - - - -D8
D7
D6 - - - -D5
D4
D3
D2
Dl
6-34
SLY AS-503
7
6
5
... 4
3
2
H G
TIMING ELEMENT
O~~ GEN ~~~E GEN ~ Wt G!THRU !7 PUB to
READ/STORE
I SYLLABLE: I SELECTOR
INSTRUCTION SECTOR REG
DATA SECTOR REG MEMORY MEMORY TIMING
I ADDRESS REG ADDRESS AND DECODER SYNC SELECT
OP CODES
AI-A9 INTV
TO LVDA INTCV
i FROM LvaA
PROGRAM CONTROL ELEMENT ~ I INTERRUPT I
CONTROL I
ADDRESS REGISTER
I OPERATION I I DATA SECTOR CODE REG
I REGISTER
INSTRUCTION SECTOR REG
HOP
I CONSTANT
MEM SERIALIZER
MOO REGS
HALTV START-STOP I FROM CONTROL LVOA
1 1 I OPERATION
DECODERS
F E D c
A , B i (EVEN) COOOl
X X DRIVERS DRIVERS
~ Y CODE
ci~,~~~TS I I INHIBIT CODE Y
C54- 603 ARRAY ARRAY TEMP GUlg DRIVERS (EVEN) DRIVERS (ODD) DRIVERS
...,CMPTR (MEM RY) -, T 0°.100. C
CPl~-VO
SENSE ERROR ERROR J "MEMORY
DETECTOR DETECTOR SENSE AMPS AMPS
X ADDRESS ~ ~ DRIVERS CLOCK CLOCK X DRIVERS DRIVERS
SYNC I
I MEMORY I PARITY MEMORY SELECT
I MEMORY AND PARITY . BUFFER A CHECK ERROR MONITOR CHECK SOFFER B
MEMORY MODE I AND
MODULE SELECT TLCV, EAMV, EBMV TO LVDA
REAO READ
STORE MEM MOO PARITY BIT REGS
DATA CONTROL ELEMENT
PARITY TRANSFER REGISTER
I INTV COUNTER (13 BITS) FROM
I t LVDA
OP
AI-A9 I L OPCODES
CODES
rTo OPI- OP4 INTV LVDA
n MULTIPLIER
MULTIPLIER MULT PRODUCT I QUOTIENT REG
PRODUCT tEUOTIENT , ~l'""
DIVIDEND PARTIAL PRODUCT I REMAINDER REGISTER
MO,
t=: DIVISOR
MULTI?LICAND MULTIPLICAND
=},o DIVISOR REGISTER
--TO LVDA
t
STORE
PARlTYSIT
ARITHMETIC ELEMENT
~ ACCUMULATOR AOD REGISTER
SUBTRACT J LOGIC r..;-----:. INSTRUCTION r f COUNTER
+ 1 I
MUlTIPLY - DIVIDE ElEMENT
PRODUCT I MULTIPLY - DIVIDE QUOTIENT TIMING
7i +
DIVIDE I MULT"LV I 1 LOGIC
~; M
o LVDA
OP CODES
B
SIGNATURES DATE
DRW ..... .tvMf&_ ~ DSGN~O<: ,,.. QC "" /~ ~I
ENGR eo;
APP , " FEC AUTH 9-348
I.
A LTR DR EOGR DATE A?? VAL
NATIONAL AERONAUTICS & SPACE ADMINISTRATION MANNED SPACECRAFT CENTER HOUSTON """'"
GUIDANCE-DIGITAL COMPUTER
SLY 6.7.1 AS-503
40 X 28 SHEET OF
7
6
5
.. 4
3
2
D
4
-
-
1
I c
SERIAL OUTPUT TO RF
3600 PPS SYNC
4 PPS SYNC
B
SIGNATURES DR ~_ /.7.
DSGN&'~""" "'{..:a... QCAlz.~ J,.,/.;
ENGR 2c .. ~u.i4-
APP ("" !L~ FEC ,1;;.-
AUTH..I!" !&.
•
DATE
I-'/?-~ 15"'~8 1'/":':'
84~6f
rJuI6"
A LTRI DR I ENGR I DATE I APPROVAL
I I I I I
NATIONAL AERONAUTICS & SPACE ADMINISTRATION MANNED SPACECRAFT CENTER HOUSTON. TEXAS
GUIDANCECOMPUTER
INTERFACE UNIT lr/~.? SL V SIZE DWG NO.
6.7.2 22 X 17 PAGE 6-36 ISHEET 1 OF 1
4
1
* S~ AS-503
6.8 NOTES - CIU
A. Selective transfer of measurement values from the IU
Telemetry systems to the LVDA is accomplished through
the computer interface assembly. This assembly contains
the timing and comparison logic necessary to separate
the selected channel from the IU PCM format.
B. The LVDA signifies the specific data channel to be trans
ferred by means of a l2-bit channel address. Upon receipt
of a "data-request" signal from the LVDA, the computer
interface assembly initiates a transfer sequence which
consists of:
• Awaiting the next appearance of the signified channel
in the PCM/DDAS format
• Writing the data sample into a lO-bit holding register
within the assembly
• Providing a "data-ready" signal to the LVDA indicating
that the selected data is available.
C. For as long as the "data-request" signal remains at the
request level, subsequent samples of the selected channels
are transferred into the holding register as they appear
in the format of the PCM/DDAS assembly. When the LVDA
returns the "data-request" signal to the standby level,
the last value transferred remains in the holding register
until another transfer sequence is initiated.
D. When the LVDA receives the "data-ready" signal, it branches
to a subroutine which operates to transfer the data from
the telemetry output register to the LVDA. Synchronization
between the telemetry system and the LVDA is accomplished
in the following manner: Each time the telemetry receives
an address from the LVDA, followed by a valid "data-request"
signal, it recognizes this input as the initiation of new
data seeking cycle as well as a signal to read in the data.
6-37
* SLY
AS-503
Upon this recognition by telemetry, it first resets its
output data register and then begins seeking the data
requested by the LVDA. The LVDA and LVDC insures that
a new address with a valid read bit is not generated
until data from the telemetry output register has been
received in response to the previous address.
6-36
* SECTION 7
CONTROL
SLV AS-503
7.1 DEFINITION OF THE CONTROL SYSTEM
The control system is composed of all the equipment which is
necessary to control the thrust vector of the launch vehicle
engines during the active boost phases and maintain proper
vehicle attitude during orbital coast phases. The major com
ponents of the control system are the Flight Control Computer,
the Control EDS rate gyro package, and the Control Signal
Processor. The major interfaces fo the control system are with
the Launch Vehicle Data Adapter, the IU switch selector, the
S-IC, 8-11 and S-IVB engine actuators and the control relay
package for the auxiliary propulsion system.
I, CONTROL
7-1
4
3
2
H
CHAN 31 SS 043
ON"A"
G
~p
CONTROL EDS ~y
RATE GYRO
PACKAGE ~R
RESET RESET BUS NO 2 BUS NO 1
CHAN 12 SS 115
OFF"A"
CHAN 75 SS 024
OFF "B"
CMD FCC S--IVB BURN MODE
STl24 STABLE
PLATFORM\
CHAN 74 SS 004
ON "B"
CHAN 33 SS 034
CMD SWITCH ENG CONTROL FROM S-IC TO S-II
SW 5EL 603A17
LAUNCH VEHICLE DIGITAL
COMPUTER
LAUNCH VEH I CLE DATA ADAPTER
F
~p PITCH RATE
CONTROL SIGNAL
PROCESSOR. YAW RATE SEE DWG ~v
741
~R ROLL RATE
602A2 K23
RESET .-:. .. BUS NO 1
K93
B> +6031
+6011
r--------, I S-IISTAGE 602A2 K34 I I I I I I I
• K34
.. K4
0>
E
~p
~V
~R S-IC
ACTUATOR OUTPUTS
$-IVB BURN MODE
I +6011 I GSE S-IC BURN L ________ J MODESUBST!TUTE ;>---t----'
+6D11 *.r-----oo~ coV~Ll
t----------------~---.~~P
t---------------~~--------_r----__1~R
t----~----------~r_----------1_-----.~~V
SPACECRAFTl ATTITUDE ---------------.. ERRORS
--------------------~
6Dll 28 VDe
6031 28 voe
6041 28 VDe
v
SIC CONTROL
S-II ACTUATOR OUTPUTS
IU G&N STEERING COMMANDS
S-IVB MAIN
E-NGINE OUTPUTS
FLIGHT CONTROL
COMPUTER
S-IVB APS
OUTPUTS
QPIAO-lS-lO
• • • • • • • • • • •
0 C B
• APPROVAL • • • • • • • • •
S-IC ENGINES VI EWED FROM AFT
[Y
S-IC ••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••• • •••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••••• • 3-V S-II
S-II ENGINES VIEWED FROM AFT
ENGINE GIMBAL ACTUATORS
S-II I····················································· .................... . I ·············•·•••···············•·•••••···•••••••·· ......••••••••...••••.
1-V S-IVB • ill • • • 1-P
• • • • • • • • •
II
S-IVB MAIN ENGINE
D:> SEE DWG 7 2 2 FOR S-IC AND S-II ACTUATOR TELEMETRY
• R-VI + ,..---.... HIt-lt-::-c-:-:---2...J R-YI
~ RELAYS K92 AND K93 ARE CONTROLLED V"" BY S-IVB THRUST a K SWITCHES AND
ARE DE-ENERGIZED WHEN S-IV8 THRUST IS 0 K
R-YII + R-YII
PITCH + PITCH
• • • • • • • • • • • • • • • •
CONTROL RELAY APS
PACKAGES
NOTES B> RELAY K4 1 S LIFTOFF RELAY AND IS DE-ENERGIZED AT LIFTOFF
'-:::-cmS;,-'G_N_AT_U_R-:ES;-;-::--t;..::D::AT..::';::i NATIONAL AERONAUTICS & SPACE ADMINISTRATION I MANNED SPACECRAFT CENTER HOUSTON TEXAS
FLIGHT CONTROL COMPUTER
INTERFACE DWG DWG NO
~ IU • • • • 7.1.1
34 X 22 7-2 SHEET 1 OF 1
•
4
3
2
7.2 CONTROL SYSTEM OPERATION
SLV AS-503
A. The prime component of the control system is the Flight
Control Computer (FCC). The FCC is an analog computer
which accomplishes two primary functions:
1. It solves and instruments the vehicle thrust vector
e'luation:
Pitch: Spc = aop1J!p + a cj> Ip P
Yaw: Syc = a 1J! + alycj>y oy y
Roll: Src aor1J!r + a cj> lr r
where
Spc' Syc' /3rc is commanded thrust direction
a is control system attitude 0 error gain
a l is control system attitude rate gain
1J!p' 1J!y' 1J!r is vehicle attitude error
cj>p' cj>y' cj>r is vehicle attitude rate
This e'luation calculates the angle which must exist
between the thrust vector (axis of engine thrust) and
the longitudinal axis of the vehicle in order to main
tain stable flight along the desired trajectory. The
FCC outputs control signals to the individual actuators
in accordance with the following e'luations:
i3 /12 rc
i3p2c Spc + S /12 rc
/3p3c = /3pc i3 Iff rc
/3p4c = /3 + S /12 pc rc
/3ylc = /3 + /3 /12 yc rc
7-3
*
By2c = Byc
By3C = B + yc
By4c = Byc
B /12 rc
B /12 rc
B /12 rc
SLY AS-503
where B 1 is the commanded pitch motion for engine p c
number one, et cetera.
2. It provides control signals to the APS engines to
establish and maintain vehicle attitude during coasting
flight. These control signals are represented by the
following equations which give error command (E) to the
pseudo-rate modulator (spatial amplifier):
Pitch: E a 1jJ + a ¢ p op P lp P
Yaw-Roll Mixed: E aoyljJy a ljJ + aly¢y alr¢r y-r or r
E a ljJ + a ljJ + a ¢ + alr¢r y+r oy y or r ly y
The following table illustrates the polarity of the
signal required to cause each engine to fire:
Error Signal Engine On
a. +E I (+p) P P
b. -E III (-p) P P
c. +E IIIII (+y, -r) y-r d. -E IIIlV (-y, +r) y-r e. +E y+r III (+y, +r)
f. -E y+r IIV (-y, -r)
B. The FCC has the following modes of operation (exclusive
of GSE test configurations):
1- S-IC Burn
2. S-II Burn
3. S-IVB Burn
4. S-IVB Coast
5. Spacecraft Control
7-4
*
SLV AS-503
This mode switching of the FCC performs the function of
routing the input signals through the proper filters and
amplifiers and routing the engine control signals to the
appropriate stage actuators. The FCC is put into the S-IC
Burn Mode with a GSE command prior to liftoff. At liftoff,
relay K4 (drawing 7.1.1) is deenergized applying 28 Vdc
to the FCC in order to maintain the S-IC Burn Mode configur
ation. The 8-11 Burn Mode is achieved with a switch selector
command which energizes relay K34 (drawing 7.1.1) applying
28 Vdc to the 8-11 Burn Mode circuitry. Power is removed
from the S-11 Burn Mode circuits by the physical separation
of the S-11 stage from the S-IVB stage. The S-IVB Burn Mode
is achieved with two switch selector commands which energize
relays K23 and K36 (drawing 7.1.1). These commands operate
in conjunction with relays K92 and K93 which are driven
from the S-IVB Main stage Thrust OK switches to provide 28
Vdc to the S-IVB Burn Mode circuitry. This configuration
is used to provide redundancy in achieving S-IVB burn and
S-IVB coast configurations. The FCC is configured for the
S-IVB Coast Mode by the removal of the 28 Vdc to the S-IVB
Burn Mode circuitry. This is accomplished with two switch
selector commands which reset relays K23 and K36 with the
S-IVB Thrust OK switches operating to back up these switch
selector commands.
Spacecraft Control Mode is achieved by command from the
spacecraft. The spacecraft can assume control during
S-IVB coast only.
C. The vehicle control requirements are different during the
various phases of flight. The function and characteristics
of each mode follow.
7-5
*
1. S-1C Burn Mode (Drawing 7.2.2)
SLY AS-503
The function of the control system during S-1C stage
burn is to maintain stable aerodynamic flight. The
FCC accepts attitude error signals from the guidance
system (LVDC/LVDA) which are obtained from a time-tilt
guidance program. Attitude rate signals are input from
the control signal processor which conditions the out
puts from the control EDS rate gyro package for use by
the FCC. These attitude error and rate signals attempt
to maintain the vehicle in a zero angle-of-attack attitude.
Filters are included in all of these signal channels to
control the effects of vehicle bending and fuel sloshing
on the control system, to control the effects of sampling
rate and quantitation of the attitude error signals, and
to maintain proper control system stability. The gains
of the attitude error and rate signals are controlled
with switch selector functions known as Flight Control
Computer switch points.
2. 8-11 Burn Mode (Drawing 7.2.2)
The function of the control system during S-11 stage
burn is to dlrect the vehicle along the desired guidance
trajectory. The attitude errors are obtained from an
active guidance program which begins just after LE8
tower jettison. The attitude rate signals used are the
same as described above for the S-1C stage. A different
set of filters are used in the control signal channels
because the vehicle dynamic characteristics have changed
with the jettisoning of the S-1C stage.
3. 8-1VB Burn Mode (Drawing 7.2.3) (Figure 7.1)
The function of the control system during S-1VB stage
burn is to direct the vehicle along the guidance tra
jectory. The attitude error and rate signals are the
7-6
SLY AS-503
same as described above for the S-11 stage. A different
set of filters is used because of the change in vehicle
dynamic characteristics with the jettisoning of the
S-11 stage. There is only one engine on the S-1VB
stage so attitude control in the roll axis is not pos
sible. Roll control is achieved with the auxiliary
propulsion system (APS) during S-1VB burn.
4. S-1VB Coast Mode (Drawing 7.2.3) (Fig 7.2 and 7.3)
The function of the control system during the S-1VB
Coast Mode is to establish and maintain the desired
vehicle attitudes in the pitch, yaw and roll planes.
The inputs to the FCC are attitude error signals from
the guidance system and attitude rate signals from the
rate gyros. The FCC spatial amplifiers convert these
analog inputs into variable width and frequency pulses
which are suitable for the APS. The APS englnes are
fired whenever the summation of attitude errors and
rates fall outside the OFF zone of the pseudo-rate
modulator curves, figures 7.4, 7.5, 7.6. The control
system can be directed to perform attitude maneuvers
during orbital coast by the guidance system by means
of the attitude error commands. No filters are required
for S-1VB coast as the vehicle bending and fuel sloshing
effects are negligible during orbital coast. The purpose
of the OFF zone or deadband for the APS is to prevent
overcorrecting the vehicle's attitude which would result
in excessive usage of the APS propellants. A schematic
of the auxiliary propulsion system showing temperature
and pressure measurements may be found in Section 8 of
this handbook.
7-7
*
Spacecraft Control Mode
SLY AS-503
The function of the control system during the spacecraft
control mode is to respond to the attitude error com
mands from the spacecraft. The inputs to the Flight
Control Computer are the attitude error signals from the
spacecraft and attitude rate signals from the rate gyros.
The spacecraft attitude error signals replace the guidance
system attitude error signals and are used in an identical
fashion as the guidance system during S-IVB coast mode.
The spacecraft attitude error signals are limited to a
predetermined limit by the FCC.
7-8
o
4
3
2
1
c
NOTES:
1. ALL SIGNAL ARROWS INDICATE POSITIVE VEHICLE MOVEMENTS.
2. VEHICLE PITCHES OVER POSITION 1.
3. ENGINE ACTUATOR LAYOUTS SHOWN AS VIEWED FROM AFT END OF VEHICLE.
4. DIRECTIONS AND POLARITIES SHOWN ARE TYPICAL FOR ALL STAGES.
5. + ~ INDICATES ENGINE DEFLECTION REQUIRED TO CORRECT FOR POSITIVE VEHICLE MOVEMENT
6. CG = CENTER OF GRAVITY F NOZZLES ON EXT = ACTUATOR EXTENDED RET = ACTUATOR RETRACTED
~ = THRUST VECTOR ANGULAR DEFLECTION
m
S-J: AND S-I[ACTUATOR LAYOUTS
m
I[t----
YAW AXIS
B
S-IV8 ACTUATOR AND SPATIAL THRUSTER LOCATIONS
S-IC AND S-I[ POLARITY TABLE
ACTUATOR SIGNAL AND ACTION NO.
+~R +~Y +~P
l-Y RET RET I-P EXT RET 2-Y EXT RET 2-P RET EXT 3-Y RET EXT 3-P EXT EXT 4-Y EXT EXT 4-P RET RET
,-.----INSTRUMENT UNIT
SPATIAL THRUSTERS
S-IVB STAGE
S-IVB POLARITY TABLE
REVISION
ACTUATOR SIGNAL AND ACTION NO. +~R -~R +~Y +~P
l-Y EXT I-P RET
THRUSTER NO IIV F Ip
lIT F
mIT F illp
ill IV F
CONDITIONS DURING COAST
~R -~R +~Y -~Y +~P -~P
IIV F F Ip F II[ F F
illIT F F illp F illIV F F
APPROVAL
PHYSICAL AND FUNCTION RELATIONSHIP OF THE SATURN V CONTROL SYSTEM COMPONENTS
1-_.,;.,.:.."...,...;..:.".,:.::.."._+D_A_T-jE NATIONAL AERONAUTICS & SPACE ADMINISTRATION DR :;~~3 MANNED SPACECRAFT CENTER HOUSTON, TEXAS
SATURN 1Z: CONTROL SYSTEM APP
J.!F~E~C~f~::~=~~h~S~L.;~Vrn~ SIZE DWG. NO.
j.; AS503 C 7.2.1 22 x 17 PAGE 7-9 SHEET OF
4
3
2
1
4
3
2
H
LVDCJ$W SEL GAIN CONTROL SWITCH POINTS 1 AND 2S-IC SWITCH POINTS 3 AND 4 S-II
• • • •
• •
G
i ~H CSP ¢, P 1-1 -!.L---------------<~>_-_:_--~o_?
• 1 "---_-----j
• I • I
K2-1
! rJ" CSP ;yl-I-~-------------~~>_-~--~~ . , .. ~--~ • I I • I I K2-1 · U I i ~1-1 I
CSP $RI-I--II-------------------------~-~--~,----
S-IC BURN OWG 7 1 1
LVDA IjI P
• • • •
~~~:~TUDE ---lII--~
LVDA IJI V
~~~:~TUDE --ii---"
LVDA 1ir R
~~~:~ITUDE ___ --~
PICKED AT LJO TO END OF S-IC BURN
PICKED DURING S-IT BURN ONLY
K2-1
F E • D
TO ALL PITCH SERVO AMP
TO ALL YAW SERVO AMP
TO ALL SERVO AMP
S-IT
DPIAO-17J07-03
TO ALL PlTCH SERVO AMP
TO All YAW SERVO AMP
TO ALL SERVO AMP
S-IT
..
c
ENGINE ACTUATOR SERVO AMPLIFIERS
8r-;-r+--~ ~
B APPROVAL
~~: f--:---~~~~!---7-~'~--------~-K-,~,
iL_-...::K:.rb-+: _·_::.-_S::.-_=IT~ _____ -~-~ TO ACTUATOR CONTROL VALVE ENG IP
Kl : .......... $-IC IS-II
~~~~~4_~_i~-------+------------~1 FROM ACTUATOR TM POT K2 I ~ S-IC
iY ~bY >-----~:--=-1~--;rf:~ I >-----/, ~_ L. __ K_2-+-___ S_-_IT______ :," TO ACTUATOR CONTROL VALVE ENG 1 Y G2-1Ql,GB-201 ~ K~ "'---+- S-IC
I $-II ~_'!_.~~~+-!---!!-----_;:-----------C...,I FROM ACTUATOR TM POT
K2 J ~ $-IC I 1 I
~---~~--~--~ : iL_-,K.::2:...L: _._::.-_-'-S.::-IT'-_____ -<~ TO ACTUATOR CONTROL VALVE ENG 2P
J Kl : ......... S-IC :: 1-: $_R __ -I
I S-II ~~~c;~_l_-;-_ii_----_i_----------.(yll FROM ACTUATOR TM POT
K2 I "'-- S-IC
~~ 1 :
$ V 2V >-----.-!--~---<ir-y I 1 L_-,K:::2:...L :' _ ~t_-_-=.S-_=IT'-______ _(~ TO ACTUATOR CONTROL VALVE ENG 2Y
G2-1~02 I Kl ~ ......... S-IC
I I S-If ~~~~~~~-ii---------T_--------------------~~I FROM ACTUATOR TM POT
K2 I A...-.... S-TC
:: :l-o_R ______ -1
-------;~~~~~ lL_--.::K::2-+: _t __ -_.:S.:-IT=-______ -<>oJ.> TO ACTUATORCONTROL VA1.VE ENG 3P
I Kl; ............ s-rc
~~~~'"-_l_-!---!~------+-------------<>-'(I FROJ~TUATOR TM POT K2 : A......-- 5-IC
~V I
~ : iL_--=K::2C-'-1 _t-'. __ S:..-II=-_____ ---<~ TO ACTUATOR CONTROL VALVE ENG 3Y
Kl : ~S-lC ~G2-r03;G8:203 •
I 5-n ~.:!!!~~-_I_T__;i_----+-----------o-,.1 FROM ACTUATOR TM POT
K2 1 ~ S-IC
~~PR :~R :e ~[?p ~----+---<' . ~ ~ 1 iL_-"'::K::~--t-: _t..-:.=-_S::.-_=IT~ ______ -<J> TO ACTUATOR CONTROL VALVE ENG 4P 1---------1 G1-~204 ~ I ~ S-IC
I Kl I 5-If : I FROM ACTUATOR TM POT
I K2 : "'--- S-IC
~V: ~b I 1 OV 4V ~---------;.r-~~,---~~ I .; R 1 i. __ ,-K.::2~_t-, ___ S_-_IT ______ _(~ TO ACTUATOR CONTROL VALVE ENG 4Y
~ R G2-~04 - K1 1 "----- S-IC
1 S-IT ~.:!!!~~~+~-II-----------------o-~ FROM ACTUATOR TM POT
K2 ~ S-TC
1-_...:S:.:IG=N...:A...:TU=R=E:,S_-1f'D...:A:..:T.::E~ NATIONAL AERONAUTICS & SPACE ADMINISTRATION MANNED SPACECRAFT CENTER HOUSTON TEXAS
SIZE DWG No..
D 7.2.2 PAGE 7-10 SHEET 1 OF 1
4
3
2
3
2
G F
r------,----!:~:----tt--~ 28 VDC TO ALL CIRCUITS
~p 8
>-----l----Jt>>----~"------, ~ I I I I
CSP ¢,V • • • • •
"'~clsl ; S-ICIS-I! • DWG711.
LVDA W •
~~~:~ITUDE 1-,' __ -!: __ ~+ • • • • • • • lVDA lJrY
~~~:~TUDE /-' __ -1-__ +"
LVOA \jIR
~~~:~ITUDE "--.r--
• S-IVS BURN • OWG 7 1 1 • • • • •
I I 1 I 1 I I I
8 • .~ • • Sit CONTROL • OWG 7 1 1 • • • • •
MSC Form 181G D (REV OCT 65)
I 3
K2
"R C> ~L8
~p 9
K2
~p (0
KiJ
~p 2
9 ~p
';y
~R
vY
~R
E • S~IVB SERVO AMPLIFIERS
S-IVB 3
S-IVB 3
S-NB 3
S-IVS 3
PITCH SPATIAL AMPL
~p
~p
,"y
~+
~-
3
R-Yn SPATIAL AMPL
~+
~-
3
+p
-p
+Yr -R
+R, -Y
•
o
TO J2 ACTUATOR CONTROL VALVE {PITCH}
TO J2 ACTUATOR CONTROL VALVE (YAW)
c
,
DC ANALOG ERROR INPUTS (Ijt)
DC ANALOG RATE
INPUTS (4))
SIGNAL TO FIREIp AP$
SIGNAL TO FIREmp APS
SIGNAL TO FIRE I, IT AP$
SIGNAL TO FIRE It IV APS
SPATIAL AMPL 1 (REF)
LIMIT SENSING
NETWORK
(DETERMINES POLARITY OF SIGNAL AND ESTABLISHES DEADBANO)
INPUT (POLARITY 1 AND 2)
SPATIAL AMPL 2 (CMO) INPUT (POLARITY 1 AND 2)
SPATIALAMPL 3 (SPARE) INPUT (POLARITY 1 AND 2)
SIGNAL TO FIRE mt II APS
SIGNAL TO FIRE mt IV APS
B
SPATIAL AMPLIFIER
RELAY PULSE WIDTH DRIVERS ANO - FREQUENCY -- (PROVIDES
DETERMINING SIGNAL TO CIRCUITS RELAY
PACKAGES)
COMPARATOR
PULSE PULSE
SHAPING AND r- COMPARE
COINCIDENCE CIRCUIT
CIRCUITS (AMPLITUDE AND TIME)
RELAY AND CONTACTS ARE REDUNDANT
- I-
t- I-
APPROVAL
DISCRETE OUTPUT TO RELAY PACKAGE VIA COMPARATOR (POLARITY U
DISCRETE OUTPUT TO RELAY PACKAGE VIA COMPARATOR (POLARITY 2)
PNO I COMPARE POLARITY
1 AND 2 OUTPUT TO RELAY PACKAGE (PROVIDES SIGNAL TO
I RELAY
.. I I
FIRE JETS)
FLIGHT CONTROL COMPUTER FUNCTIONAL SCHEMATIC
S-IVB BURN AND COAST DWG NO.
7.2.3 34 X 22 SHEET OF
4
3
2
7.3 CONTROL SYSTEM REDUNDANCY
A. Control EDS Rate Gyro Package
SLV AS-503
There are three identical gyros in each of the three axes
sensing the vehicle's attitude rates. Two of the three
output signals for each axis are compared in the control
signal processor. If the two signals agree within prescribed
tolerances, one of these signals is used in the FCC. If the
two signals are not within the prescribed tolerance, the
signal from the third gyro is sent to the FCC.
B. Flight Control Computer
1. S-IC and S-II stage circuits
The S-1C and S-II stages each have five propulsive
engines, the outer four of which can be gimbaled in
the pitch and yaw axes by two hydraulic actuators at
each engine. Each actuator is driven by a servo
amplifier within the FCC. These circuits are not
redundant but backup is provided by the fact that
there are four individual actuator loops for each
axis. Should one actuator loop fail, the other
three loops in that axis will compensate with larger
excursions since the total vehicle movement is being
sensed and fed back to the FCC via the rate gyros
and stable platform. Mechanical feedback is used
in both the S-IC and S-I1 actuator servo loops.
2. S-IVB Burn Circuits
All circuits in the FCC used for S-IVB Burn are redundant.
Each of the three attitude error and rate inputs is
divided into three separate channels which exist up
to the servo amplifier comparator. A comparison of
two of the three channels is made and one of these
signals drives the actuator if the comparison is
satisfactory. If the comparison is unsatisfactory, 7-12
* SLY AS-503
the third channel is used to drive the actuator.
Mechanical feedback is used in the S-IVB actuator
servo loops. The roll axis is handled in the same
manner except that spatial amplifiers and comparators
are used with the output driving the APS relay packages
rather than an actuator.
3. S-IVB Coast Circuits
All circuits in the FCC used for S-IVB Coast are also
redundant. Each of the three attitude error and
rate inputs is divided into three separate channels
which exist up to the spatial amplifier comparator.
A comparison of two of the three channels is made
and one of these signals drives the APS relay package
if the comparison is satisfactory. If the comparison
is unsatisfactory the third channel is used to drive
the APS relay package.
7-13
SLV AS-503
7.4 CONTROL SYSTEM GENERAL NOTES
A. Flight Control Computer
B. Control Signal Processor
C. Engine Actuators S-IC S-II S-IVB
1. Max Engine .:.5. 17° .:.7.29° +7° Displacement
2. Max Actuator 5°/sec 9.6°/sec 8°/sec Drive Rate
D. APS Pitch Yaw Roll
1. Deadband +1.0° +1.0° +1. 0°
2. Maneuvering 0.3°/sec 0.3°/sec 0.5°/sec Rate Ledge
3. Engine Thrust 150 Ib 150 Ib 150 Ib
7-14
H
4
3
2
Mse Fonn UilG 0 (REV OCT "5)
G
r------.. I I I I I I I I
I ~I~--~~~ I I I I I I I I I I I I I I I I I I EDS I DISTRIBUTOR I I I ~1~--l2~~ I I I I I Ii-I I I I I I I I I I I I I I I I I I I I I I I I
I I I I
I I I r-I
I I I I
t L _______ I
RATE SWITCH J
-l RATE SWITCHj
j RATE SWITCH J
J RATE SWITCH J
F
r-------., I RATE GYRO I I PACKAGE : I I I I
PS3-26 V
PSl-26 V
PS2-26 V
i I S-: PS3-26 V I I I I I I I I I I I I I I ! ~ DEMODULATOR..r l.
1R GYRO '\ I .J PSI!60 V I i PSl'..26 V
~ DEMODULATOR-I I I
1R GYRO J : j P52!60 V : I PS2-26 V
~ DEMODULATOR -.l 1 -{" GYRO j I
J PS3~60 V I PS3:26 V I L ________ J
E • o
COMMAND COMPARISON
CIRCUIT
REFERENCE
28 vac bDll
SPARE COMPARISON
CIRCUIT
COMMAND
~~4V,DC --~L ___ _ --- ----VR12-602~ VR15-6D2
{ ROLL RATE j [ROLL RATE j \" ±Ioo/SEC,J \ ±loo/SEC .J
0l'!!!Q::!!!:-IO OPIAO:l,.4-IO
~ ~ , COMMA'D ~
~
REFERENCE COMPARISON
CIRCUIT
SPARE
28 VOG 6031
•
$P
;Y
---VR25-602
COMMAND rOj 1 SPARE 5/0 , 0 OR 28 VOCJ 6'PIAO-17JIO-Ol
~ ;R ....
28 VDC
REF INPUT
c
TO FLIGHT CONTROL COMPUTER
TO FLIGHT CONTROL COMPUTER
TO FLIGHT CONTROL COMPUTER
COMMAND INPUT --1I-~P-1
SPARE INPUT --11--------:-: UIT COMPARISON CIRC
B
ENERGIZES AT PRESET INPUT DIFFERENCE 1 6S"jSEC
TO Fe c
TR DR ENGR
& SPACE ADMINISTRATION DATE NATIONAL AERONAUTICS HOUSTON, TEXAS ~"""'';::~T.;::::::::--t;:;~ MANNED SPACECRAFT CENTER
CONTROL SIGNAL PROCESSOR
BLOCK DIAGRAM
4
3
2
8.1
8.1.1
SECTION 8
PROPULSION AND STRUCTURES
S-IC STAGE
Propulsion and Structures (General Description)
SLV AS-503
The S-IC is a cylindrical booster 138 feet long, 33 feet in
diameter, and has a gross weight at liftoff of approximately
4.7 million pounds. The stage is powered by five F-l rocket
engines, each developing 1.5 million pounds of thrust. One
engine, mounted on the vehicle longitudinal centerline, is
fixed. The remaining four engines are mounted equidistant
on a 364-inch diameter circle about the center engine and
are capable of being gimbaled through a plus or minus 5°
square pattern for thrust vector control. During the boost
period, the five F-l engines consume approximately 4.3 million
pounds of propellants, LOX and RP-l.
The F-l engine is a single-start, turbopump-fed, fixed-thrust,
gimbaled, bipropellant, liquid rocket system. The engine has
a single bell shaped thrust chamber with expansion ratio of
16:1. The thrust chamber is regeneratively fuel cooled through
the 10:1 expansion area tubular walled construction. An exten
sion nozzle is used to increase the expansion area from a
ratio of 10:1 to 16:1. This expansion nozzle is cooled through
an inner wall by exhaust gases from the engine pump turbine.
The propellants are stored in separate containers in a tandem
arrangement with the LOX tank on top. Both tanks are cylin
drical structures closed at each end by an ellipsoidal bulk
head. The LOX and RP-l tank volumes are 47,000 and 29,000
cubic feet, respectively. Anti-slosh and anti-vortex baffles
are provided in both tanks. Inflight pressurization is pro
vided for maintenance of the required pump inlet pressures.
The S-IC instrumentation system provides the capability for
measuring approximately 900 stage performance parameters.
8-1
8 PROPULSION AND STRUCTURES
SLY AS-503
The signals collected from individual transducers and sensors
are processed onboard and transmitted to the ground by six
separate telemetry links. The telemetry links include three
PAM/FM/FM, two SS/FM and one PCM/FM. The signals are radiated
over four antennas. The PCM system is also used for direct
wire ground telemetering of digital data acquisition system
(DDAS) measurements.
Other systems aboard the S-IC include eight retrorockets for
retarding the stage during S-IC/S-II separation, an emergency
flight termination system which accomplishes engine cutoff
followed by tank rupture for propellant dispersion, and elec
trical power distribution system, and flight control system
components which execute steering commands issued by the instru
ment unit.
As a result of a pogo type instability during S-IC boost on
the AS-502 vehicle, a helium LOX prevalve cavity pressuriza
tion system has been added to the AS-503 S-IC stage. The
system is proposed to decrease the likelihood of a pogo oscil
lation by injecting helium into the LOX prevalve cavity of
each engine such that the cavity acts as a vibration damper,
thereby lowering the natural frequency of the LOX liquid column.
8-2
ACTUATOR POSITION FEEDBACK
SERVO AMPLI FIER
" ~ ENGINE COMMANO--", TORQUE SeRVO
V Be MOTOR VALVE
I ,
-
Dr FFE RENTI AL PRESSURE FEEDBACK
Thrus t ..
I 1-
ACTUATOR POSITION . ACTUATOR
;(
I ~
- - -
ENGIfJE DYNAMICS
TELEMETRY
SLV AS-503N
ENGINE POSITION
B
FIGURE 7.1 7-16
II ---
III
I
VIEW LOOKING FORWARD
IIV =1=1-1
Ip = 2 = 1-2
III =3=1-3
IIIII = 4 = 2-1
II Ip = 5 - 2-2
IIIIV = 6 = 2-3
VARIOUS ENGINE NOMENCLATURE
Auxiliary Attitude Control System Engine Orientation
SLV AS-503N
IV
FIGURE 7.2 7-1'7
e VEHI CL[ ATTITUDC '!---'
SLV _ AS-503N
------.., r - PsEUDD RATE HODULATOR I
I 5J~ l I I h(t) 0 ;ll I ! I I
\1 C(t)I_E I ,I ! Eo . I MINrr~UM PULSE I ~---- --<:)-, DURATION DEVICE I
I • I i I 'J' I I I !
I ! I ~, I K ~!i ~! l'!.1 t) I f i i ".i,;l I T fS + 1 I L..:..J
1 _________ J ! I I , i I I'
CONTROL
TORQUE ENGINE THRUST, VALVE CHARACTERISTICS,I l~
RELAY AND SOLENOID
CHARACTERISTICS I TRANSPORT TIME DELAY I ETC.
l\LL DISTURBANCE
LO~QUE=_
Auxiliary Attitude Control System Schematic
I
FIGURE 7.3 7-18
MANEUVERING RATE LEDGE
-4
ON ZONE
-3
t PROGRAMMED
.p LIMIT ON ZONE
PITCH AND YAW AXES DURING S-IVB COAST PHASES
J DEG/SEC
+0.5 ----------0.32 DEG/SEC
-- - -------0.2 DEG/SEC
.p DEG 4
MODULATED ZONE
o lD
APS Pseudo-Rate Modulator Characteristics
SLV AS-503N
FIGURE 7.4 7-19
Maneuvering rate ledge
-4 -3
t Programed '" limit
On zone
On zone
<I> deg/sec
Figure 7-5 7-20
I
1.0 deg
0.32 deg/sec
0.2 deg/sec
Pitch and yaw axis APS
Pseudo - rate modulator characteristics
AS-503
SLY AS-503
IjI deg
4
Modu lated zone
" !., ...
Maneuvering rate [edge
On lone
¢I deg/sec
1.6 d ..
Figure 7-6
~d ..
Roll axis
APS pseudo-rate modulator characteristics
AS-503
Modulated 10110
>-en enr J,< o
'"
7.5 CONTROL SIGNAL PROCESSOR CHARACTERISTICS
Input Power required:
Rate Gyros Scale Factor Range
28 + 4 Vdc
Control Signal Processor Output Scale Factor Range
Comparison Circuit Switchover Point
Tolerance
EDS Rate Switch Parameters . ¢ YAW, PITCH
Activate point
. ¢ ROLL
Activate point
SLY AS-503
0.5656 V P-P/deg/sec ± 20 deg/sec 11.31 V. P-P
4.5 Vdc/deg/sec ± 10 deg/sec 45 Vdc
7.4 V Diff ± 1. 65 deg/ sec + 10%
+ 5.0o /sec + 0.55°/sec* + 3.0o /sec ± 0.55°/sec*
*¢ Yaw, ¢ Pitch activate points switched from ± 5°/sec to ± 3°/sec at liftoff plus 2:14.9.
7-22
H
8
7
6
5
4
3
2
G
,-______ 39(.00
SIll 691> 00 ___ -II!'-~.li" FUEL VENT LINE (ROTATED INTO VIEW,
5TII ll5 '''--'--+----'
E .. o
POSITION 4
c
TOP VIEW LOOKING AFT
" ,
BOTTOM VIEW LOOKING FORWARD
r----LOJ: RELIEF_2 PLACES(REF)
GOX LI~E TO GOX DIFFUSER (REF)
CAMERA_2 PLACES (REF)
_ ,,,,,,,,,,-~-STA 1476 .. 25 ACCESS.I)OOR 21 X 32 (73" 20 REF)
8
OSGN
"
'" -3
A
NATIONAL AERONAUTICS & SPACE ADMINISTRATION MANNED SPACECRAFT CENTER
PROPULSION S-IC STRUCTURE
SLY SEIZE DWG NO
AS-503 811 44X 34 PAGE 8-3 SHEET
8
7
6
5
•
4
3
2
*
8.1.2 Staging (General Description)
A. Subsystems
1. Exploding Bridge Wire Firing Units
SLY AS-503
Exploding bridge wire (EBW) firing units are used to
generate the high-voltage, high-energy pulse required
to initiate the electric detonators. Each EBW unit
consists of a high-voltage supply, an energy storage
unit, a trigger circuit, and a switching device. The
power supply uses 28 Vdc vehicle power to charge a
storage capacitor to 2300 volts. Upon receipt of a
signal, the trigger circuit actuates the switching
device which causes the storage capacitor to discharge
across the detonator.
2. EBW Detonators
The EBW detonators (one for each firing unit) are the
electrically activated devices used to initiate the
high explosive ordnance trains. When the high
voltage, high-energy pulse is applied to the bridge
wire element in the detonator, the wire explodes and
releases a large amount of energy. This energy ignites
a small quantity of chemical explosive, which, in
turn, detonates a larger, more powerful output charge.
This final charge detonates :the explosive ordnance
train.
No heat sensitive primary explosives are used and the
detonators are not sensitive to accidental application
of vehicle or ground power, static discharge, or rf
energy. A spark gap in one pin of the firing circuitry
prevents burnout of the bridge wire if power is
accidentally applied. This gap has a breakdown voltage
of 600 to 1200 volts.
8-4
8LV * A8-503
3. Confined Detonating Fuse
A confined detonating fuse CDF) manifold is used to
transfer the detonation from an EBW detonator to the
multiple CDF assemblies. The manifold consists of
a metal body with an EBW detonator located at one
end. A linear shaped charge (L8C) is installed in
a hole through the center of the manifold. A
detonation initiated by the EBW detonator will
propagate through the L8C and ignite each CDF assembly.
The CDF assembly consists of a low energy detonator
cord encased in a multilayered protective sheath. The
sheath is designed so that all explosive effects are
contained within the case.
4. 8-1C Retrorockets
Eight solid propellant 8-1C retrorockets are mounted
in pairs on the aft 8-1C stage structure, under the
four F-I engine fairings, and are used to retard the
8-1C stage after separation. Each retrorocket has a
burning time of 0.67 seconds and develops a thrust
of 92,375 pounds (vacuum thrust at 70°F). The thrust
level developed by seven retrorockets, with anyone
retrorocket out, is adequate to separate the 8-1C stage
a minimum of 6 feet from the vehicle in less than
I second.
Each retrorocket is ignited by either of two pyrogen
initiators mounted on its aft structure. The CDF
assemblies connect the pyrogen initiators to the
respective firing units, thus completing the ordnance
train.
5. 8-11 Ullage Rockets
Eight solid propellant 8-11 ullage rockets are mounted
at equal intervals around the periphery of the 8-11
8-5
*
interstage. The ullage rockets provide the positive
thrust required to settle the J-2 engine propellants
prior to engine start. With anyone ullage rocket
out, the remaining rockets are capable of maintaining
a minimum vehicle acceleration of 0.1 g during the
coast portion of S-ICjS-II separation.
Each ullage rocket burns for 3.25 seconds and develops
a thrust of 22,700 lbs (in vacuum). Two pyrogen
initiators are mounted on each ullage rocket and com
plete the ordnance train required for rocket ignition.
6. Linear Shaped Charge
The linear shaped charge is used to sever the vehicle
structure during separation. The explosive is designed
so that, when detonated, the force of the explosion
is focused along a line to provide the required cutting
action.
The detonator blocks complete the ordnance train to
accomplish physical separation. An EBW detonator
is mounted on each detonator block, thus linking
the block with the respective firing unit. Each end
of the LSC is attached to a detonator block either
of which can fire the explosive charge.
B. Operation
Physical separation is initiated by the Instrument Unit
(IU) at the end of S-IC boost phase, following shutdown
of the five F-l engine. Separation requires the performance
of the following major functions in the sequence described.
1. EBW firing units armed
A ground latched interlock renders the EBW firing
units inoperative while the vehicle is on the launch
pad. This interlock is released with umbilical disconnect
8-6
* SLV AS-503
during liftoff, and the sybsystem is reset to flight
condition. At approximately 9 seconds after inboard
engine cutoff the IU sends out the command to arm
the S-IC/S-II separation ordnance. The ordnance
arm command is routed through the S-11 switch
selector to both the S-IC stage electrical circuitry,
to supply plus 28 Vdc to the EBW firing units for
first plane separation and retrorocket ignition,
and to the S-II stage electrical circuitry to supply
plus 28 Vdc to the EBW firing units for ullage rocket
ignition and second plane separation. The firing
units use this energy to charge the internal storage
capacitors to 2300 volts to provide the firing
pulse for rocket ignition and LSC detonation.
2. S-IC engine cutoff
Cutoff of the center F-l engine is enabled by the
Launch Vehicle Digltal Computer at approxlmately
136 seconds after liftoff. The four outboard F-l
engines shutdown is enables at approximately
144 seconds after liftoff.
3. S-II ullage rocket ignition
Immediately following S-IC engine shutdown, the IU
initiates ullage rocket ignition. The slgnal is
routed through the S-I1 switch selector and the 8-11
electrical circuitry to trigger the ullage rocket
firing units. The internal storage capacitors
discharge a high-energy pulse, causing the bridge
wires to explode, releasing the energy required to
detonate the explosive charge. The detonation
propagates through the EBW detonators.
4. First plane separation and S-IC retrorocket ignition.
First plane separation is initiated immediately after
8-7
*
•
SLV AS-503
8-11 ullage rocket ignition at approximately 149
seconds after liftoff. The separation command is
routed through the S-1C switch selector to the S-1C
electrical circuitry to trigger the ordnance train
for first plane separation and retrorocket ignition.
The LSC, and in turn, the retrorockets 19nite to
separate the structure and retard the S-IC stage.
8-8
8
7
6
5
4
3
2
m COMMAND SEQUENCE AND CONTROL DISTR RESET
sw sa ll5AS
COMI.IANO S-IC/S-D
SEPARATIO .. 5S 157
CHAN 15
FIRING UNIT EBW I NOI
S-IC STAGE
H
'" COMMAND LIFTOFf
'H" COMMAND ARM ESW GROUND
RE'JRO AND SEPARATION ~ SS 143 CHAN 10
Kl20
t~ I'-----~ ~30-2
I
G
I EBW I FIRING UNIT NO 1
I DETONATOR I BLOCK NO 1
I EBW FIRJNGUNIT
N02
I DETONATOR BLOCK NO 2
I
FILAMENT
,L,-
1ST SEPARATION PLANE
EBW FIRING UNIT
NOI
E
m COMMANO SEPARATION CONTROLLER INHIBIT
o
~,~~ ____ -,!O_ - i ESE COMMAND SEPARATION RELAYS RESET
EBW FIRING UNIT
NO 2
...
r------- -------~
r----- COF CDF ::::=='i I ,---- MANIFOLD MANIFOLD -----, I I
r : i~:: NOl N02 ::~i : : : I I ,- --, I r I I I
I r ., I I I 1 I I 'I' I I I I I I I I I
I I I I I I I I I II :: L _______________________________ .J :::::::
I I I ______________________________________ ~ I I I , I I
: -':=-==~~-:--~~~~~oc:.:"-o~:-------------------~' -----~!!! i i , (3 REQDl r I I I
I II I II I I I I II
~ ________ f" _-_-_-~_-~_-_-_-_-::_-~~_-~::~_-_-~_-_-_-~~~~~:::;-- ---- -- J : : :
L _______ ~ ~-------J , :
S-D ULLAGE ROCKETS I I
C'" """~-" """"-" "'-"""'''''-~::::::::'j : i
, ,
""""""~""""""'c"""""""'-~::-:::::::'j
I S-IC/S-D INTERSTAGE
c 8
COMMAND S-UULLAGE
TRIGGER S5022
CHAN 24
COMMAND SoD SECOND PLANE
SEPAAATION S5042
CHAN 23
,. FIRI~~UNIT I NO 1
I DETONATOR I BLOCK NO 1
,~,
I
I
COMMAr.tO S-D ORDINANCE
"" 5511>3 CHAN 11
EBW FIRING UNIT
NO 2
DETONATOR BLOCK NO 2
U
FILAMENT
A
, , '----
2ND SEPARATION PLANE
• • • • •
MATI~AL AERONAUTICS " SPACE ADMINISTRATION
'" AUTH _
PROPULSION S-IC/S-n
SEPARATION SUBSYSTEM
SLY SIZE 812
55X 34 PAGE 8-9 SHEET 1 OF 1
8
7
6
5
4
3
2
*
8.1.3 RP-l Pressurization
A. Fuel Conditioning
SLV AS-503
Fuel conditioning is re~uired to prevent fuel stratifi
cation. At T-5.0 hours, GN2 bubbling is initiated by
opening a solenoid valve in the ground GN2 distribution
console and allowing GN2
at 150 psig to be injected into
the fuel suction ducts near the fuel pump inlets of
each F-l engine. Bubbling-is terminated when the fuel
tank prepressurization command is given.
B. Tank Prepressurization
Prepressurization of the fuel tank is re~uired prior to
engine ignition to insure the necessary net positive
suction head pressure at the engine pump inlets.
Prepressurization of the fuel tank is initiated at
T-l.5 minutes. The fuel tank vent valve is closed, the
ground GN2 bubbling valve is closed, and the ground
prepressurization solenoid valve is opened. Helium
flows from the ground helium distribution console,
through the umbilical connections, and into the fuel
tank. The fuel tank prepressurization switch is set
to actuate at 29 psia and deactuate at 27.5 psia. The
switch operates to close the ground prepressurization
helium valve when fuel tank pressure reaches 29 pSla.
Prepressurization is complete at approximently T-50
seconds.
c. Flight Pressurization
During S-IC powered flight, ullage pressure is maintained
by helium supplied from helium cylinders. Flight
pressurization is initiated at liftoff, at which time
the fuel pressurization valve in the manifold assembly
becomes operative. The opening of this valve allows
helium to flow from the helium cylinders, through the
8-10
* SLV AS-503
engine turbine exhaust heat exchangers where it is heated
and expanded, and into the top of the fuel tank. Action
of the fuel pressurization valves maintains the ullage
pressure between 24.2 psia and 26.0 psia. The following
pressurization valve sequence is programed and is based
on predetermined helium requirements as a function of
flight time.
l. Valve No. 2 is opened at 49.5 seconds from liftoff.
2. Valve No. 3 is opened at 95.3 seconds from liftoff.
3. Valve No. 4 is opened at 133.5 seconds from liftoff.
Valve No. 5 operates independently and is controlled by
the fuel tank pressure switch which operates at pressures
between 26 and 24.2 psia. Its function is to supply
additional fuel tank pressure if helium demands are
greater than can be provided by the other four valves.
The fuel tank vent and relief pressure switch is set to
operate between 31.5 psia and 29.7 psia. Its function
is to keep the fuel tank pressure from exceeding the
maximum operational level by causing the fuel tan~, y;~;t valve to open, thus venting excess ullage pressure.
8-11
•
8
-
7
-
6
-
5
4
3
2
H I
CMO HE FLOW CONTROL VALVE NO SOPEN
K115
.;~ 28 VOC
'" RESET
G I
LOX PREVAt..VE CAVITY
LOX FlLlAND DRAIN UHf NO 3
~U'""U
COMMAIID FUEL PRESSURIZING
VALVE NO 4 OPEN
'" CMO HE FLOW CONTROL VALVE 1104 OPEN
1011
F I
,.,~\ ~::l-' PP:lSS HE SUPPLY
\o-3~0;S1A J
r ~.-l:=:! '''''y-''~'-'' .-l:=:!
r ~;'l:=:!
'" "'"
sw sa m~
COMMAND FUEL PRESSIJRIZING
VALVE ~O 3 OPEN
SS 055 eHANb
T
'!~t~ It[ FLOW CONTROL VALVE NO 3 OPEN
E
-------~ PRESS HE SUPPLY
\ 0-:500 PSI!' )
""'"7""H'-"
COMMAND FUEL PRESSURIZING
VALVENOZ OPEN
SS 002 CHAN 5
-
'"
• LOX PREVALVE CAVlTY PRESSURIZATION SOLENOID VALVES
'" -..{h
W ~ U
1011
CMO HE FLOW
"" RESET CONTROL VA,LVE NO 2 OPEN
D
HELIUM ~ .... EMERGENCY
~ DUMP
'" CMO HE FLOW CONTROL
,
I C
I
I HEUUM HI~H
PR!:SS5W ~ I 3110-3190 --=
,
0 S
"'
~,
~172-118'
PRESS REG 1M POGO HE HI ..
I
COLD H!:lIUM BOTHE
PR~~~~:~~UT I POGO HE 1M)
J-f~~~l AF:3A3-127 -12-05-00 0-300 PSIA
AF:3A312-~_lO_OO
HELIUM IIIJECTION VALVE
Cji.0L
POGO SUPRESSION HELIUMIWECTION REGULATION
1011
B
LOX TANK
COLO HEliUM COLO HEliUM BOTTlE SOTTLE
VALVENO{CLOSED .~ ZSWC GSE GSE
1~+-+---~~--~~~--+-~--~~4---~-+--+--r--~Ir---~~--------------~: . ~~ ® @ ® C9 ® <D h I I FUEL PREPRESS
1 ~104 .~. KI02 I I PRESS SW
~ , - 7 -- ----- ----- '- .... -- ---- ----- \- l=iTi~ ----- ----- I : FUEL FLIGHT : FUEL VENT : ~R~R~UNO K~O K~04 u~~ K:3 ~-b ~ K~02 : - : ~Ei_S2!WO i ~a~::~kE~s i ~~E;~~U~~~~t ~:;~GIZEO ---. t: _ _ i i i 29 5-31 PSli
'" ~
HE FLOW
I A
'" " ,~,
BOTTLE §7 NO 1 LOX SUCTION DUCT
NO 2 LOX SUCTION OUCT
NO 3 LOX SUCTION DUCT
NO 4 LOX SUCTION DUCT
OATE
LIFTOFF ~ I r..LllllLll.llL lID >4 ~~~~~J':'C K114 of K113 K112 : : I ""'";'" r;:Jllllllllll:rn::rn:~llllllllllllIIl!IlII[![;-]
LI ------- "" ------- "" 7 ------tL--.-::'''''''''------------E}------" _;:~ ;-~ 6, ~~ VALVE NO 1
7 K115
d_ r I
'" ~ HE FLOW
I VALVE NO 2 , , ,
, ~ ... " HE FLOW VA,LVE NO 3
-rl •
FUEL TANK (242 - 26 0 PSIA)
~152-1l7
PRESS FUEL TANK ULLAGE
0-45 PSIA APIA2-1-1-
HEOIFFUSER
ENGINE HEAT EXCHANGER
APPROVAL
'=c-=Y~r+~
r---fiI--I~ ~ ~ ~ ~ ... ",
HE FLOW VALVE NO 4
~ '" HE FLOW VALVE NO 5
[~mrIIIIllllllll]](-~lImlII~~ FUEL TANK PREPRESS
•
SIGNATURES DATE NATIONAL AERONAUTICS &. SPACE ADMINISTRATION
DR r'-/" MANNED SPACECRAFT CENTER -~~ OSCN e£-&-Z'..,I-O.. #""-! QC:m .,$6
"" '" '" ... UTH _
PRDPULSION S-I C FUEL PRESSURIZATION
SLV~SIZ:TDWG NO.
503 EI 813 SHEET OF
8
f---
7
6
5
4
3
2
*
.8.1.4 LOX Pressurization
SLV AS-503
The S-IC LOX pressurization and conditioning subsystem is
designed to pressurize and condition the oxidizer in the
S-IC stage tank to insure the availability of LOX at the
pressure, temperature, and density required by the LOX pump
inlet. The subsystem can be divided into three function
oriented areas operating at different periods as shown below.
The areas are as follows:
• LOX conditioning
• Tank prepressurization
• Flight pressurization
A. LOX Conditioning
LOX conditioning is necessary to prevent geysering in
the suction ducts and to provide the LOX pump inlet with a
uniform density oxidizer. The conditioning is accomplished
by both helium bubbling and thermal pumping. In order
to establish a path for thermal recirculation, the suction
ducts are interconnected as shown in the schematic. At
the start of LOX loading, the interconnect valves No.1
and No. 4 are in their normal positions and the emergency
bubbling valve is closed. The ground bubbling valve is
opened and ambient helium flows into suction ducts No. 1
and No.3. As the tank fills with LOX, two separate
thermal pumping systems are established in the LOX suction
ducts. One thermal pumping system consists of flow
down suction duct No. 3 and up duct No. 1 and the other
consists of flow down suction ducts No. 4 and No. 5 and
up duct No.3.
Helium bubbling is terminated when the LOX tank is about
6.5 percent full and thermal pumping is established.
When bubbling is terminated, thermal pumping becomes the
8-13
SLV * AS-503
means of LOX conditioning. However, should the thermal
pumping process be disrupted due to premature closure
of an interconnect valve or LOX prevalve, or if the
temperatures of the LOX in the suction ducts should increase
excessively, helium gas will be bubbled into all five
suction ducts. Should premature closure of the prevalves
occur, interconnect valve No. 3 will be opened and LOX
trapped below the outboard prevalves will be vented
through the interconnect valves No. 1 and No.4, and
up inboard suction duct No.5. LOX trapped below the
inboard prevalve will be vented through the bypass check
valve.
B. Prepressurization
Prepressurization of the LOX tank is required prior to
liftoff to provide the necessary LOX pressure at the
engine pump inlets.
Prepressurization of the LOX tank is initiated at T-72
seconds. Both LOX tank vent valves are closed and
bubbling through ducts No. I and No. 3 is terminated.
The ground prepressurization valve is then opened and
ambient helium gas flows from the ground supply and into
the LOX tank. The ground prepressurization valve is closed
when the prepressurization pressure switch senses tank
ullage pressure at 26.0 psia. Approximately 45 seconds
will be required for prepressurization. Engine ignition
at T-7 seconds will result in LOX consumption and ullage
pressure decrease. The prepressurization switch will
deactuate at 24.2 psia, thereby opening the ground
prepressurization valve and providing supplemental
ground pressurization until liftoff.
8-14
M
8
7
16
5
3
2
K H
ESE COMMAND
klOX VENT AND
KI2b RELIEF VALVE OlSABLE
, -UMBILICAL VEHICLE
,
~,,~,~",~.~,"~",~";,,~;---------------------------~'~.------~e---. ~X TANK PRESSURE t-1-----1 I ____________________________ ~ _______________ ,
lOX VENT AND 1 I ~ • :!~i\:.~,':: S,':'""'''i s:~""i h
I .;A +lOll If ~ 27 5 PSI'" If ~ 24 2 p:~:21 rr~'. 23 7 p:~:ll
29 0 PSI'" 26 0 PSIG 25 5 PSIG
AUTOMATIC CHECKOUT ~====:[)::~f.~--i-__'!_<t!><~=l:::::JF===========~ ,===:!.!::.. ~===:IJ LOXTA~PRESSURE SWITCHES
. !
LOX VENT AND RELIEF VALVE 24 0-25 5 PSIG
OVERBOARD 0 ~~
,
LOX TANK PRESSURIZATION (HELIUM)
~ ~F~IIII~ ~~======,~ ~~-~~~-===8-~~:~",~~l~ool'~'~oO
NO 2 INTERCONNECT VALVECQNTROl
LOX BUBBLING HELIUM
CONTROL VALVE I~ I I
TO ENGINES N02 3 4 AND 0 5 HEAT
EXCHANGERS gOI/DIEMGINE
'W EXCHANGER
o CO 01-- 0 FLOW "'HER
1,1 II n II H
:I
, ,
II
II ,
II ,
II
~153-119
PRESS LOX TANK ULLAGE
'i::" ,-NO~~ -
v 11_ d= E"'E~GENCY SUSSUltG VALVE
o 0 0 0
II
,
IIII , ,
II
[ [
PREVALVE CONTROL
LOGIC
[ T [ T
o
ESE LOX INTERCONNECT VALVE NO 9 CLOSE
ESE LOX ESE toIdMA/4) Ir;TERCONNECT LOX INTERCONNECT VALVE NO 3 VALIlES OPEN CLOSE
c
ESEl())( INTE~CONNECT VALVE NO 1 CLOSE
~ 1", r! ~ f ~,::" f',,::" f :,::" ~ f--=J ~
Ir -~ L~ L~ ),f - '-"I~ L, - "~"'l,::: "" i! "" rl, ~ ~ -~-~ ,
)1 HEINJ
-=- -=-: -=- : -=- : -=- -=-: -: - : I I I I I
, , N~~
II
':rr: HE INJ
II
II co
I I I I I
: : :: : I I I I
II
II
:rr: HEINJ
, , , , , ,
N~ ...
f []IITERC~ECT SUCTION DUCT NO 4 VALVE C4 PLACES)
o 0 0 0
SUCTION OUCT 1103
SUCTION OUCT N05
SUC1IONOUCT NO 1
II
k NC i -=-
NOZJt:==!
II
, , , , , , : : ,
N~~
!
, , , , , ,
, , , ,
.1. ~l-! _-
t·
o "'"" ,,",_:1 VENT CONT~OL
~g':;'~~~VtLVE ---====l.l-n-I
TOGNZ SUPPLY
RELIEF VALVE
PNEUMATIC MANIFOLO
B
SIGIIo\,TURES
m tiOIN>CN OSGIt o9I\..L
ENGR
A EltGR
DATE NATIONAL AERONAUTICS'" SPACE AOMINISTRAT10N
PROPULSION S-IC LOX
PRESSURIZATION
SLV AS-503
SIZE ()W(; N(I
J BI4 PAGE 8-l7 SHEET
8
7
6
5
4
3
2
*
c.
• •
Flight Pressurization
SLY AS-503
Flight pressurization of the LOX tank is required to
provide the necessary LOX pressure at the efgine pump
inlets. At engine ignition command, the turbopumps
begin to supply LOX to the LOX dome of each thrust
chamber. Some of this LOX is bled from the LOX dome
and passed through the heat exchanger where the turbine
exhaust heat converts the LOX to GOX. Some LOX is
bypassed around the heat exchanger through an orifice
in order to regulate the GOX temperature. As the engine
progresses into mainstage, each engine contributes to the
LOX pressurization system. The GOX flows from each
heat exchanger into a common pressurization manifold
containing a GOX flow control valve. This valve has an
adjustable minimum stop which insures a certain minimum
GOX flow and is designed to maintain LOX tank ullage
pressure at about 20.5 psia subsequent to liftoff. During
the time period between engine ignition and liftoff,
minimum flow occurs through the GOX flow control valve.
Until liftoff this flow is supplemented by the prepressuri
zation described above and the tank is maintained at
about 26 psia. After liftoff and throughout the flight,
the GOX flow control valve maintains LOX tank ullage
pressure at about 20.5 psia by modulating GOX flow
between an optimized range of 30 to 50 pounds per second
(with a maximum flow capacity of 70 pounds per second) •
The actual pres sur ant flow depends on the tank pressure
sensed by a reference pressure line connecting the valve
with the LOX tank.
Zero GOX venting during flight is the design objective;
however, should tank pressure venting be required, it
will be performed as follows:
8-15
* SLY AS-503
The flight vent pressure switch No. 1 will assure
primary control of tank venting until approximately
T+65 seconds. This switch, which actuates at 29.0 psia
and deactuates at 27.5 psia, will open the LOX tank
vent valve. As the vehicle gains altitude, the external
ambient pressure decreases, and between approximately
T+64 and T+75 seconds, either flight vent pressure switch
No. 1 or No. 2 may cause venting. Flight vent pressure
switch No.2 which actuates at 25.5 psig and deactuates
at 23.7 psig, will operate the LOX tank vent valve after
T+75 seconds when the external ambient pressure has
decreased to such an extent that flight vent pressure
switch No. 2 assumes primary control of the venting
operation, should venting be required. Should the pres
sure switches or solenoid valves which operate the LOX
vent valve malfunction, the LOX tank vent and relief
valve will mechanically relieve tank pressure between
25.5 and 24.0 psig.
8-16
*
8.1.5 S-IC Pneumatic Control System
S~
AS-503
Prior to pressurization of the 3000 psig (1.27 cu ft) GN2 storage sphere, the normally closed GN2 solenoid valve must
be in the open position. Ground supplied gaseous nitrogen
is introduced through a GN2 storage self-sealing quick dis
connect coupling, GN2 pressurization filter, and GN2 solenoid
valve into the sphere. The sphere is pressurized to approxi
mately 1500 psig prior to propellant tanking. Pressurization
to approximately 3000 psig occurs at T-30 minutes. The GN2 solenoid valve is closed shortly before liftoff and remains
closed throughout flight. Nitrogen flows from the sphere
through the pneumatic control filter and pneumatic control
regulator where the gas pressure is reduced to approximately
750 psi. Gaseous nitrogen then flows from the regulator to
the control pressure manifold which contains a pneumatic con
trol relief valve. The relief valve mechanically opens to
relieve overpressure if manifold pressure becomes excessive.
On the S-IC vehicle during flight, gaseous nitrogen flows
from the pressure manifold to three normally closed three-way
solenoid valves. Upon completion of an electrical circuit by
the actuation of the fuel tank vent and relief pressure switch,
the fuel vent and relief control solenoid valve opens to allow
gaseous nitrogen to open the normally closed fuel tank vent
and relief valve. Similarly upon completion of an electrical
circuit by the actuation of the LOX tank vent and relief pres
sure switch, the LOX vent and relief control solenoid valve
opens to allow gaseous nitrogen to open the normally closed
LOX tank vent and relief valve. Also, the helium fill control
solenoid valve is energized open to allow gaseous nitrogen to
close the helium fill shutoff valve.
8-18
* SLV AS-503
Gaseous nitrogen is routed from the pressure manifold to the
prevalve control manifold which feeds five 750 psig GN2 stor
age spheres. Each sphere feeds two normally closed LOX and
fuel prevalve control solenoid valves. The LOX prevalve con
trol solenoid valve, when energized, opens and allows gaseous
nitrogen to close the normally open LOX prevalve and flowmeter
assembly, and the fuel prevalve control solenoid valve opens
and allows gaseous nitrogen to close the two normally open
fuel prevalve and flowmeter assemblies. A fuel prevalve con
trol orifice is located in the line between the solenoid valve
and the fuel prevalves so the fuel prevalves will close after
the LOX prevalve, thus maintaining the desired fuel-rich
shutoff.
The GN2
storage sphere and purge sphere are pressurized simul
taneously from a ground source. Gaseous nitrogen flows through
the GN2 coupling and GN2 filter, then separates and continues
through the normally closed GN2 solenoid valve and the purge
system fill solenoid valve into the storage sphere and the
purge sphere, respectively. The solenoid valves are in the
open position throughout the countdown, but are closed prior
to liftoff and remain closed to isolate the two systems during
flight.
8-19
3
2
H G
TO FUEL TANK VENT AND RELIEF VALVE SOLENOID CONTROL VALVE
TO lOX TANK VENT AND RELIEF VALVE SOLENOID CONTROL VALVE
TO LOX TANK VENT AND RELIEF VALVE SOLENOID CONTROL VALVE
g~~ CONTROL PRESS t!-----e......,..-o-, ABOVE 2915 ± 60 PSIA I .. I I INDICATION I ,
GNZ I HIGH PRESS
F
-
ENGINE NO 1
ENGINE NO 2
ENGINE NO 3
ENGINE NO 4
ENGINE NO 5
-N
E
GN2
SPHERE 750 PSIG
GN 2 SPHERE
750 PSIG
GN2
SPHERE 750 PSIG
SPHERE 750 PSIG @N2
GN2 SPHERE
750 PSIG
N
D
-X TO FUEL PREVALVE .
~ FUEL PREVALVE CONTROL VALVE
-- -X TO LOX PREVALVE
~ LOX PREVAL VE CONTROL VALVE
-- -X TO FUEL PREVALVE
~ FUEL PREVALVE CONTROL VALVE
-- -XI N TO LOX PREVAL VE
~ lOX PREVALVE CONTROL VALVE
-- -X TO FUEL PREVALVE
~ FUEL PREVALVE CONTROL VALVE
-- -X TO lOX PREVALVE
~ LOX PREVAL VE CONTROL VALVE
-- -X TO FUEL PREVALVE
~ FUEL PREVAlVE CONTROL VALVE
-- -X TO LOX PREVALVE
~ LOX PREVAl VE SOLENOID CONTROL VALVE
-- -N J X N JIL TO FUEL PREVALVE
b FUEL PREVALVE ~ CONTROL VALVE
-c _
X TO LOX PREVALVE
~ LOX PREVALVE SOLENOID CONTROL VALVE
-
c B
r::Jr===tc=I><l===B:=:-=N:==- TO LOX N I N INTERCONNECT 'I..,..f" VALVENOI
~±-:--I LOX INTERCONNECT ~ 'Y CONTROL SOLENOID ~ VALVE
. ~:lC:==Jr=~x(~===N:=-=:J1:~ TO LOX X INTERCONNECT VALVE NO 3
LOX INTERCONNECT CONTROL SOLENOID VALVE
l 'I~Jr===tc::[>~:E==::1::-==B::- TO LOX ><. INTERCONNECT .y VALVEN04
~ LOX INTERCONNECT ~-:-. CONTROL SOLENOID t VALVE
N
A
--"~ ! SPHERE TM ,1 0K SWITCH PRESSURE
REGULATOR .,1 Il' [~:E==:J1:==Ji===N:==:lC:==Jr===tc==:::][:==:E==::tc==:::]==:J ~ NC ~ ~~~5_2975 ~50P51G "I I" INI '_"....,;S;.:'G:::NA::.T;.:U:;:R;.E;S-:-:-1j.:D::A:::T::.E-l NATIONAL AERONAUTICS & SPACE ADMINISTRATION r OR ~ J""&,,. IwzdI-A MANNED SPACECRAFT CENTER HOUSTON TEXAS
~~~~~OSLU~~~Y ~g]~mI:Jf~~1:::!~=:1~:::::i=llm~t~9<:]:: [::N.R:J[~ CON~TRO~L_~ PRES~SUJIR~E'~ MAN~IFO~LDl rlP~ GN2 FILL ~ ....,... Y HIGH PRESS ~
I ~CONTROL SYS OK SVvlTCH 7
_ LIFTOFF) GN2
CONTROL PRESS 1 i:;t' , + SHUTOFF VALVE {I 695 - 735 { . .III RELIEF
(CLOSED AT GSE ~SIA' \," VALVE
TO PURGE SYSTEM
- ABOVE715±20PSIA ~ ,IN INDICATION
TM ,bD~S~G~N~~~'~~~h<~~~~"~i~~r------QC S-<= "" ..l. • .t. ,,,,,,_,, PROPULSION
PNEUMATIC CONTROL SYSTEM S-IC
ENGRJ/.' .,/. J/ 1~-71 ~ , /1
APP (:i,.,~ _ ;
tF~E~Cd~~~=jl~~~u...~V~;~S~L~V SIZE
~ AUTO "_' -1S..- -8-'" f-'A:....:.:;S::-:-;:5,;.O~3tD7.:-!--::-:c:--___ ,-,::-;8"".I-;-.5---;",--I 34 X 22 SHEET OF
4
3
2
*
8.1.6 F-l Engines
A. General Description
SLV AS-503
Five F-l engines are used on the S-IC stage of the Saturn
AS-503 vehicle to provide thrust during first stage boost.
The five engines are similar, including interface connec
tions, however, the four outboard engines are gimbal mounted
for thrust vector control whereas the center engine is
rigidly attached to the thrust structure. Each engine de
livers approximately 1.5 million pounds of thrust. The F-l
is a single start, bipropellant engine using rocket pro~
pellant (liquid) (RP-l) for fuel and liquid oxygen (LOX)
for oxidizer.
The engine hydraulic system is an integral part of the
engine and uses RP-l as the hydraulic fluid during flight.
The fuel is bled from the high pressure side of the turbo
pump and is used to drive the engine positioning actuators
and various hydraulically actuated valves, and is then re
turned to the pump inlet.
Ground support equipment is required to start the engine,
but once started it is self sustaining. The F-l engine
system consists of a gas generator, a turbopump assembly,
a dual media heat exchanger, a thrust chamber, a nozzle
extension, a checkout valve, a four-way control valve, two
main LOX valves, two main fuel valves, a hypergol manifold,
a bearing coolant control valve, two pyrotechnic igniters,
and two thrust chamber pyrotechnic igniters.
B. Start Sequence and Mainstage Operation
The start of the F-l engines of the S-IC will be accom
plished in a 1-2-2 order with a minimum stagger timer of
0.3 seconds. The center (No.5) engine will be started
first, followed by the diametrically opposed pairs of the
8-21
*
other four engines.
SLV AS-503
At engine start, the checkout valve
moves to the engine return position. This transfers the
hydraulic fuel return from the ground line and directs
the return to the turbopump No. 2 low pressure fuel in
let. When the engine start command is received, the high
level (600 psia) LOX dome and gas generator purge is
initiated; the ignition stage timer is energized; and
the turbopump bearing heaters are de-energized. When
the pyrotechnic Igniter fuses burn through and the ignition
is detected, the four-way solenoid valve start solenoid is
energized. Hydraulic pressure holding the gas generator
ball valve, oxidizer valves and fuel valves closed is re
lieved and directed to the turbopump No. 2 low pressure
fuel inlet. Hydraulic filter and four-way solenoid valve
manifold is now directed to the opening ports of the
oxidizer valves and to the No. 2 sequence valve located
on and actuated by the No.2 oxidizer valve. The oxidizer
valves open and admit LOX into the thrust chamber. As the
oxidizer valves reach approximately 16 percent open, the
gates in the sequence valves are opened and hydraulic
pressure is directed through the No. 2 sequence valve,
to and through the No. 1 sequence valve, and to the gas
generator ball valve opening port. The gas generator
ball valve opens, propellants under tank pressures enter
the gas generator combustion chamber through the injector,
and the propellant mixture is ignited by the gas generator
igniters. The exhaust gas is ducted through the turbopump
turbine, through the heat exchanger, and out through the
thrust chamber exhaust manifold where the fuel rich mix
ture is re-ignited by the turbine exhaust gas igniters.
As the turbine accelerates the oxidizer pumps, the pump
dishcarge pressure increases and propellants at increasing
flow rates are supplied to the gas generator. Turbopump
8-22
* SLV AS-503
acceleration continues; and as the fuel pressure increases,
the bearing coolant control valve opens at approximately
225 psig and directs cooling fuel onto the turbopump shaft
bearings. When the fuel pressure increases to 375 + 30
psig, the igniter fuel poppet opens and allows fuel pres
sure to build up against the hypergol cartridge burst
diaphram. The hypergol diaphram bursts under increasing
fuel pressure, unlocking the ignition monitor valve poppet;
and hypergol fluid, followed by the ignition fuel, enters
the thrust chamber. When hypergolic fluid enters the thrust
chamber and contacts the oxidizer, spontaneous combustion
occurs and establishes thrust chamber ignition flame.
During initial engine operation, thrust chamber pressure
is transmitted to the sodium nitrite prefill and routed
through the checkout valve to the ignition monitor valve.
When the thrust chamber pressure increases to approximately
20 psig, the ignition monitor valve actuates and directs
hydraulic fuel to the opening ports of the fuel valves.
The fuel valves open; fuel is admitted to the thrust
chamber, and the gas generator fuel purge comes on. As
fuel enters the thrust chamber fuel manifold, 30 percent
of the fuel is routed directly through the injector to the
thrust chamber combustion zone. The other 70 percent of
the fuel passes through the thrust chamber tubes for cool
ing and then passes through the injector into the thrust
chamber zone. The thrust chamber pressure increases until
the gas generator reaches rated power (controlled by ori
fices in the propellant lines feeding the gas generator).
When engine fuel pressure increases above the ground source
fuel pressure, the hydraulic pressure source is trans
ferred to the engine and the thrust OK pressure switches
8-23
SLV AS-503
pickup. The engine is now at main stage. Main stage
continues until cutoff is given or caused by rough
combustion or low thru~t.
8-24
• •
8
-
7
-
6
-
5
4
-
3
-
2
-
SWITCH NO 1
SWITCH NO 2
I K I
'" @"~,,, SWITCH
'"
'"
>0,
LOX TANK
AlfTOMATIC CHECKOUT P~ESSURE S ...... TCHES THRUST OK
I I H I G 1 E I I D I c I
~~~~~~:~(:J:::X::::l1J=::!:~:l::::J'L::::X'::::]'C:::J'L::::l'::::J[::::X::::J'C::::X::::X::::JL::::l::::J[::::!::::1::::J[::::X::::JL::::X'::::]'C:~l SWITCH ...... 1N -!L..
~?3E!f~!g 5 _ NI~::J[::::!:::::J!::~ , ,I"::::JL::;-;:X::::]'C::::X'::;-] '"'"" '" c):::::x::::1:rJ ' r:I" '~
Lb PRESS COMBUSTION
r------------I"I---.--;~"~~~'~'~·~ PRESSURE N r-- N N
SWITCH N N N MANIFOLD I ,~
" ENGINE
'"
(
TOE'lGINES 134 AND 5
, - "*'
I MAIN
chT ~~EiET
PURGE . .,
-"r--__ ~"~:' ~ 1rII=Y' l) , ' -c --"-- "::::~~S;::::S::"':S::~ ::::::s~~» ~ '1-=
HI I e~~V( N
M M M M M M I M M M M M M M M' ...::IE]::I::" ..:::I:"', C! "~
" I, .- .....::.-. ~ , ~I!:IZ~I:~
1'1 1'1 1'1 1'1 II E1 • • • • • • • • • THRUST CHAMBER N PREFILL
~J'L:::~'::~]'C:~:'~::::J!N::::J'L::-' ~::J'L::::X'::::]'C:::J'!::::l'::::J''-1'1 1'1 1'1 1,1 I.~, II II
HYPERGOL PURGE
"., RETURN
N N NNNNNN
N N
[ MANIFOLD ~
, .~ ~ ,
FUEL JACKET PURGE
,.::r:;-t-ol
"::':~=E'=I~,
. , CHECKOUT VALVE
, , "
00
.....::.-'.£" •
lHRUST CHM1BER
---LJ...
-::x::::JNc::::xf----1::J:: 'FOUR WAY STOP SOLENOIO
ENGI~E CONTROL
.£I.::JO£I.::Jq VALVE
RJ_l SUPPLY
,
/'1 1./ .1
:L: , , , " , :::J::FOURWA.V
:~";J4::~::::L __ .J STOP .JL.. _ N SOLE~OID
•
B
-
~TUReINE r-==-' ~MUST ~IGNITORS
-r---r-_I -
I A LTt DR ENGR OAT(
'''' GENERATOR FUEL PURGE
• N I~'} r --=::::H'::::]'C::::'!:::::J!';-] , -I', '
I;::::;l
SERVO VALVE_T Il~~!~~~ ANDACTUATOR~
FUEL TANK
r 8 IY
" Er;GLNE
""
" ENGINE
""
_~ FUELPREVALYE
S
.If" LOX PREVALVE
S . E FUELPREVALYE
S
--~J:J[~::'!:~:l,::::J[::::H,::::][::~.!:::C:j:~ '''OOM~ , ~~~i LOX N
" . PURGE N N
1...],c=1:t:j:l:=:JN, -,--,-
SYSTEM
s~ r
• ••
'" GE"ERA.TOR VALVE
1"1 •• .::JMOM£lMI:1MC.MDM£JMl:lMI:.MOM£lMI:""~ •
"" EXCIIJUtGER N /SSEMBLY
I;::::;l
""·'''''',1 ~ ANOACTUATOR I t:.::J
FILTER MANIFOLD
B> ENG , SWITCH 1 SWITCH 2
K33-11S K:34-11S APlBO-19ROS-01 APIBO-L9R05-02
K3I>-1l5 K37-115 APlBO-19ROS-04 AP160-19R05-0S
K39-11S K40-115 APIBO-19ROS-07 APIBO-19R05-08
K42-11S K4b-1l5 APIBO-19R05-10 APIBU-19R02-01
K45-115 K4b-1l5 APIBO-19R02-03 APlBO-19R02-04
SWITCHES 1 AND 2 MONITORED BY FLIGHT CONTROLLER IN REA.LTII.IE
NOTES G> Er;G , , , , ,
MEASUREI.IENT
llEI<lOl 06-102 OS-103 OS-104 OS-IDS
TI.ICHANNEl
APIBOV07 10-00 AP160V0801-00 AP1BOV09-D3-00 AP160V09-04-00 AP1BO\llO-0/,-OO
APPROVAL
8
I-
7
-
6
-
5
4
I-
3
-
2
I---r.=- lURBINE ~ \ 'I I All k~_ T~::~:~~ I \ II !/ t I
l ______________________________ I. ___ ::::::::::::::::::::::::J:,,""::,,::~::::-'~~,,'_ __ ,,"__',,_''''"_''';~~::,;Ji::s~:; t~:::.J'.~'~'.'"" _______________ !!I..::"""'::"""'::'--""'''''''''::''''''''''''''''::'''~;.-:.::;;.-::;,l~!::.::.1:~~~:"!.'~!:..'::I~'!:;;lf:i-!l~ ___ ~~~~~~~ ~1r..\·~l:!':.~~~~~1:r;,::~"'::"" _______________________________________ Jl'·I!'!"!I~"!~!~!!'II;1~!~iI:~~~i~i~;·'i"~~~~·'i~!·'~'1'~~·~:;·~·';'~~~'~M:'~;":'.~:~~":Ml I
F N ~~~~ l fl r] J ~~~of~~~~~?:: ~~GN~ai'.a... v:" PROPULSION FI ENGINE 1 Sl::I:Y 'L ~ "" " MECHANICAL SYSTEM S-IC
_ .. PRESSURI2A.TIO~ APP i. I
I SYSTEM DRAW1NG FEC SLY jSIz:IOWGNO
"" - ",. AS-5031 J 1 8.1.6 S5 x 34 PAGE 6-25 SHEET OF ..
*
8.1.7 S-IC Hydraulic System
SLV AS-503
The four outboard engines, positioned by their respective
gimbaling systems, are used to control the vehicle during
S-IC boost. All four gimbal systems are identical, and each
gimbals an entire engine independently. During standby oper
ation, high pressure fluid (RJ-l) is supplied from a ground
source through the engine control pressure quick disconnect
coupling and the filter manifold to two servo valve actuators.
The fluid returns to the ground source through the checkout
valve and engine control pressure return quick disconnect
coupling. During engine operation, high pressure control
fluid (RP-l) is supplied from the No. 1 fuel discharge of the
turbopump assembly through the filter manifold to the servo
valve and actuators. The fluid returns through the checkout
valve to the No.2 fuel inlet of the turbopump assembly.
8-26
4
3
2
H G
SLEW FILTER ORIFICE ASS'Y
FI RST STAGE RLTER ORIFICE ASS'V
r---, j GIMBAL I SYSTEM ! RETURN
F
YAW ACTUATOR
PITCH ACTUATOR
E • D
*ENG
1 2 3 4
**ENG
1 2 3 4
**ENG
1 2 3 4
•
c
r---l
I G~~U~D I
r---'"
I F~iG~T I I SUPPLY I I SUPPLY I
L
SAMPLING VALVE
MEAS NO TM CHAN NO
016-101 APIAI-09-06-00 016-102 APIAI-09-07-DQ 016-103 APIAI-09-08-00 016-104 APIAI-09-09-00
MEAS NO TM CHAN NO
GI-lOl DPIAOV15-00-00 GI-I02 CPIBOVlS-OO-OO GI-I03 CPIGDV23-00-00 GI-I04 CPIBDV24-00-00
MEAS NO TM CHAN NO
G2-1Dl DPIAOV21-0D-OO G2-102 CPIBOV2S-00-00 G2-103 CPIBOV08-00-00 G2-1D4 CPIBOV09-00-00
B APPROVAL
j-------i TM
LEGEND
• • • RETURN
SUPPLY PRESSURE
1iii:~~:!1 CONTROL PRESSURE
1-:::::-":':::::;:':':;;'=;--+'7"-;:-:1 NATIONAL AERONAUTICS & SPACE ADMINISTRATION MANNED SPACECRAFT CENTER HOUSTON TEXAS
PROPULSION HYDRAULIC SYSTEM
S-IC SIZE DWG NO ..
D 8.17 PAGE 8-27 SHEET OF
4
:3
2
* 8.2
8.2.1
S-11 STAGE
SLY AS-503
Propulsion and Structures (General Description)
The S-11 stage measures 81.5 feet in length and is 33 feet
in diameter. It has a gross weight at liftoff of about 1.0
million pounds. The stage is powered by five J-2 rocket en
gines utilizing liquid oxygen and liquid hydrogen as pro
pellants. Each engine develops a nominal vacuum thrust of
approximately 200,000 pounds. The four outer J-2 engines are
equally spaced on a 210-inch diameter circle, and are capable
of being gimbaled through a plus or minus 7.30 square pattern
for thrust vector control. The fifth engine is mounted on
the stage center line and is fixed. During their burn period,
the engines consume approximately 930,000 pounds of propellants.
The J-2 engine is a high specific impulse (I ) engine fea-sp
turing a tubular wall, bell shaped thrust chamber with a
27.5:1 expansion ratio. Two independently driven turbopumps,
both powered in series by a single gas generator, supply LOX
and LH2 to the thrust chamber. The gas generator operates on
the same propellants as the engine.
The propellants are stored in an integral container. The LOX
and LH2 compartments are separated by a common insulated bulk
head. The LOX and LH2 tanks have volumes of 12,600 and 27,700
cubic feet respectively. The tank pressurization system is
designed to assure adequate propellant inlet pressures to the
turbopumps.
The stage instrumentation system transmits over 700 measure
ments to ground receiving stations for real time and postflight
vehicle performance evaluation. Six telemetry links are
employed: three PCM/FM/FM for relatively low frequency
measurements, two SS/FM for relatively high frequency measure
ments and one PCM/FM for digital measurements. The PCM link
is also used for ground telemetering by direct wire of DDAS
8-28
* SLV AS-503
system measurements required for automatic checkout. A tape
recorder is used to record certain S-II/S-IVB separation data
for playback.
Stage separation system components located on the S-II stage
include a controller for sequencing separation events, eight
ullage rockets to provide propellant settling during engine
start, and linear shaped charges which physically sever struc
ture at both separation planes.
Other systems aboard the stage are sensors for an emergency
detection system, a propellant recirculation system for chill
down of propellant lines, flight control system elements for
executing steering commands issued by the Instrument Unit, and
electrical power system and a flight termination system.
8-29
5
4
3
2
POSITION 4
RADIO COMMAND AND TRACKING
H
AID CONTAINER ----,t!r
TM CONTAINER NO 2
TM CONTAINER NO 1
POSITION 1
M$C Fo,m 1616 E (REV OCT 6S)
DESTRUCT CONTAINER
G
r~' STA 929 STA 823 -=t
STA 327
SIGNAL CONDITIONER CONTAINER NO 2
SIGNAL CONDITIONER CONTAINER NO 1
STA 866 00
."';'1'+-".-'''-- UMBILICAL ARM SUPPORT FITTING
ACCESS DOOR 30 X 36 50
F
STA 196
STA 848 75
STA 817812 STA 815.25
TANK FRAME
LH2 TANK PRESS LINE
LH2 TANK
WORK PLATFORM (REMOVABLE)
E
GAS DISTRIBUTOR
CONTINUOUS TANK PR(lBE-,
LOX LEVEL
LH2 RECIRCULATION SYSTEM
LH 2 FILL AND DRAIN
...
LOX VENT LINE
STA 345
o
LOX FILL AND DRAIN LINE
LH2 EMERGENCY SHUTOFF VALVE (S)
c
ENGINE NO 3
ACCESS DOOR 20 OOOIA BOTTOM OF BU LKHEAD
SIGNAL CONDITIONER CONTAINER NO 1
POSITION 3
r~~--f=~---t---ECPURGE
RECEIVER
MANIFOLD
ENGINE NO 2 ---,\I HEAT SHIELD
ENGINE SYSTEMS FLUID LINE ---
ELECTRICAL MAIN POWER CONTROL CONTAINER ----"~¥':&'-:;&'"
J2 ENGINE (5)
PLENUM CHAMBER AT 5TA 196 00 ----2:-~~
LH2 FILL AND DRAIN ___ 7
POSITION 2 ---,/
3650---'-'=.:..... 4220----~:::-
L02 PUMP SEAL DRAIN - __ __
STA 223 00
,STA341 00
B APPROVAL
LOX VENT FITTING AND FAIRING
ENGINE LOX LINE (5)
i>Oc,;.~---- ULLAGE ROCKET (8)
h':----",:-"\!,,----- SlGNAL CONOITIONER CONTAINER NO 2
\:<---'1-"1.---- INSTRUMENT CONTAINER NO 1
:,-,r'-;#'---- PROPOSED CAMERA LOCATION TYPICAL AT POSITIONS 1 AND :3
FLIGHT CONTROL CONTAINER
SYSTEMS TUNNEL (REF)
LOX FILL AND DRAIN LINE
It UMBILICAL ARM
LOX FILL AND DRAIN LINE
LH2 FILL AND DRAIN LINE
'-:-::-7::::-7-;-:".--+-::-,...,-:1 NATIONAL AERONAUTICS & SPACE ADMINISTRATION r DR MANNED SPACECRAFT CENTER HOUSTON TEXAS
PROPULSION s-n STRUCTURE
SLY SIZE
AS-503 J 44X2125 SHEET I OF I
5
4
3
2
8.2.2
SLY AS-503
Staging Systems Operation (General Description)
A. Second-plane Separation
To be supplied.
B. S-II/S-IVB Physical Separation
Physical separation is initiated by the instrument unlt
(IU) at the end of S-II boost phase, following shutdown
of the five J-2 engines. Separation requires the perform
ance of the following major functions in the sequence
described:
1. EBW Firing Units Armed
A ground latched interlock renders the EBW firing
units inoperative while the vehicle is on the launch
pad. The interlock is released with umbilical dls
connect during liftoff, and the subsystem is reset
to flight condition. At approximately 482 seconds
after liftoff, the IU sends out the command to arm
the S-II/S-IVB separation ordnance. The ordnance arm
command is routed through the S-II switch selector to
both the S-II stage electrical circuitry, to supply
plus 28 Vdc to the EBW firing units for S-II/S-IVB
separation and retrorocket ignition, and the S-IVB
8-31
SLV AS-503
stage electrical circuitry to supply plus 28 Vdc to
the EBW firing units for ullage rocket ignition. The
firing units use this energy to charge the internal
storage capacitors to 2300 volts to provide the firing
pulse for rocket ignition and MDF detonation.
2. S-11 Engine Cutoff
3. Separation
Separation is initiated at approximately 518.7 seconds
after liftoff. The separation command is routed through
the S-11 switch selector to the S-11 electrical circuitry
to trigger the ordnance train for separation and retro
rocket ignition.
Four solid-propellant S-11 retrorockets are mounted
at equal intervals on the periphery of the S-11/S-1VB
interstage structure and are used to retard the S-11
stage after separation. Each retrorocket has a burning
time of 1.54 seconds and develops a thrust of 34,810
pounds vacuum thrust.
Each retrorocket is ignited by either of two pyrogen
initiators mounted on its aft structure. The CDF
assemblies connect the pyrogen initiators to the
respective firing units, thus completing the ordnance
train.
The mild detonating fuse is used to sever the vehicle
structure during separation. Two trains of MDF are
installed in a groove in the aft skirt. A tension
plate riveted to the aft skirt and bolted to the aft
interstage joins these structures at the separation
plane. The thinnest section of the tension plate is
located directly over the groove containing the MDF
used to sever the tension plate.
8-32
8LV A8-503
The detonator blocks complete the ordnance train to
accomplish physical separation. An EBW detonator is
mounted on each detonator block, thus linking the block
with the respective firing unit. Each end of the MDF is
attached to a detonator block either of 'which can fire
the explosive charge. The MDF and, in turn, the
retrorockets ignite to separate the structure and retract
the 8-11 stage.
8-33
H I G
4
-
3
• 2
-
• 1
•
I
COMMAND S-II/S-IVS SEPARATION
SS 002 CHAN 5
SW SEL 206A31A -,
GSE COMMAND SEPARATION
SYSTEM RESET
® K91-1 ©
F
COMMAND S-II/S-NB ORDINANCE ARM
SS 071 CHAN 8 --
K90
E
+2011
GSE COMMAND SEPARATION CONTROLLER INHIBIT
D
COMMAND FROM
28 VQC lS_Il ENGINES CUTOFF CIRCUITR'( ALL ENGINES CUTOFF
K90 .. K90 --
1 g~~MAND -:-SEPARATION SYSTEM RESET
tl~=:Tf-_t-"U~"'"kJ-"--.- ------ -------------f------ --- -------- - K91-;-'"
® K92 © L..--------U--~.J='rt-lt=l--~,,~--. ________ .!.':.2_
.-:!:- K93
K93
.. h--,-, --------I---tt1:lJ ~
I c ~ ;
• • • • • • • • • • • • • • • • • • • • • • • • • • • • • • • • • • • • • • • • • • • • • • • •••••••••••••• ••••••••••••••••••••••••••••• •
..... ~........ . ... . • • ••• • •••• · •........... , ............................ , ..... "' ........ , ..... . • • •
•
• • • • • • • • • • • • • • • •
;; .
FIRE CHARGE
EBW FIRING UNIT
1A
I~ EBW DETONATOR
CDF
MANIFOLD PYROGEN
FIRE CHARGE
EBW FIRING UNIT
1B
I~ EBW DETONATOR
CDF MANIFOLD
NO 2 NO 1 INITIATOR ! I ! (8 REQD) T~,--'-'---'
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'---------~--------~
FIRE CHARGE
EBW FIRING UNIT
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I~ EBW DETONATOR
DETONATOR BLOCK NO 1
LINEAR SHAPED CHARGE
FIRE CHARGE EBW
FIRING UNIT 1B
~ EBW DETONATOR
DETONATOR BLOCK NO 2
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'~'""'=S='GN7.Ac.TU:..R"ES'-c-+-"'DA"T.:.E--l NATIONAL AERONAUTICS & SPACE ADMINISTRATION DR 7!J.JJ ;l;~ A--19·68 MANNED SPACECRAFT CENTER HOUSTON TEXAS
DSGN<l1I:.J...:' ~ W= QC~~ ~ g/~~~
ENGRA'A ~' 4.. .71 "",
APPL ().
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PROPULSION S-II/S-ISlB SEPARATION
SUBSYSTEM
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34 X 22 PAGE 8-34 I SHEET
4
3
2
8.2.3 8-11 LH2 Pressurization
A. Prepressurization
8LV A8-503
Prepressurization is initiated in the terminal countdown
sequence at approximately T-97 seconds and continues until
umbilical disconnect. The two fuel tank vent valves are
closed and in the low pressure vent mode. The disconnect
valve and ground prepressurization valves are opened to
allow Ghe at minus 275°F to flow from the ground source
through the prepressurization solenoid valve and into the
fuel tank distributor. The fuel tank pressure is main
tained between 34 and 36 psia prior to 8-IC launch.
B. Interim Pressurization
During the 8-IC boost, the LH2 vent valve control solenoid
valves are energized thus placing the LH2 vent valves in
the low pressure vent mode. The low pressure vent mode
maintains the 8-11 LH2 tank ullage pressure in the range
of 2,.0 to 29.5 psid until 8-IC engine cutoff.
C. At T3 + 0.11 seconds, the normally closed solenoid valves
will be deactivated to place the vent valves in the high
pressure vent Node, this~changes the vent valve range to
30.5 to 33.0 psid. During 8-11 powered flight the ullage
pressure in the fuel tank is maintained by gaseous hydrogen
supplied from the engines.
After 8-11 engine ignition, liquid hydrogen is preheated
in the regenerative cooling tubes of the engine, and tapped
off from the thrust chamber injector manifold in the form
of GH2 to serve as a pressurizing medium. The ullage
pressure drop in the fuel tank is sensed by the pressure
regulator which opens the pressurization line and permits
the GH2 flow into the ullage space. The pressure is main
tained at a nominal range of 28.5 to 30.0 psia by the
pressure regulator. At approximately 250 seconds after
8-35
8LV A8-503
8-11 engine ignition, the regulator is actuated and
locked into a full open position by an integral solenoid
valve energized by the "step pressurization" command
from the switch selector. The regulator, in a full open
position, permits incrfiased flow of GH2 , which raises the
ullage pressure to the vent valve setting range of 30.5
to 33.0 psia to compensate for the loss of head pressure
caused by the lowering of the fuel level in the tank.
8-36
H
8
• 7
6
5
• 4
3
2
LHZ TANK 34-36 PSlA
G
GSE COMMAND
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ESECOUMANO LH2 VENT VALVES OPEN
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1-.\ I~!'''!'!''!"'!'!' ~I'~ATE NATIONAL AERONAUTICS" SPACE AOMINISTRATION
OR ltM..z.'~ 8-" ......... NEC SPACECRAFT ceNTER HOUSTON TEXAS OSGN
" -" PROPULSION EIIGR , s-n LH2
44X 34 PACE 8-37 SHHT
8
7
6
5
4
3
2
*
8.2.4 LOX Pressurization
A. LOX Conditioning
8LV A8-503
LOX conditioning is necessary to provide LOX at the LOX
pump inlet at uniform temperature and density.
Conditioning of LOX is initiated at the start of LOX fill
and continues to approximately 10 seconds before 8-11
ignition. Conditioning is accomplished by recirculating
the LOX down the suction ducts, through the LOX pumps on
the engines, into the return lines and back into the LOX
tank. LOX recirculation is started by self-induced thermo
pumping or, when necessary, by thermopumping induced by
injecting gaseous helium. Thermopumping is self-started
by the heat differential present in the uninsulated return
lines. The heat absorbed by the LOX during this cycle
maintains thermal pumping. Recirculation is terminated by
closing the return line valves and LOX bleed valves.
Provisions for injecting ground supplied gaseous helium
to start thermopumping are available during LOX fill and
until umbilical disconnect. The helium is injected through
bosses into the return lines by opening the helium injection
control valve. Chilled helium may be used to further de
crease LOX temperature.
B. Tank Prepressurization
Prepressurization of the LOX tank is required prior to
liftoff to provide the required NP8H for engine start and
starts at approximately T-187 seconds and continues until
liftoff. The command to open the prepressurization valve,
to begin prepressurization, is interlocked with the closed
indication of the LOX tank vent valves. Opening the ground
prepressurization valve allows helium at minus 275°F to
flow from the ground source, through the vehicle
8-38
* 8LV AS-503
prepressurization valve, and into the LOX tank through
the distributor. When the LOX tank pressure reaches
37.5 psig the pressurization valve is closed by the
two tank pressure switches.
The 8-1C ignition command closes the disconnect valve
and initiates umbilical line bleed. Ground helium re
mains available for use until liftoff. Ullage pressure
provided at liftoff is maintained by LOX boiloff through
out the interim period between umbilical disconnect and
8-II ignition.
C. Flight Pressurization
Pressurization of the LOX tank during 8-II powered flight
is by gaseous oxygen supplied by heating LOX bleed from
the LOX pump outlet and is initiated at 8-II ignition and
continues until engine cutoff. After 8-11 ignition the
gas generator exhaust passes through the heat exchanger.
When the LOX turbine discharge pressure reaches a pressure
differential of 100 psid, the LOX anti flood heat exchanger
valve permits LOX bleed from the LOX pump outlet, to pass
into the heat exchanger. Flow of GOX produced at the heat
exchanger is regulated by the GOX regulator control valve,
varying according to LOX tank ullage pressure required, as
sensed by the reference pressure line. At approximately
250 seconds after engine start, the GOX regulator control
valve is actuated to its full open position and remains
in this position the remainder of 8-1I powered flight.
When the GOX regulator is actuated to its full open
position, LOX tank pressure increases to a nominal
40 psia.
8-39
4
3
2
H
lOX TANK VENT AND RELIEF VALVE OPEN 42 P$IA CLOSE 40 PSI A
OXIDIZER VENT
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G
GSE PNEUMATIC ACTUATION
TO PNEUMATICS
TO PNEUMATICS
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TO PNEUMATICS
TO PNEUMATICS
ESE ESE
COMMAND lOX TANK VENT VALVE CLOSE
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OXIDIZER VENT
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LOX TANK VENT AND RELIEF VALVE OPEN 42 P$IA CLOSE 40 PSIA
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FROM ENGINE NO 5 LOX PUMP OUTLET
FROM ENGINE NO 4 LOX PUMP OUTLET
FROM ENGINE NO.3 LOX PUMP OUTLET
FROM ENGINE NO 2 lOX PUMP OUTLET
FROM ENGINE NO 1 LOX PUMP OUTLET
o 01-_---'0'-_--';0 r----i_.t-"'--V ""'--t...::..J---~~
OXIDIZER HE PREPRES$URIZATION
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LOX TANK POSITIVE PRESSURE
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o
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I-:::,....,,,:;=~.::.:;=---:+::.:.,:-=-! NATIONAL AERONAUTICS & SPACE ADMINISTRATION MANNEO SPACECRAFT CENTER HOUSTON TEXAS
PROPULSION S-IT LOX
PRESSURIZATION
8.2.4 8-40 SHEET OF
4
3
2
8.2.5 S-11 Pneumatic Control System
A. Countdown through liftoff
SLY AS-503
The S-11 pneumatic subsystem is prepressurized with helium
at ambient temperature and 1500 psig at approximately
T-6.5 hours. The LH2 prevalves are actuated at the closed
positlon. The LH2 and LOX recirculation valves and the LOX
prevalves are left In their normally open position. The
subsystem is pressurized at approximately T-30 minutes with
helium at ambient temperature until a pressure of 3000
psia is attained In the high pressure helium receiver.
The regulator closes automatically when the pressure
downstream reaches 750 psia. The normally closed pneu
matic actuation solenoid valves prevent the actuation of
the LOX and LH2 recirculatlon valves to their closed posi
tions until commanded by the switch selector.
B. Llftoff Through S-1C Boost
Pressure is maintained to hold the LH2 prevalves In the
closed position until 0.5 seconds prior to S-1CjS-11 sep
aration. At that time, the built-in solenoids of the
LH2 prevalves are actuated, allowlng the LH2 prevalves to
open.
C. Staging and S-11 Burn
The low pressure helium receivers contain sufficient pres
sure for prevalve actuation in the event of engine failure.
8-41
H
4
3
2
GSE
• • • • • • GSE I ACTUATION
G
• • NC LH2 VENT NC • GSE VALVE NO 2 • ACTUATION
El! If If Ii ! " ! ! ! ! " " ! " ! " " " ! , ! " ! " ! ! " "9 ~c • PNEUMATIC • ACTUATION LH2 FILL AND • SYSTEM DRAIN VALVE
• HE FILL
• • • • • • • • • • • • :H'",~~="-t • • • • • • • • • • • •
NC
• • • • • • • • • • • • • • • • • • • • • • • • • • • • • • • • • • • • • • • • • • • • •
LOX FILL AND DRAIN VALVE
STAGE
PNEUMATIC CONTROL REGULATOR 675-750 PSIG
LOX VENT VALVE NO 2
SURGE SPHERE
F
PNEUMATIC ACTUATION SOLENOID VALVE
THERMAL RELIEF VALVE
E
LOX PREVALVE (5 PLACES)
N 0
•
N 0
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r------------------------------------------------I I NC
PNEUMATIC ACTUATION SOLENOID VALVE
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K44
CH1LLDOWN VALVES CLOSE
55134 CHAN 88
1aVDC
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K62
~DC TM
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K62 ..
GSE COMMAND RELAY RESET
~62
---------- -
LOX RECIRCULATION RETURN VALVES (5 PLACES)
N 0
NO
LH2 RECIRCULATION RETURN VALVE
ENGR
APP FEC
K62
----l NATIONAL AERONAUTICS & SPACE ADMINISTRATION
HOUSTON TEXAS
PROPULSION s-n PNEUMATICS
SIZE DWG NO ..
D 8.2.5 PAGE 8-42 SHEET OF
3
2
*
8.2.6 J-2 Engine System
A. General Description
SLY AS-503
The engine system consists of five single start J-2 engines.
The J-2 engine is a 200,000 pound thrust, high performance
engine, utilizing liquid oxygen (LOX) and liquid hydrogen
(LH2 ) as propellants. The center engine is fixed in posi
tion and is thermally protected on the upper half of the
engine by a flame impingement shield. Each outboard engine
is capable of being independently gimbaled for attitude control.
B. Operational Description
START - All five engines are started simultaneously upon
receipt of a command from the switch selector.
STEADY STATE - All five engines operate at approximately
100 percent thrust during mainstage operation and use a
nominal 5:1 propellant mixture ratio.
CUTOFF - Each engine initiates a cutoff sequence upon
receipt of a command from the switch selector or from LOX
or fuel depletion sensors. Under normal conditions, all
engines are shut down simultaneously by propellant deple
tion signals from any two of five sensors located in the
LOX and LH2 tanks.
MALFUNCTION DETECTION - Each engine is provided with a
system to detect malfunctions and to effect a safe shut
down. A cutoff signal is given to an individual engine
prior to attainment of main stage operation if the required
signal is not received from the ignition monitor. Once
an engine attains main stage operation, it may be shut
down if both main stage OK pressure switches deactuate
due to low-level thrust. If neither main stage OK pres
sure switch has indicated sufficient thrust for main stage
operation at expiration of the ignition phase t~mer, a
8-43
* SLY AS-503
shutdown of the particular engine is initiated. The
main stage OK pressure switches are checked through the
remote checkout self-sealing quick disconnect coupling.
C. Engine Purges
HELIUM TANK PURGE - Prior to propellant loading, helium
purge gas is supplied from the GSE through the helium
tank fill self-sealing quick disconnect coupling, the
manifold leading to each engine, the helium fill check
valve, and into the helium tank. After partial pressuri
zation, the ground supply valve is closed and the helium
tank is vented through the normally closed helium tank
emergency vent control solenoid valve. This procedure
is repeated three times to insure adequate purging.
START TANK PURGE AND PRECHILL - Following the helium tank
purge, the start tank is purged in the same manner as the
helium tank, utilizing the start tank fill self-sealing
quick disconnect coupling, the start tank GH2 fill check
valve, the start tank fill filter, and the normally closed
start tank vent and relief valve. Approximately 20 minutes
prior to launch, cold GH2 (1250 psig and -250°F) is sup
plied in the same manner for prechill purposes.
THRUST CHAMBER LH2 JACKET PURGE AND PRECONDITIONING - Prior
to chilldown of the thrust chamber, helium purge gas is
supplied through the thrust chamber LH2 jacket purge and
preconditioning self-sealing quick disconnect coupling,
the manifold leading to each engine, the thrust chamber
LH2 purge and preconditioning check valve, and into the
main LH2 feed line downstream of the normally closed main
LH2 valve. The gas passes through the thrust chamber and
out of the system through the fuel injector. The bell of
the engine thrust chamber is subcooled to approximately
-200°F with cold helium through this same purge and
preconditioning route.
8-44
*
SLY AB-503
TURBOPUMP PURGE - Helium purge gas is supplied through
the turbopump purge self-sealing quick disconnect coupling,
the manifold leading to each engine, and then to four
engine locations. The four engine purges performed are:
1. Seal cavity of LH2 pump, with flow passing through
a turbopump check valve. Purge gas exits through the
turbopump check valve and the LH2 pump seal cavity
bleed self-sealing quick disconnect coupling.
2. Seal cavity of LH2 turbine, with flow passing through
a turbopump check valve and LH2 turbine seal cavity
purge orifice. Purge gas exits through overboard
bleed lines.
3. Seal cavity of LOX pump, with flow passing through a
turbopump check valve and LOX turbine seal cavity purge
orifice. Purge gas exits through overboard bleed
lines.
4. LH2 injection of gas generator, with flow passing
through gas generator check valve and the gas generator
LH2 injector purge orifice. The purge gas exits
through the exhaust aspirator located on the thrust
chamber.
LOX DOME PURGE - At engine start, the normally closed
helium control solenoid valve located within the pneumatic
control package is opened, allowing gaseous helium to flow
from the helium tank, through the normally closed pressure
actuated purge valve, the LOX dome purge orifice, the LOX
dome purge check valve, the normally closed main LOX valve,
and into the thrust chamber LOX dome. Purge gas exits
through the LOX injector. When the four-way main stage
control solenoid valve is closed, the purge terminates
after approximately 1 second.
8-45
*
SLY AS-503
LOX TURBOPUMP INTERMEDIATE SEAL PURGE - The LOX turbopump
intermediate seal purge is very similar to the LOX dome
pu~ge, with gaseous helium entering the LOX turbopump seal
cavity through the LOX pump intermediate seal purge
orifice. Purge gas exits through the LOX seal cavity
manifold. This purge is continuous throughout engine
operation.
GAS GENERATOR LOX INJECTOR PURGE - Purge gas flows from
the helium tank, through the pressure actuated purge valve,
the gas generator LOX injector purge check valve, and into
the gas generator LOX injector. Purge gas exits through
the exhaust aspirator located on the thrust chamber. 'rhis
purge is performed during static testing and is not per
formed during flight.
NOTE
For J-2 engine data, further information may be obtained from the Rocketdyne publication, "Preliminary Technical Engine Data Manual," R- 3825-l. (CONFIDENTIAL)
D. Propellant Management System - General Description
The propellant management system monitors propellant mass
for control of propellant loading, utilization, and deple
tlon. Components in this system include continuous capaci
tance probes, propellant utilization valves, discrete liquid
level sensors, and ground and onboard electronics.
PROPELLANT LOADING - The control of propellant loading and
replenishing is performed by a ground-based computer in
conjunction with related equipment and systems. The stage
mounted propellant management electronics continuously
monitor the output of the LH2 tank continuous capacitance
probe and the LOX tank continuous probe. During loading
8-46
• •
operations, the signal from each probe is transmitted from
the onboard propellant management electronics to a ground
checkout and display. Backup sensors to the probes are
provided for both the LH2 and LOX systems. The LH2 fast
fill emergency cutoff sensor and the LOX fast fill emergency
cutoff sensor indicate 98 percent mass of propellant loaded.
The LH2 overfill p~ergency cutoff sensor and the LOX over
fill emergency cutoff sensor indicate 101 percent mass of
propellant loaded. The signals received from the 98 per
cent mass discrete liquld level sensors in either tank
stops fast fill automatically. The overfill signal received
from the 101 percent mass discrete liquid level sensors
automatically stops the entire loading sequence.
PROPELLANT UTILIZATION - During flight, the signals from
the LH2 and LOX tank continuous capacitance probes are
transmitted through LH2 airborne electronics package and
LOX airborne electronics package to both the telemetry
system and the airborne computer which compare the signals,
and provide an error signal to the propellant utillzation
valve on each LOX pump. Based on this error signal, the
propellant utilization valves are positioned to minimize
residual propellants at cutoff and assure a fuel rich
cutoff. This is accomplished by varying the amount of LOX
delivered to the engines. The propellant utilizatlon
valves are installed at the turbopump outlet and control
propellant mixture ratio by varying the amount of LOX
returned from the outlet to the inlet of the pump •
8-47
4
3
2
H
ENGIN~ START
5W SEL 206A31Al
MSC F""", 16U, D {~EV OCT 6~l
55034 CHAN 33
GSE COMMAND ENG CONTROL RELAYS RESET
G
+2011
~ ~OC ____ j ;17
K16
S-II ••••••••••••••••• .................
S-IC 1 S-II COMMAND ENGINE START LOCKOUT
ENGINE CUTOFF
SPARKS DEENERGIZE
,-I
F
'--------- ENGINE CUTOFF
E • o
ENGINE ELECT CONT ASSEMBLY
IGNITION PHASE CONTROL
AS! AND GG SPARK EXCITATION
HELIUM CONTROL
MAINS TAGE CONTROL
OPEN START TANK DISCHARGE VALVE
FUEL JACKET TEMP OK
ASI DETECTED
r--------------l NORMAL CUTOFF COMMAND
ENGINE CUTOFF COMO
PRESSURE SWITCH NO 1 ACTUATED
PRESSURE SWITCH NO 2 ACTUATED
START TANK DEPRESSURIZED
•
c
o
8
:~ K85-207 [9 K86-207 K87-207 K88-207 K89-207
SEE ENGINE SYSTEM DRAWING FOR A,B,D, E,F ,G,H,J,K,L,M,N, AND P
ENGINE 1 READY ENGINE 2 READY ENGINE 3 READY ENGINE 4 READY ENGINE 5 READY
APPROVAL
B> BPIBO-24R08-10 8PIBQ-24R08-09 BPIBO-24R08-08 BPIBO-24R08-07 BPIBO-24R08-Ob
r.;-.... DATE AERONAUTICS & SPACE ADMINISTRATION 17' r.:::-==:-:-:r".,...."+.,,...rl MANNED SPACECRAFT CENTER HOUSTON, TEXAS
PROPULSION J2 ENGINE 1.0GIC
S-II STAGE OWG NO ..
8.2.6 8-48 SHEET OF
4
3
2
*
8.2.7 S-11 Hydraulic System
A. General Description
SLY AB-503
The S-I1 hydraulic system provides attitude control by
gimbaling one or more of the four outboard engines during
powered flight. The system consists of four independent,
closed-loop, hydraulic control subsystems, which provide
power for gimbaling. Electrohydraulic actuators (two per
outboard engine), mounted in perpendicular planes, furnish
gimbal forces by extending or retracting simultaneously
or individually in accordance with electrical input signals.
The primary components are the main hydraulic pump, auxiliary
pump, auxiliary pump electric motor, accumulator reservoir
manifold assembly, and two servoactuators.
B. System Fill
The engine gimbal actuation system is filled with hydraulic
oil (M1L-H-5606A) from a low pressure ground source through
the high pressure service self-sealing quick disconnect
coupling. The low pressure service self-sealing quick
disconnect coupling is also connected to the ground source
to allow the return of fluid to GSE during preflight purging
and flushing operations. The manually controlled prefiltra
tion bypass valves on the servoactuator assemblies are
actuated to the bypass position prior to initiation of
system flush to prevent contamination of the hydraulic
actuators. The accumulator is precharged with GN2 through
the GN2 fill valve. Fluid is circulated through the system
by auxiliary pump. When sampling tests indicate that the
contamination level of the fluid is acceptable, the pre
filtration bypass valves are actuated to the flight position,
the auxiliary pump is stopped, the main hydraulic pump is
manually rotated, and the servoactuators are driven full
strok to complete the filling and bleeding operations.
8-49
*
C. Operational Phase
SLY AS-503
For the purpose of this description, preflight operation
shall begin with propellant loading and end with S-IC/S-II
stage sepration.
PRELFIGHT OPERATION - Prior to propellant loading, each
hydraulic system is filled with hydraulic fluid at low
pressure through the hydraulic fluid fill self-sealing
quick disconnect coupling. During and following propellant
loading, the hydraulic system fluid is intermittently
recirculated by the electrically driven auxiliary pump
in order to prevent the fluid from freezing. Recirculation
is terminated just prior to S-IC ignition command. Recir
culation is not necessary during S-IC burn, due to the short
duration of S-IC burn. The accumulator reservoir manifold
assembly contains an accumulator and a reservoir. The
reservoir receives fluid from the servoactuators during
engine operation and supplies low pressure fluld to the
auxiliary and main hydraullc pumps. Prior to launch the
accumulator is fliled from the pressurized auxlliary pump
flow. Just prior to liftoff, this fluid is stored under
high pressure in the accumulator by closing both hydraulic
lockup valves which are contained in the accumulator
reservoir manifold assembly. These valves are controlled
by an independent lockup control solenoid valve. The
engines remain in the "nUll" position during countdown,
except during gimbal checks. These checks are made between
20 and 30 mlnutes prior to liftoff.
INFLIGHT OPERATION - After S-IC/S-II stage separation, an
S-II switch selector command unlocks the accumulator lockup
valves, releasing high pressure fluid to each of the two
servoactuators. This fluid provides gimbaling power prior
8-50
8LV * AS-503
to main hydraulic pump operation. The main hydraulic
pump is driven directly from the accessory drive pad of
the engine LOX pump. During 8-11 main stage operation,
the main hydraulic pump supplies high pressure fluid to
the servoactuators per engine, one for the pitch axis and
one for the yaw axis. Each servoactuator contains a servo
valve which controls the position of the hydraulic actuator
in accordance with electrical signals transmitted from the
flight control system. \
8-51
,~,
NEUMATIC UPPLY
K
STAGE PNEUMATIC SUPPLV
FUEL PRESSURIZATION LINE PURGE
~~~ti~~T PRECHILL
TO lOX PRESSURIZATION SYSTEM
, un 207 ENG 4 LOX
PREVA,LVE OPEN
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LOX TANK
FROMEIIG ."
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"'lC3 ENC4 ENGS
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STAGE
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STAGE~ PNEUo.IATlC SUPPLY
PLENUM CHAMBER
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N"TlON"L A,ERONAUTICS & SPACE ADM'NISTRA,TION IMNNEO SPACECRAFT CENT£R
PROPULSION,J-2 ENGINE SYSTEM, SolI STAGE
SLY SIZE DWGNO
AS-503 J 827 60 5X38 25
9
B
7
6
4
2
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8
7
6
5
4
3
2
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G
TItE~MAL SWITCH OPEN 200±lO'F ClOSE_155±W" F
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LOW PRESS RELIEF VALVE CRACKlf«; PRESS - 200 PSI, MIN RESEAl PRESS - 175 PSI, MIN
----CONTROLLED PRESS S; S S S S S S
RETRACT p.,.,., • ••
SUCTION S/S/S?S?S
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~---- ~~~~"'UlATOR RESERVOIR
ACCUMULATOR (DIU D1SPLACABLE VOLUME - 127511>12 POSITION AREA - 22 41"12 BOOTSTRAP PISTON AREA _ 1 351"12
:~~~~~~~~~t~2~ _ 300 1"13 PRECHARGE PRESS - 2200 PSI AT 70· F SOOTSTRAP PISTON AREA - 1 101HZ
RESERVOIR VOLUME CAPACITY _ 206 71"13 VOLUME FILL _ 1551N3 PISTON AREA_ 5021HZ RES TO Ace OIL PISTON AREA RATIO 37 21 RES TO ACC GNZ PISTDNAREA RATIO 45 (,1
B A
'" ENGR DATE APPROVAL
_---- lOW PRESS HY!) en UlCK
DATE NATIONAL AERONAUTICS & SPACE ADMINISTRATION
fH8
S-JI ENGINE GIMBAL SYSTEM
SLY SIZE DWGND
AS-503 J 8.2.8 PAGE 8_53
8
7
6
5
4
3
2
8.3
8.3.1
8.3.2
S-IVB STAGE
Propulsion (General Descri~tion)
SLV AS-503
The AS-503 S-IVB stage is a three-burn vehicle and incorporates
provisions to condition and/or maintain the propulsion system
for each start and burn. The propulsion system consists of
a bipropellant J-2 engine, a fuel supply tank, an oxidizer
supply tank and a propellant utilization system (PU). The
fuel and oxidizer tanks incorporate separate pressurization
systems, venting systems and chilldown systems, which condition
the propellants to insure proper engine start and burn. The
above systems, plus other supporting systems are further defined
in the appropriate subsection.
On the Saturn V vehicle there is an additional propulsive
requirement to maintain the propellants settled at the pump
inlets when the J-2 engine is inoperative. This requirement
is satisfied using two systems. The first is a high thrust
(140-pound) short duration burn system employing two hypergolic
engines, one located in each APS module (see subsection 8.3.11).
This system is used during the transition periods when the
J-2 engine is shut down or started up. The second is the
low thrust (minimum of 6 pounds) continuous vent system. This
system utilizes vented LH2 tank boiloff gas to supply the
propulsive force. This very low acceleration is maintained
during the orbital coast period. This continuous vent system
is further described in subsection 8.3.4.
Structures (General Description)
The S-IVB structure of the Saturn V vehicle consists of a
forward skirt assembly, propellant t~nk assembly, aft skirt
assembly, thrust structure assembly, and aft interstage assembly,
drawing 8.3.0.
8-54
A. Aft Interstage Assembly
SLV AS-503
A truncated cone of aluminum skin panels, 260 inches in
diameter at the forward end, 396.750 inches in diameter
at the aft end, and 227.5 inches long. It is externally
stringer-stiffened with extruded attach angles at each
end; the forward attach angle is bolted to the aft skirt.
The S-IVB/S-II separation is forward of the interstage.
B. Aft Skirt
A cylindrical section structure of aluminum skin panels,
260 inches in diameter and 85.5 inches long. It is
stiffened by external stringers, extruded attach angles
at the forward end, and an ordnance separation frame at
the aft end.
C. Thrust Structure Assembly
A truncated cone, fabricated of aluminum skins, formed,
chem-milled, riveted to stringers and frames and attach
angles at the large end, and fastened to the cast aluminum
engine mount at the smaller end. The thrust structure is
bolted to attach angles on the LOX tank dome and provides
the attach point for the J-2 engine and distributes the
J-2 engine and distributes the J-2 engine thrust over the
entire tank circumference.
D. Propellant Tank Assembly
Consists of the forward dome, cylindrical tank wall, and
LOX tank assembly. The LOX tank assembly consists of
the aft dome and the common bulkhead which isolates the
LH2 tank from the LOX tank. The forward dome and aft dome
are similarly constructed of nine pie-shaped segments of
sheet aluminum structure, which is formed, etch-milled, and
welded together. Both domes have attach flanges In the
center for an access door in the forward dome, and the
8-55
8.3.3
SLV AS-503
LOX tank sump in the aft dome. The cyllndrical tank center
section is fabricated from seven aluminum skins with a
waffle pattern mechanically milled on the interior surface
skin, which is formed, seam welded together, then welded
to attach rings at both ends. The common bulkhead is
constructed of a 1-3/4-inch fiberglass honeycombed core,
bonded between two hemispherical domes. The domes are
fabricated by welding a contoured center plate with nine
fusion welded aluminum etch-milled skin segments to cir
cumferential rings. The domes are then bonded to the honey
comb and welded to the aft dome.
E. Forward Skirt Assembly
A cylindrical structure fabricated of aluminum skins,
260 inches in diameter and 122 inches in length. It is
stiffened by external stringers and has attach angles at
both ends. The forward skirt is bolted to the forward
end of the tank assembly and the instrument unit is bolted
to the forward end of the skirt.
Staging (General Description)
Several systems are employed to cause the physical separation
between the S-II and the S-IVB stages. These systems receive
commands from the instrument unit via the S-II and/or S-IVB
sWltch selectors.
The propellant settling, as activated by the S-IVB switch
selector, is the solid propellant ullage rocket system. The
ullage rockets are ignited during the physical separation
process to provide for propellant settling of the S-IVB
stage. After the J-2 engine ignites, the spent ullage rockets
and their fairings are jettisoned (Drawing R.3.1.)
8-56
TYPICAL 2 PLACES 1800 APART
(NC1'\IN'\L THRUST 3390 LBS LE'GTH 34. 1 DIAMETER 7.3)
AFT SKIRT ASSEMBLY
SPRING-LOADED JETTISON ASSEMBLY
FRANGIBLE NUT
C~ CQVMANI)
CHARGE CQVMANI) CHARGE
ULLAGE ULlAGE ULLAGE
IGNITION OiARGING JETTISON
ON RESET ON
SS 164 SS 134 SS 144
CHAAl 54 CHAAl 88 CHAN 55
r-- -- -ULLAGE-,
CONFINED Dt TCHA. TI N(,
FUSE (CDF) (TYPICALL
HIGH VOLTAGE
CONVERTER
IGNITION I FIRING I UNIT U HIGH
I VOLTAGE
I CONVERTER
I I
HIGH 2300 VOLTAGE
I VDC TRIGGER
Propulsion - S-IVB Ullage and Ignltlon Systems
COI'W\ND FIRE
ULLAGE IGNITION
ON SS 124
CHAN 56
(0 K23
HIGH VOLTAGE
CONVERTER
2300 VDC
COfoMOND ULLAGING
FIRING RESET
SS 053 CHAN 73
K23-1
--, 'r-ULlAGE I I
JETTISON I I FIRING
UNIT U I I HIGH
I I VOLTAGE caWERTER
I I HIGH I I 2300
VOLTAGE I VDC TRIGGER I
5000 I VOLT I
PULSE I
--1 ULlAGE
JETTISON FIRING
UNIT 42
HIGH VOLTAGE TRIGGER
5000 VOLT
PULSE
CClM'I'WJ FIRE
ULLAGE JETTISON
ON SS 032
CHAN 57
S-IVB SWITCH
SELECTOR
SLY AS-S03
DRAWING 8.3.1
8-57
f . -'-'-. I --
! '
'~ {
I:
'I' I' II' I, , I
: I' ! I'
I ' I , ,I I
___ I'-"-,:\ll1.'''-l.!L' u.li..'ij' I L!UL'--'-1
'"
Propulsion - S-IVB Stage Structure Layout
I' , I
SLV AS-503N
DRAHING 8.3.0 8-58
8.3.4
SLY AS-503
Two commands are required to either ignite the rockets or to
jettison them. This command process is as follows:
• The IV issues a charge command which provides 28 Vdc to a
relaxation oscillator in the exploding bridge wire (EBW)
firing unit. The oscillator output is amplified, stepped-
up by transformer action, and rectified to charge the storage
element and place a 2300 Vdc potential across a gap tube.
This charging process requires a maximum of 1.5 seconds.
• The IV then issues a firing command which provides 28 Vdc
to another amplifier in the firing unit which provides a
5000 volt trigger voltage to the gap tube causing the
2300 Vdc stored energy to be applied to either the ignition
ordnance or jettison ordnance.
Discharge of the EBW firing units ignites the redundant ordnance
items leading to the direct ignition of the solid engine
propellants or firing of the frangible nuts, thereby releasing
the holding bolts.
LH2 Pressurization (Drawings 8.3.2 and 8.3.2a)
The fuel tank ullage pressure must be maintained at proper
pressures to assure a net positive suction pressure at the
LH2 pump inlet to insure proper engine start and operation.
During rapid fill phase, LH2 is supplied at the rate of 3000 gpm.
The LH2 tank vent and relief valve is open during this time.
The final topping fill rate is 250 gpm. At the start of final
topping, the vent and relief valve is closed and prepressurization
is initiated with helium from ground source at 600 psia at
-360° F. The fuel tank is prepressurized to 28 to 31 psia.
During boost and prior to engine start it is anticipated that
LH2 ullage pressure will rise to near LH2 tank relief pressure
8-59
SLV AS-503
of 31-34 psia. If this occurs, or if at any other flight
time venting occurs, the gases will vent through the non
propulsive vent.
During engine firing, GH2
is bled from the J-2 engine tapoff
at 750 psia and at -260° F to maintain adequate LH2 tank
pressure. Pressure is controlled by the fuel tank pressurization
control module.
During burn, the flight control pressure switch is enabled
and senses ullage pressure. This pressure switch controls
tank pressure within 31 psia and 28 psia by sending a signal
to the pressurization control module when tank pressure exceeds
31 psia, thus closing the control valve and decreasing pressuri
zation flow. When tank pressure falls below 28 psia a signal
is sent to the pressurization control module, opening the
control solenoid valve and increasing pressurant flow.
Between burn periods the pressurization system is deactivated
and continuous venting of the tank is performed. Thls is
not a relief vent, but rather, a controlled vent using the
boiloff gases as a propulsive source. The tank pressure is
held to 20 psia by the continuous vent system. The vented
gases are directed aft and provide a continuous low thrust
(8-15 lbf) on the vehicle to maintain the proper propellant
position.
The dual repressurization system pressurizes the stage propel
lant tanks to flight conditions for restart of the J-2 englne.
Repressurization for first start is accomplished by the cryogenlc
repress system. )
The 02/H2 burner provides the heat to expand
the cold helium used to pressurize the propellant tanks prior
to first J-2 engine restart.
The burner utilizes LOX and LH2 from the main tanks. A thrust
of 16 to 30 pounds is obtained, and is directed approximately
8-60
SLV AS-503
through the center of gravity of the vehicle. The 02/H2 burner
heats cold helium for use as the oxidizer and fuel tank pressurant.
The nine cold helium spheres are located in the LH2 tank, and
contain helium initially charged to 3100 psia at _420° F. The
pressure is reduced to 385 ~25 psig by the LOX tank pressure
control module. Cryogenic repress control modules are located
in each supply line. The solenoid valves in the module are
controlled by a signal from the respective tank flight control
pressure switches which are sensing tank ullage pressures.
The ambient helium repressurization system provides second
restart repressurization as well as backup for the cryogenic
repress system.
The ambient repress system operates late in the restart preparations
sequence. If helium from the amblent system is required for the
first restart (due to a malfunction in the cryo repress system
or for makeup gas), it is supplied through an independent con-
trol module for each propellant tank. Two spheres are provided
for LOX tank repressurization and six spheres are provided for
LH2 tank repressurization. The LOX tank repressurization
bottles are tied in to the LH2 tank repressurization bottles
through check valves. This allows the LOX tank bottles to
aid in the repressurization of the LH2 tank.
8-61
LH2 TANK LATCHING
REUEF VALVE OPEN ON OFF SS 126 SS 132 CHAN 99 CHAN 100
+4015 28 VDC
LHZ TANK CONTINUOUS
VENT VALVE CLOSE ON OFF SS 131 SS 011 CHAN 84 CHAN 87
LHZ TANK CONTINUOUS
VENT ORIFICE VALVE OPEN
ON ~ OFF" SS 012 SS 113 CHAN 111 CHAN 112
+4015
LHZ TANK VENT
VLV OPEN ON OFF SS 061 SS 106 CHAN 38 CHAN 76
• S-IVB SWITCH SElECTOR
LHz TANK VENT AND LATCHING
REU EF VALVES BOOST CLOSE ON OFF SS 146 SS 166 CHAN 77 CHAN 78
~- -n--ESE 71 ...-K6--1-*1_...-I+--l ESE
-n--+ K5-1T ~3_1
~~ A PRESS FUEL TK\
( NON-PROP VENT to I __ m o-so PSIA OP 1IlQ-O I-Jlll-OO 1-
NON-PROPULSIVE -VENT 1- LP~ ~ PRESS FUEL ~~
( NON-PROPUL~VE VENT NO 2 o-ro pgA J
DPlBO-OI-IO-OO -- ;::E ~
( CONT VENT ) I() 1 TEMP
\ 25 TO 260 DEG R I
Y _~ T ::1
k ooIS\-409 (pm, FU;:t TKj
CONT VT NO 1
\ o-so PSIA J OP IBO-O:HI!I-OO
'---""
-::I -~~~
(PRESS FUEL TKJ ( CONT VENT ) CONT VT NO 2 NO 2 TEMP
\ o-so P~A ! \ 2S TO 260 DEG R J OP IBO-03-IO-00 --12 JULY 1968
0'1BO-05-02-OO
.. ESE
DIRECTIONAL
I CONTROL VALVE
~
NC rr ~ --r ACTUATION CONTROL ESE ESE MODULE
CONTINUOUS VENT MODULE
T
MIL
~- -FYEl PQs1 .:...=.I....;...
T .-F
~
ZO'05PSI~J ~ POS - OP -'-I I-'- CL !"'-'-
® ESE
D -/KI1-410 ........ FUEL VENT OP VALVE OPEN LATCHING
LATCH \ 0 TOldVOC J RELIEF VLV
CRACK 34 PSIA CL CPIBO-09ROI-OS -- RESEAT 31 PSI A MIL II
Il II -- ~ FUEL VENT /K1-410, LH2 VENT \ NC CL
AND RELIEF ( VALVE CLOSED rpQs OP
CRACK 34 PSIA OTOldVDC J t:..= RESEAT 31 PSIA
CPlBO-09ROI-01 DP lBO-09UO 1-0 1
~ ;::E NC ~ ~ flJ1~ ACTUATION
CONTROL PNEUMATIC MODULE SOURCE
=- PNEUMATIC - SOURCE
- I /K0154-41~ =- PNEUMATIC J~ELlEF OVERRIDE SOURCE SHuTOFf VALVe CLOSED
). OTOldVDC I CPI80-09R09-09 -
:;:E ~flr~ '.:::= [3::
ACTUATION --- CONTROL "'-./Ko ISH I"
rRlflCE SHUTOFF 1 MODULE VALVE CLOSED ~ oro 28 VDC
CPIBO-09ROI-02 DPlBO-09UOI-02
/'
1ST BURN RELAY
ON SS 031 CHAN 68
OFF SS 051 CHAN 69
2ND BUR~ RELAY ON SS 103 CHAN 32
OFF SS 034 CHAN 33
+ 4D15
LHZ TANK CONT VENT
RFUEF OVERRIDE SOV OPEN ON OFF SS 145 SS 105 CHAN 107 CHAN 108
@ ®
SLV AS-503N
LHZ
TANK LATCHING
RELIEF VALVE LATCH
ON SS 72 CHAN 64
OFF SS 12Z CHAN 19
-n'H~'i
K56 ... + 4015 28 VDC
+ 4D15 ....--28 VDC
::=EJ NC NC
3::: ~-flr~~ <=
----l REPRESS, & FL T CONTROL (ACT 34 PSIA) PNEUMATIC
H (0 ACT 31 PSIA) SOURCE ACTUATION CONTROL -- MODULE CIP -- /DIn-41O, 1 ,{ PREss. FUEL
ULLAGE EDS 1 \
TO REPRESS. \ 0 TO SO pgA FROM CRYO SYSTEM CP 180-0 1-02-00 SYSTEM
~ DPlBO-OHl2-OO I LH2 TK PRESS CO NT MOD f.!-J I I ~ -- I f IsTEP J 1
"""" /D178-4~ FROM AMB LL PRESS FUEL ) SYSTEM
\ ULLAGE EDS 2 PRESSURE VALVE
\ 0 TOSOPSIA r-NO -fl NO CP 180-0 1-03-00 DPIBO ~H13-'11
LH2 TANK FUEL TANK PREPRESS
LOX TANK
-HELIUM DISCONNECT
& W
FROM JZ ENGINE
LHZ PRESSURIZATION SYSTEM SCHEMATIC-503N(MANNED)FUGHT
DRAWING 8.3.2
8-62
S-IVB SWITCH SELECTOR
LHZ TANK REPRESSURIZATION CONTROL VALVE OPEN
K90-2
~ TEMPHE \ REPRESS J
'\ lID TO 660o R/ DPI~OO
~ TEMP-HE ') REPRESS
-=-K87-Z
JT CRYO U AMBIENT
'\ 110 TO 66O"R7 DPI~JlL!!i 00
LH2 REPRESS CONTROL MODULE (AMBIENT)
~ I TEMP-HE ) ~ ESE
S rl REPRESS \-01=10 TO~660o,.,--lR
OP ltD JlL~OO
.,:-==!~::::t>i¢=! NC
, ,
NC
~ ~ It NC FROM -=! -t:::::!::::! -I====:::==~~ AMBI ENT L-J '--'
HELIUM fiLL
8
~
(PRESS FUEL TK)
HE REPRESS SPHERES
\ 0 TO 3500 PSIA I DPl~~-OO
..,,1----< I f";'\-~~ ~ (PRESS FUEL TK)
HE REPRESS
@3
\OTO 3500 PSIA / HELIUM SUPPLY 40 SPHERES COLD
T 10 CPIB~I-OO fROM LOX PRESS
C0=i MODULE
11 fROM LOX TNK - +-AMB REPRESS
SPHERES
12 JULY 1968
TO Ji ENGINE t HELIUM TANK fiLL
SPARK EXC NO Z
-=-
• -PILOT BLEED
SPARK EXC NO 1
-=-
SLY AS-503N
S-IVB SWITCH SELECTOR S-IVBISWITCH SELECTOR i
ESE COMM LOX & LHZ S-IVB SWITCH SELECTOR
OZHZ BURNER SPARK EXCITER COMMAND
OZHZ BURNER LOX VALVE PILOT VLV TANK REPRESS CONTROL STAGE REPRESS SYSTEM
OZHZ BURNER fUEL VALVE LOX TANK REPRESS VALVE OPEN RELAYS MODE SELECTOR
Off ON Off CHAN 75 CHAN 71 70
+4015~
_ _ K80-1/.
:Sf OZHZ BURNER-1 LOZ VL V CLOSE
f
CLOSE OPEN ON ON 74 89
CLOSE OPEN O~ VOTING CIRCUIT ENABLE CONTROL VALVE ENABLE DISABLE ar-0 (AMBIENn (CRYOGENIC) OFF ON OFf OFF ON ON OFF
CHAN 61 60 72 CHAN 86 85 CHAN 36 37
",roo" ~ r±, [~~~: ---------, "@ ______ ~ ~<W"--~---.. --~
ESE 02HZ BURNER fUEL Hof-~ VALVE CLOSED
H
~
(TEMP BURNER \
lOX INJ J t \ 160T096O"RJ r +1 rn DPIBI)-IOLOIOO
~--~~--~-----
\ C"I
K52-1
f , .. ESE FUEL PROP r l ~~~~~: +4D!5 ~ I'M ~~OP~ ~L m ~ ~ G ~ +:r4~15 : '-~-KI-9)'-03------' 3 ~ ~ -=-
IU PWR '(EVENT BURNER ') K75-1 ----TEMP BuRNER : lOXMANf CHAMBER DOME Kill C
\ '60101'60 OR/ KI-2 - ----~- -------, \ OS~~ 18~ I BRIDGE BRIDGE BRIDGE
K52 • BURNER r> EDSCUTOFf ~
BURNER LHZ PROP VALVE ACTUATION CONTROL MODULE
TO LHZ TANK
OP I~(i;-OO IU {B u fR ESE ENGINE OPI~03 ~r¥~ -......... I, I MALf JEVENT BURNER ') -......... u fROM ESE LOX.AN' •••
i' sov OP
+4015
"". "'" T K18'
TO 1ST & ZND BURN -
KIO}
PNEUMATlCS):~I===:::;-;:~===::;;:" SOURCE
G).--I--...J
lGRD FILL, PREPRESS REPRESS. FL T CONTROL 31 PSI A ACT MAX Z8 PSIA 01 ACT MIN
- ~C
CL
\ 1'-,--'--1 COMPONENT TEST \ 0 TO 18V J
I T@ lilT r-:- OPI80 09UOH3 1 L:.. u fR PROPELLANT
I ® r> DEPLETION ----- ~
IT@ZPZI§
f ~ fROM RANGE FROM PRIMARY '-----'( ~
I T@31 _ SAFETY DLOX PR ESS 3 l ~ 1; L.J:j\BURNER SYSTEM _ __
,,, ~SHUT =======:f::I=======" 50 ! 1 ROh i I=-- T DOWN - 11
_ I@ACT:;;?'r~ %,,- I~ - TO LOX TAM< .rcJ83-IOl' './" POS 41 PSIA ACT ~ T~~:~N~ER \ '1' ~ INUO_ Z INJ NO 1 LOX SHUTDOWN 38 PSIA DIACT ~ _~
K31-1 -• TIM KI0l
LOX 'REPRESS CONTROL MQDULE (AMBIENT)
~ ESE
,~ :=t;>'4:===!== =-
lr -- NC
K32rf-------s:-~~~-J- ----ti32 --- IP ~ _ FLT CONT SYSTEM - ____ ~IP
(DlSBL'D FOR REPRESS)
MEASUREMENT FUEL TANK i REPRESS SW o 31 PSI A ACT MAX GRD fiLL PRESS'D, PRE-PRESS U -~~~ Z8 PSIA D/ACT MIN & FLT CONTROL PRESS OK RELAY DSBL
J'i-!- ~ VALVE LOX TANK REPRESS ~. \f/JTOBf/JoRI 11 DPD2JJ t PRE-PRESS,FLTCONT I +4D15 _OPI~ 00 « IT CLOSE I & GRD FILL
O_P=C=='::::--~~============!:::==-:J' I (~(=~:::::J OPEN VALVE CONTROL
PILOT +=
BLEED DUMP
~ I I
P CMD
FROM LHZ REPRESS REG TO K76 BACK-UP SW VIA K5Z M
LHZ SUPPLY - -'1~ SWITCH '10 LHZ PROP VALVE 'T
I
TO K74 ON LOX PR ESS SCHEMA TIC
PILOT BLEED
II L-J
LOX REPRESS CONTROL MODULE (CRYOGENIC)
LH2 REPRESS CONTROL MODU'--E (CRYOGENIC)
FROM LHZ TANK PRESS CONTROL MCDULE
(TEMP BURNER \ (lH2 PRESS·COll J \ 60 TO 660 R / DP~OO
~~~~~'(~~~~~~~~~0118~1I=11~~C3)8==~ __ ~~III~ r ~ rh ih ~
~ : NC
I
NC
~
II - PILOT BLEED
485 PSI A ACT MAX ¢ 335 PSIA DIACT MIN~
LH TANK REPRES~ ~+4DI5 RE~ BACK-UP SW W TO K5Z
£ l TEMP BURNER )
lH2 PRESS HE IN
35 TO 1£0° R .J OPIBO 10Uil 00 -
-I - L-J
~~ EVENT HE ') ( EVENT HE HTR lH2 HTR LH2
( VLVFUlLOP VLVFUllCl) o TO 18V / \ 0 TO 18V
CPI!!l-09RI~05 CPltD-09!!!S:0'
-
CllH03
(TEMP BURNER \
NOZZLE J .f/J TO IfIff'R /
OP~OO
T
OZHZ BURNER
LOX SUPPLY
BURNER LOX SID II VLV ACTUATION, CONTROLjIMODULE
-- :-7
PNEUMATICS SOURCE
l.::========:' ;:=: = I ====!"I NC
485 PSIA ACT MAX COLD HELIUM SUPPLY ~ 335 PSIA 01 ACT MIN ~p I r'-~ fROM LOX PRESS
NC ~r.-=1::~!2!i:~::;-;::====~'V'~ I MODULE
J K WI t.==::t;l.¢==~
C KI08
4
LOX TANK REPRESS D REG BACK-UP SW
01" '
02H2 BURNER SCHEMATlC-503N (MANNED) FLIGHT
DRAWING 8.3.2a 8-62a
8.3.5 LOX Pressurization (Drawing 8.3.3)
SLV AS-503
The oxidizer tank pressurization is accomplished by using the
LOX pressurization control module. At the beglnning of LOX
tank fill, the vent and relief valve is opened. During rapid
fill, LOX is supplied to the tank at a maximum rate of 1000 gpm
and is then reduced to 200 gpm during slow fill. When slow
fill is complete, the vent and relief valve is closed and
prepressurization begins until desired pressure has been
reached.
The LOX tank is prepressurized to 38 to 41 psia by the cold
helium flow from the GSE and controlled by the cold helium
shutoff valves. Cold helium for inflight pressurizatlon is
stored in eight spheres charged to 3100 to ~ 100 psia at
-420° F located in the LH2 tank. The flight control pressure
switch (sensing tank ullage pressure) controls prepressurization
by opening and closing the onboard cold helium shutoff valves
for cold helium pressurant flow, and in this way acts as a
regulator. Normally, the cold helium regulator backup pressure
switch picks up at 450 to 485 psia and closes the cold helium
shutoff valves and drops out at 335 to 370 psia and opens the
/ cold helium shutoff valves. In case of regulator failure during
flight, the regulator backup pressure switch acts in a bang
bang mode. During prepressurization and boost, the backup
pressure switch is deactivated. After engine ignition, the
flight pressure switch is changed over from control of the
onboard cold helium shutoff valves to control of the heat
exchanger bypass valve. The cold helium shutoff valves cycle
to the open position allowing cold helium to flow from the
cold helium supply through the regulator, reducing pressure
to 385 ~ 25 psia through the shutoff valves, past the plenum
chamber into a manifold. A portion of the cold helium flows
to the engine heat exchanger where it is heated and expanded.
8-63
SLV AS-503
Another portion flows through an orifice to the LOX
pressurization line where it is mixed with the output
from the heat exchanger. The combined flow is directed into
the LOX tank. Flow through two orifices is insufficient to
maintain tank pressure during engine firing. As LOX tank
pressure decays to 38 psia, the flight pressure switch drops
out allowing the heat exchanger bypass valve to go to its
normally open position. This permits additional flow from
the heat exchanger to increase the LOX tank pressure. When
the LOX tank pressure reaches 41 psia, the flight pressure
switch picks up, closing the heat exchanger bypass valve.
The LOX tank pressure cycles between 38 and 41 psia. At engine
cutoff, the flight pressure switch is disabled allowing the
cold helium shutoff valves to go to their normally closed
position.
Between first and second burn, the LOX tank pressurization
system is deactivated during the two coast periods between
burns. There is a vent system similar to the LH2 tank in that
there is a vent and relief valve and a non-propulsive vent
and relief valve as a backup. However, should the tank be
commanded to vent or have relief vent, there is a propulsive
force directed through the approximate center of gravity.
Prior to the two restarts, the LOX tank is repressurized to
the flight control pressure switch settings, 38 to 41 psia.
Thls is accomplished as described in paragraph 8.3.4.
8-64
HEAT EXCHANGER BYPASS VALVE
ENABLE DISABLE SS 161 SS 016 CHAN 50 CHAN 51
LOX TANK FLT PRESSURE SYSTEM
ON OFF SS 171 SS 167 CHAN 103 CHAN lD4
©® Kll ~ _______ ::-~ Kll-l
S-IVB SWITCH SELECTOR LOX TANK PRESSURIZATION SHUTOFF VALVES
CLOSE OPEN SS 152 SS 172 CHAN 79 CHAN 80
1<;; VENT VALVE
•• O~~
~F- • '-
© ® +211 V 1
LOX TANK VENT VALVE
OPEN CLOSE SS 045 SS 013 CHAN 93 CHAN 94
LOX TANK VENT BOOST CLOSE PILOT VLV COMMANO
ON OFF SS 073 SS 033 CHAN 95 CHAN 96
VENT VALVE
F- BlST CLOSE
-- .J> • K15 ESE' "' "r...~,. ;;1- \9 fb --------------::-A~!':-l' w:if---~ '--, ~-@r.=====::::::rr===========il
LH2 TANK
/"DI80-42~ LOX ULLAGE' r.::p
PRESS - EDS 2 r-u:: \ OT050P~A / CPIBO-14-O~0
~ ( TEMP-COLD HE)-IT = ~
mo 56O"R I r,'\ DP IBO-18L08-OO I C 2.J _
~ [J) (TEMP-COLDHE )-crr~
me 80'R / r.\
(P lBO-14-O~0
cB ~ 5 0 LOX ULLAGE \ r= PRESS - EDS I~
~J \ OT050P~A j \..:..- CPlBO-I4-02-OO fJ' ] DPlBO-14-02-OO '0 ~ R8 J COLD HE \..:..-1==.J--""1 PRESS
CIP
OPIBO-18L07-OO - ~ o TO 3500 pgAj
(P 160-01-0 1-00 VcOXTAN~
====/~==========~
COLD HELIUM DUMP MODULE
FROM ~ CRYO SYSTEM -===iUii=====:
SLY AS-503N
LOX TANK NPV OPEN
ON OFF SS 114 SS 165 CH 105 CH 106
LOX TANK NPV OPEN LATCH ON OFF SS 062 SS 123 CH 44 CH 45
-PNEU PNEU
-=- SOURCE =-SOURCE
~ ~ -....jo.--I- t---I---I- -
Lr- ~ ~-~ lOX TANK NPV ACT CONTROL MODULE
OP LATCH
~ (LOX NPV VLV-CL
OT028VDC j CP IBO-09 R09-10
= rh EID- 1-
..--L/K198-42~
fox NPV VLV-oP~ \ OT07i>VDCj
CPIBO-09R08-Q6
--
---/0243-40 .........
{ LOX NPV NO 1 \ PRESS .J
\ OTO SO P~A j CP 1BO-05-04-00
PURGE r-;::::=::::r><:t:::====~ LOX NPV VENT l & RELIEF VALVE :::1'1 _ CRACK 45.5 PSIA MAX It.r / 0244-«14" RESEAT 41 PSIA MIN I fLOX NPV PRESS) VENT & RELIEF VALVE , NOZZLE NO 2
FROM."-I-__ ~_.p~ ESE
CRACK 44 PSIA MAX \ 0 TO 50 PSIA j RESEAT 41 PSI A MIN CPlOO-08-09-OO
~ . I=~==~==~~~~====================~LOXTANK
(PRESS-COLDHE' __ ~~~~~~~~~=~~~,!"!!!_,, FROM AMB BOTTLE BACKUP J lOX TANK PRESSURIZATION MODULE I SYSTEM o TO 3500 P~AI ~ HEAT EXC i'i==!=================:I1:======i1
I -~ BYPASS VLV 7 HEAT EXCHANGER n :::~ ::=~F~-~I==~INC
I RELIEF VALVE 3500 PSIG CRACK 3200 PSIG RESEAT
rfr1 "" _t:Cl ,. N:CK FJ ~- !LH=O=!==========P=R=IM=A=R=Y=O=RI=FI=C=EI~~ 38s! 25 PSIG bic. ® ~ J.2 HEAT
(AT PLENUM) .?- I--' ..!. ~
COLD ::.-- n ~ ~ ( COLD HE ) HELIUM SUPPLY ~ '-======!====il REG PREss. SHUTOFF VALVES I ~ 0 TO SOD PSIA to----------- PLENUMW OPIBO~6-00
I ~ ~ VOO
HEATEXCtlf;/lGER POS -L- ---:.L BYPASS ORIFICE BOOST CLOSE l!:i OPEN /" K2-424" /"KOOI6-4OC'\.
ACTUATION CONTROL MODULE LOX VENT VALVE) !Lox VENT VALVE' CLOSE I OP EN J
\ 0 TO 28 v \ 0-28V I CPIBO-09R02-01 CPlBO-09ROI-07 DPIB0-09U02-01
11 • ...1 I SOURCE [nt ) !4D15 '-======~r===~==~
FROM ~CT 465 + 211-15 PSIA "I COLD HE ""~==f'-'-:J=====~============: D ACT 350 +20-15 PSIA(t -- CIP):========='==============.J FILL PORT ~ I LOX TANK REG.
TO CRYO REPRESS SYSTEM D BACKUP PRESS SI
L ____ ...:~~~~~~~~r===-PNEUMATICS
~W 12 JULY 1968 LOX PRESSURIZATION SYSTEM SCHEMATIC-5D3N (MANNED)FLIGHT
DRAWII~G 8.3.3
8-65
8.3.6
SLV AS-503
Propellant Chilldown Subsystem (Drawing 8.3.4) Chilldown of the LOX and LH2 subsystems is accomplished by a
closed loop forward flow recirculation system. Propellant is
circulated from the tanks by centrifugal pumps through low
pressure feed ducts, the J-2 engine propellant pumps, the
propellant bleed valves, and back to the tanks through return lines.
The forward flow chilldown subsystems are activated during
ground operation prior to liftoff and are maintained during
boost to engine prestart. The chilldown subsystems insure
that the J-2 turbopumps are properly conditioned for all burns.
Prior to propellant tank prepressurization and subseQuent burn
repressurizations, the recirculation line shutoff valves are
opened, the prevalves are closed and recirculation flow is
inltiated. At prestart, with the chilldown pumps still running,
trhe prevalves are actuated open, allowing reverse flow,
which removes any trapped gas bubbles from the low pressure
feed ducts.
After engine start the bleed valves, which allow return flow
to the tanks, are closed and the chilldown pumps turned off.
8-66
S·IVB SWITCH SELECTOR
SLY AS-503N
LOX CHILLDOWN PUMP FUEL CHILLDOWN PUMP CHILLDOWN SHUTOFF PILOT VALVE PREVALVE CLOSE COMMAND OFF ON OFF ON ON OFF ON OFF SS 042 SS 121 SS 153 SS 071 SS 125 SS 065 SS 026 SS 151 CHAN 23 CHAN 22 CHAN 59 CHAN 58 CHAN 91 CHAN 92 CHAN 82 CHAN 83
LH2 TANK
I +4041 I ESE '
I INVERTER I I
INVERTER j
\
~ ~ ~ ~ /D2-403" CHILLOOWN ~I-_______ ~/ FUEL \ {FUEL PREVALVE\ {FUEL PREVALVE\ ( FUEL PUMP) FUEL PUMP \
"'\ VALVE I ~ r CHILLDOWN FLOwl I CLOSED I I OPEN I INLET TEMP INLET PRESS. M ~~~~~Zll~~~~nZ~hz~~~~-p==z~ r \ 0 TO IGO GPM I \ 0 TO 113 VDC I \ 0-28V I \ 35 TO (loR \ 0 TO GO PSIA I ~ ~OS NO FLOWMETER ! DPlBO-2H1HII CPIBO-09R02-03 CPlBO-D9R02-Ol DPlBO-19LO1-00 CPlBO-I3-01-OO
ANTI-VORTEX SCREEN
(FUEL CHILL \ DPIBO-09U02-03, Of'IBO-13-01-OO
VALVE CLOSE l- §FJffmZZL~PR~E~VjAL~V~E~~::::~~~~::::~~::::~~::::~I::::~::::~~:dI~ZZ:;::ZZ2Z'zz:;::zz~;;:;;~l =j; \ 0 TO 28 VDC J LH2NO CP lBO-09R08-09 N NO POS I
R'l - BLEED
, /,,(OX:~ANK-----~ V ANTI- :.a-...'::lj ~5::m===E~-jrr===~==m;\l=======lDjl
VORTEX M)~ ~ II II H _ _T. FROM PNEUMATIC ~ SCREEN ~I Lt.=========ii====ii=======~i======[=1==t><~==- POWER CONTROL
( OXIO CHILL \ • '<2 9l"__ II II II R - MODULE
\ 0 TO 28 VDC I NO X:J'::P~OS~I====-::::=========! I VALVECLOSE I PI ~
CPIBO 09R09-05 NO CHILLDOWN ...---. VALVE
/KI09-403 " ...----.....KIIO-~3 P PREVAL VE 'C,p,6n<lr§:~~:!:=:=========II===~ -{
LOX PREVALVE\ {OXID PREVALVE\ J • ;;> F CL CL /KIIO-«I3 " -'#I ~LOWMETER
L-~O~PE~N,-_t-~-t~~CL~OS~E~-~\--§-~ ~~~~~~~~~~ \ 0 28V I \ G TO 113 VDe I F4-424 ACTUATION CO NT MODULE
CP IBO-091l12-06 CP 180-09R02-02 I LOX CHILLDOWN )
/ C4-403 " T [I) \ DT050GPM DP~-o\·r I FLOW
12 JULY 1968
( OXID PUMP "H Of'IBO-21-03-00 IriLEr TEMP §
\ lfiD TO 170· R J l=F~rrJj DPl~2-OO ~
L D3-403"
{ OXID PUMP \
INLET PRESS t-\ OT060PSIA
CP 180-13-02-00 OPI80-13-02-OO
( OXID~ .~ OXIDIZER TURBINE
Jl Jl
PNEUMATICS SOURCE
-ENGINE PNEUMATICS
I!:flNC
MAIN LOX ( ~ VALVE '7--)
)\
GASU GF.NFRATOR
ENGINE PNEUMATICS
I!4iNC
I THRUST \ CHAMBER
MAIN FUEL VALVE
-( FUE~)
~ FUEL TURBINE
MAIN STAGE PRESSURE SWITCH NO 1
MAIN STAGE PRESSURE SWITCH NO.2
1--® ®-7.
K3 I ~ ESE I I :.
Ar-1I--~~K~3-~1~~~~ __ ~·
I I I I I
K61-2
L ________ 1
ENGINE CUTOFF COMMAND
OFF SS 162
I I I I
CHILLDOWN SYSTEM SCHEMATIC-503N(MANNED)FLlGHl
DRAWING 8.3.4 8-67
8.3.7 Pneumatic Control System (Drawing 8.3.5)
SLV AS-503
The pneumatic control system provides supply pressure for all
stage pneumatically operated valves with the exception of J-2
engine valves. A pneumatic power control module filters
ambient helium flowing from the ambient helium sphere and
regulates the sphere pressure of 3,100 ~ 100 psia at 70
+ 10°F down to 490 ~ 25 psia. This pressure is used as indi
cated below:
A. LH2 nonpropulsive vent valves actuation
B. LH2 vent directional control valve actuation
C. LH2 continuous vent orifice shutoff valve actuation
D. LOX tank vent control valve actuation
E. LOX and LH2 prevalves and chilldown shutoff valves actuation
F. LOX and LH2 fill and drain valves actuation
G. 02/H2 burner propellant valves actuation
H. J-2 engine GH2 start system vent valve actuation
I. LOX chilldown pump motor enclosure purge
J. LOX and LH2 turbopump turbines and gas generator purge.
Items A. through J. above are each e~uipped with a separate
actuation control module. Each module contains two solenoid
valves which, on command, exercise on/off control of each
respective valve. The pneumatic control system is protected
from overpressurization by a solenoid valve/pressure switch
combination which serves as a backup to the regulator. In
the event of regulator malfunction causing system pressure
to rise to 600 ~ 15 psia, the pressure switch will actuate
thereby causing the normally open solenoid valve to close.
When the pressure decays to 490 ~ 25 psia the switch will drop
out and the valve will again open.
8-68
LOX FILL & DRAIN VALVE PURGE
o LOX NPV LINE PURGE
u
LHZ CHILL VALVE PURGE
LHZ FILL & DRAIN VALVE PURGE
LOX PRESS SENSE LINE PURGE
o ..: 1!1
LOX VENT & RELIEF VALVE PURGE
II
LHZ NPV PURGE
LOX
LHZ CONT. VENT REG MODULE PURGE
CHILLDOWN MOTOR CAVITY PURGE
I J
BURNER LHZ PROP VALVE PURGE
u LOX AMB REPRESS CONTROL MODULE
LHZ CONT VENT PURGE
6 LHZ AMB REPRESS CONTROL MODULE
+
AMB ~ HELIUM ~1ZJ:=~===~'=::::::;;r::::======~======:=::!.J FILL ~ __
/0156-40i, /0136-403, .] AMBHESUPPLY P/jBHESUPPLY \
SPHERE NO 4 SPHERE NO 4
\ 0 TO 3500 PSIA \ 0 TO 35110 P~A
CPlBO-14-{14-00 DPIBO-14-04-{)I)
AMBIENT HELIUM - P -FILL MODULE , 45 PNEUMATIC
FT3 SPHERE
G
BURNER LOX ESE SHUTDOWN START TANK VALVE VENT PILOT PURGE VALVE OPEN
1 11 I -F
ESE AMB HE SUPPLY SHUTOFF 4015 VALVE CLOSE ~voc
G
ENGIN'E PUMP PURGE CONTROL V.~LVE COMMAND
S-IVB ~WITCH SELECTOR
ON SS 022 , CHAN 24
K47
OFF SS 075 CHAN Z5
®
K72-1 K72 K;tl·1 J I·
D
r ~--r'---~-- oWI-------\w
+4011
"~VOC
PNEUMATIC POWER CONTROL MODULE
'"
® C~ I CONTROL HE , .... __ - ....
r-i REG DISCHARGE LOX 0-6~ P~A I
OBlBO-06-06-OO ---~
/cON THE REG DIS' --I CHARGE BACKUP
\ 0 6~PSIA I
TURBINE SEAL CAVITY PURGE
+ n~
• ~----~ .-:-~ ~~~~~-~90 1? KZl-l PSIA
CPIBO-15-IO-OO - 0
®
NO ~ START TANK VENT I:===!======il PILOT VALVi-::E=~_
'/if 4---{F
ENGINE PURGE CONTROL MODULE
~
T ----4"]
<L c::;
I
SlV AS-503N
START TANK VENT CONTROL VALVE OPEN
S-IVB SWITCH SELECTOR
ON OFF SS 003 SS 43 CH 30 CH 31
+4015 © ® Z8 VDC • ! • 1 K95
----u--=--~ ~5-1
GG PURGE
~ i;n
VDC
P'
LHZ PUMP SEAL CAVITY PURGE
[+
LHZ TURBINE SEAL PURGE
+
...---/D~-403,
I PRESS-ENG , , PUMP PURGE REG I ---_ ~ :ND
~==~~====~==========~========~===~~~F=~-~~~ I~<F==~~==~======~==~P ~ 465 TO 550 IC>OI
,NC -ACT.
~ \ 0 TO 150 P~A I
OF lBO"{!6-08-OO
ESE 5-,-f-------..l
ACTUATION CONTROL MODULE (TYPICAL)
LHZ FILL & DRAIN VALVE
U JULY 1968
II
LH Z DIRECTIONAL VENT CONTROL VALVE
II
LHZ VENT & RELIEF VALVE
II II
LHZ LOX LATCHING FILL & VENT & RELIEF DRAIN VALVE VALVE
PSIA
CONTROL HRIUM SHUTOFF VALVE
II
IL
\I LOX & LHZ PRE VALVES
II
ENGINE START TANK VENT VALVE
LOX & LHZ CHILLDOWN VALVES
, II
LOX VENT & RELIEF VALVE
II
BURNER LOX SHUTDOWN VALVE
130 PSIA --O/ACT 105 PSI A
I II
BURNE.R LHZ LOX LHZ PROP CV NPV VALVE VALVE VALVE
PNEUMATIC SYSTEM SCHEMATIC 503N(MANNED) FLIGHT
DRAWIIJG 8.3.5
8-69
8.3.8 Propellant Utilization (Drawing 8.3.6)
SLV AS-503
The PU subsystem is a propellant mass ratio control device con
sisting of capacitance mass sensors, an engine LOX flow control
valve, and an electronic assembly to enable control. The metering
probes provide capacitance output directly proportional to tank
propellant mass. The changing level of dielectric (LOX or LH2 )
changes the capacitance value of the probe, which is fed into
the PU electronics assembly. The signals from the assembly
position a servomotor which controls the LOX bypass valve on
the J-2 engine within ~10 percent of 5:1 engine mixture ratio.
Propellant residuals can be maintained to less than 575 lb (0.25%)
total usable load.
The sum of the LH2 and LOX potentiometers are fed to a shaping
network. The amplified, modulated signal is applied to a mix
ture ratio servo. The servomotor controls the PU valve position,
varying engine mixture ratio to compensate for tank mass un
balance. PU valve potentiometer feedback nulls the amplifier
output. Additional potentiometers supply telemetry and mass
loading signals.
8-70
LH2 MASS PROBE
- LH2
~ LOX
LMASS 7~_-----, PROBE
FREQ-INVERTCONVERT
~90 TO ,10 CPSI
DhBO-0,-03-0'0 ---/1,23-'1~
(
VOLT-INVERTCONVERT
2lVDC
120 TO 23 5VDC/
OPIBO-O,-O,-OO -\OT05VDCj
DPIBO-09-0S-00 ---
> ""'I--~ MASS RJEL FINE > I I
LH2
BRIDGE
~ : I I I
.> I LH2 MASS I
~I
-~-i----~ L---r----' : H 1
\ : > > : f'XU'2 MASS
'---~~F=E=E~D~BA~C~K-----~J-~.{ > REBALANCE
H
/
r---I-F-E-ED-BA-C-K-------o" 1 :"5~_-r'll -<>-L-O-X.....IMASs
REBALANCE n , I : I
LOX BRIDGE
-/M'-41~
M __ L ____ ~
I
). ~
~ MASS '\
I RJEL } COARSE o TO SV
DP IBOVO 3-0 1-00 ------
K3
VOLT- '1 ..... --1 INVERT -CONVERT
LOX MASS ~
/N3-4~ MASS J I OXIDIZER
::n=r-r- K3-2
. ~--. ~
115 VAC
5 VDC
\ SVDC 4.5 TO S.5VDC'
D,hBO-04-02-00 --49 21
VDC 2.S V SQ WAVE C VDC A
INVERTER/CONVERTER --+®
28VDC 28V FORWARD ESE BATT NO. 2
I COARSE
MASS 0 TO 5V .J OXIDIZER DPIBOV03-03-00 FINE ___
PROPULSION - S-IVB PROPELLANT UTILIZATION SYSTEM
BOILOFF BIAS .....
SHAPING NETWORK
~ I FUEL: BOILOFF\
BIAS SIGNAL I \ 0 TO 15 VDC 7 DPIBQ,-O'-:J!J-oo
+21V
PU ELECTRONICS ASSEMBLY
FEEDBACK SHAPING NElWORK
H
I PU VAL
SLV AS-503N
POS ITI :::,.~ _400 TO
DPIBO-23-0
•
LOX PUMP
~
DRAWING B.3.6
8-7l
8.3.9
SLV AS-503
J-2 Engine (Drawings 8.3.7, 8.3.8 and 8.3.8a)
At engine start command, the electrical control package activates
the following:
A. Spark plug exciters to energize the spark plugs in the
augmented spark igniter (ASI) chamber and the gas generator.
B. Helium control solenoid which allows helium into the pneumatic
control system, closing the bleed valves, charging the
accumulator, and purging the LOX dome.
C. Ignition phase control solenoid which opens the ASI LOX
valve allowing LOX to flow to the ASI chamber, the main
LH2 valve allowing LH2 to flow through the thrust chamber
tubes and injector, and to the ASI chamber.
At the completion of these events there is flame in the ASI
chamber, hydrogen flowlng through the tubes and injector to
conditlon the thrust chamber for mainstage operation, and purge
pressure in the LOX dome to prevent the entry of hydrogen.
Upon expiration of a pre-determined time calculated to allow
satisfactory thrust chamber conditioning, an electrical signal
is sent to open the start tank discharge valve allowing the
start bottle to blow down, thus supplying energy to spin up
the propellant turbopumps. The signal also activates the
ignition phase timer which, upon expiration, de-energizes the
start tank solenoid, closing the start tank discharge valve,
and simultaneously, energizes the main stage control solenoid
which opens the main LOX valve and terminates the LOX dome
purge. As the first stage actuator of the,main LOX valve
moves from the closed position, control helium from the ignition
phase control solenoid passes through the se~uence ports opening
the gas generator valve and closing the oxidizer turbine bypass
valve.
8-72
* SLV AS-503
During steady-state first burn, the start tank which provided
energy for start is refilled from a gas tapoff on the engine
LH2 injector and a liquid tapoff on the main fuel line down
stream of the LH2 propellant valve.
When an engine cutoff signal is received by the electrical
control package, it de-energizes the main stage and ignition
phase solenoid valves and energizes the helium control solenoid
de-energize timer. This, in turn, permits closing pressure to
the main LH2 valve, main LOX valve, and the ASI LOX valve.
The gas generator valve closes and the LOX turbine bypass
valve opens to complete the engine cutoff sequence. Upon
expiration of the helium control solenoid de-energize timer,
the helium control solenoid de-energizes, thereby venting the
helium in the pneumatic control low pressure systems and the
LOX and LH2 bleed valves open.
8-73
CO/'lW'<D S-IYB ENGINE READY BYPASS
COM'l'\NO S - I VB ENGINE START
ON SS 143
CH£:N ... IO
OFF SS 154 S-IYB
CHI'!! 70 SWITCH SELECTOR
ON SS 023
~9
S-IYB OFF
SS 135 DiAN SWITCH
. ~ _27 SELECTOR
~K63_ ~ ~ __ D K57-1
(6 --::- ® ----K§1~.:[~-v-JV-r::! L-________________________________________________ , 4011 I
CONNECTORS INSTALLED
MIS OK PRESS SW NO. I DROPPED wr
MIS OK PRESS SW ~ NO. 2 DROPPED OUT-
"'1:' KS7 I
S-IB/S-IVB
SEPARATION PLANE
y y
K64-1
ENGINE START BOARD
TO EM_
COMMAND S-IVB ENGINE START INTERLOCK BYPASS
ON OFF SS 004 SS 024
CCM'ONENT TEST SPARK SYSTEM
NO. I NO. 2
ASI SPARK SYSTEM ON
~74 ~r75
S-IVB SWITCH
SELECTOR ;~. ~:O
r4~ ______________________ ~ ____ +-~EM
-----~ @ -:: ®
CCM'ONENT TEST HELILM
HELILM ON CONT
® ®
-G:~----;-~II 1.0 sm + • HELIUM
C()\jTROL
DE-ENE"R:'GlZED TJr-fR
I HELILM SOLENOID
_i-r! 0
0
0
~ SPARK CONTROL BOARD
START TPNK
CQIoToIAND FUEL INJ TE/oP OK BYPASS
+28 VDC_ •
SPARE MONITOR_ OXI 01 ZER TURBINE ~ BYPASS VALVE OPEN--
K103_
ENGII'E ,.... START _ r<
ENGr;;'E
~+ ~V_ TO EM_ :.J + }-I---------.-... + ENGINE READY
DISCHARGE IGN PHASE MIS CONT CONT ON CONT ON ON
® ® ® + + +
Cl\I RESET SS 163 SS021 Tll C~~6
HELILM CONTROL ON
IGNITION PHASE ~ CONT ON ~
START TANK DIS-~ CHARGE CONT ON ~
M)NITOR BOARD
/ J
NO. 2 ASI I SPARK EXCITER
"0. I ASI t SPARK EXCITER
NO.2 GG I SPARK EXCITER
NO. I GG J SPARK EXCITER
MIS CONT SOLENOID I
SLY AS-5031l
COWoAND 5- IYB ENGINE CUTOFF OFF ON
MAINSTAGE_ + r.f-~ __ --, CONT ON ASI SP~_ SYSTEM ON
4015
\ 0 TO 28 VDCJ
DPIBO-12U05-01 --i L0----~-¢K;~-~I ;:1 ~ • iV>~.i'-HH----' "~
~ L-+-______ ~---------~~======~~==~~---+__~~---~ IGN PHASE I I CONT SOLENOID
SS 162 SS liS i 13 C""'jL-12 __ t--.
S-IVB SWITCH
SELECTOR
GG SPARK,_ SYSTEM ON
MAINSTAGE OK-~ VALVE CONTROL BOARD
-~- - '-~~E~ 1-------++--41_>1, j KIOI~ ~ 0.45 S~ ~ ~ r-L_-_-... -_-_~~~-=-~., m-- ~ IGNITION PHASE :. 3.3 S J .I-j}-t----..... -----'
DIFFERENTIAL 0.64 S TIMOR SPARKS·
RESISTANCE L~===~~.~ DE-ENERGIZED DETECTOR START TANK DISCHARGE TIMER
DEU>.Y TIMER SENSE REF
PROGRAM'ER BOARD
FUEL INJ'.-{}.-______ r-__ +-__ 4-____ -t __ J TEI'-P OK + I"'
FUEL INJ ~~ TEJ-P -. SENSOR
+4015 DIFFERENTIAL RESISTANCE DETECTOR
REF SENSE CUTOFF
CONTROL NO. I BOARD
~------- ------- ----:>,....
i~AR~------~~ ~ +
I ,- ~ 'r DEPRES~-V ® '" (j) ~
~----), K61-1 IGNITION ~ DETECTOR ~ PROBE
. I +28 ¥DC 1---
+ L _____________ -1 .....-.TOEM
( + LINK
1
TO EM
TO
START TANK I DISCHARGE CONT
SOLENOID
EM TO EM
I: P= CONTROL I CCM'ONENT
.... -------------------START TAN( TEST @
+
CIO CIO
~ LOCKIN
+
~,-,::-::c==>
$ri:T
KIO~ •
CUTOFF CONTROL NO. 2 BOARD
DISCHARGE CONT
SYM30LS
VEHI CLE M::I'IITOR SI GNAL
GROUND M::I'IITOR SIGNAL
FEEDBACK SIGNAL ------__ PRESENCE OF POSITIVE ACTION ------.()o l>SS~NCE OF POSITIVE .ACTJON
~. OR NOT INPUT
-D AND GATE
J:>- OR GATE
---D>- DRIVER
IGNITION CCM'LETE
MIS OK NO. I f,t§ MIl ~ tlft- MIS OK NO. 2
-G--- ISOU>.TlON DIOOE
d><t:&-~U>.~TES SETTING SECONDS S DENOTES PRESSURE BYPASS PRESSURE
SWITCH SWITCH
Propulslon - S-IVB J-2 Englne Electronlc System DRAWING 8.3.7
8-74
(LOX PUMP INLET\
FROM STAG E .= 11 PNEU CONTROL SYS
12 JULY 1968
'-
~ HYD PUMP
• .. I
1
~ {
MAlN OXIDIZER \ VALVE POgTION\
\ OTOlOO% J CPIBO-23-{)J-oo DPIBO-23-{)J-oo
I
-~Q ,Jt=€
II
II u
HEAT EXCHANGER
II
II
II u ..
-•
TO LOX PRESS SYS
FROM LOX PRESS SYS (COLD HE SUPPLY)
-TO GAS -~ GENERATOR
t ;=
TI - -- --t I I -r;= -
-- /OO~'i'.. III
PRESS lb TO LH2 I THRUST CHAMBE~ PRESS SYS
o TO 1000 PSIA 1 OPIBO-I~o-OO -
OP - OPEN CL - CLOSE
NC
t NC 1 NO
I
- ~ CAVITY DRAIN
THRUST CHAMBER JACKET PURGE
1'-iic
II PRESS
ACT FAST SHUT-DOWN
VALVE
~ """Glie
n 1:, I7i:Z';!iSl()j]II[!lJ
'---~rrwJ~ GAS GENERATOR
-~-,,-- ~}GG U ~. ~~~~
FROM GH2 START TANK___ FUEL PUMP
•~DRAIN
~ MAIN FUEL \ VALVE POSITION'
~ oro 1O~ I " CPIBO-23-{)4-!ii"
DPIBO-23-{)4-00
II\. -+
LH2 PUMP
t
-/'C3 .... 03' (
FUEL PUMP \ INLET
\ 3ITO 41 OEGR J OPIBO-19LOI-00
'--""
-/' 1XXl2-403'-..
J FUEL PUMP , INLET PRESS \
\ 0 TO 60 pgA --, CPIBO-134lI-OO OPIBO--I341I-OO
J·2 Engine System Schematic 503 Flight DRAWING 8.3.8
8-75
S-IVB SWITCH SELECTOR I I
MAINSTAGE CONTROL IGNITION PHASE CONTROL HELIUM CONTROL ENG PNEU BOTTLE START TANK VENT PASSIVATION TO HC ENG: SOL VALVE OPEN SOL VALVE SOL VALVE OPEN VENT VALVE OPEN CONT VALVE OPEN START INTERLOCK OFF ON CLOSE OPEN OFF ON OFF ON OFF ON DISABLE ENABLE (RELAY DEENERGIZED SS 157 SS 015 SS 116 SS 057 SS 064 SS 025 SS 101 SS 156 SS 043 SS 003 SS 137 SS 171 AT SIl/SIVB SEPARATION)
SLY AS-503N
L-~~ ____ -+~ ______ ~~ ____ ~~ ________ ~~~~ __ ~~ ______ ~~~ __ ~~ ________ ~~ ____ ~~ ______ ~~ ____ ~~-I ENG CO~~L BUS POWER ENGIN E CUTOFF
& PO COMMAND
CH 15 CH 14 CH 41 CH 40 CH 110 CH 109 CH 21 CH 20 CH 31 CH 30 CH 2 CH 1 U ESE COMMAND
+7 +T ~~~!------ '" OFF ON
E:E~-- =- -= -= ---' _t_--\:U.I;J-;;;i. HOll j~~ ;---'~! ;----h
12 JULY 1968
ESE ESE ~-M- ESE ~-M-~
LH2 TANK
NOTE CONTACTS K58-1, K92-2, K93-2, • K94-2, K95-2, AND K96-2 ARE CONNECTED IN SERIES TO INDICATE PASSIVATION RELAYS RESET PRIOR TO LIFTOFF.
NO
NO
OP
OP
CL
ESEl-.... - ..
LH2 BLEED VALVE
Nob=;-, PURGE VALVE
H
~ ~I
K58-1 I +4D15
f --l T ( K213) K58-2'
MAIN STAGE 0--......... CONTROL VALVE
IGNITION ~ PHASE CONTROL~ ~ VALVE -= I , I
NO
PNEUMATIC POWER CONTROL MODULE
START TANK VENT CONT. VALVE
®I--~
rlNC I
START TANK
BOTTLE HE CNTRL VENT VALVE NC NC VALVE
NO NO
J!--~c c--!l
• LOX PUMP SEAL PURGE
ORBITAL SAFING SCHEMATIC 503N (MANNED) FLIGHT
DRAWING 8.3_8a 8-'75a
8.3.10 Hydraulics System (Drawing 8.3.9)
SLV AS-503
Pitch and yaw control requirements of the S-IVB stage during
main stage burn are accomplished by varying the direction of
the J-2 engine thrust vector. Roll control is provided by
the auxiliary propulsion system. The required gimbal ra~e for
directional control is provided by an independent, closedloop,
hydraulic system, figure 8.3.9. Gimbal forces, provided by
two electro-hydraulic servoactuators, are available during
J-2 engine firing (hot gimbaling) or non-firing (cold gimbaling).
Engine position is proportional to the electrical input command
signal to the servovalve in the actuator. The actuators can
extend or retract separately or in unison.
The hydraulic system consists of five major components mounted
on the engine and/or stage structure and are connected by metal
tubing and teflon-lined flexible hoses, drawing 8.1.7.
The five major components include:
A. Engine-driven hydraulic pump
B. Auxiliary pump
,C. Accumulator-reservoir assembly
D. Yaw servoactuator
E. Pitch servoactuator
Depending upon mode of operation, hydraulic power for gimbaling
the engine is derived from the engine-driven pump and/or the
auxiliary pump and may be supplemented by the accumulator.
~.10.1 Engine-driven (main) hydraulic pump.- The engine-driven hydraulic
pump provides the high flow rate required to gimbal the engine
at a rate as high as 15 deg/sec. The pump is a yoke-type,
variable displacement pump with a flow rate of 8 gpm at 8,000 rpm
and 3,550 psia nominal pressure. The pump, mounted on the
8-76
SLY AS-503
LOX turbine gas collector dome accessory pad, is powered by
a crown-spline ~uill shaft extending from the turbine shaft
to the pump.
8.3.10.2 Auxiliary hydraulic pump.- The auxiliary hydraulic pump is a
fixed angle, variable delivery pump with a rated flow of 1.5 gpm
at a minimum of 3,500 psia. The pump is driven by a 56 Vdc
motor re~uiring either a ground service power or stage power.
The motor cavity is filled with dry air. This air maintains
a positive pressure within the motor to prevent excessive
brush wear and transfers motor-generated heat to the hydraulic
fluid. This heat thermal conditions the fluid during prelaunch
propellant loading operations and during the orbital coast
phase. For the coast phase, the pump turns on 172 minutes after
first burn cutoff and operates for 8 minute heating and
circulating the fluid.
8.3.10.3 Accumulator - reservoir assembly.- The accumulator-reservoir
assembly is a combination nitrogen gas powered piston type
accumulator and a differential piston type reservoir. The
accumulator stores the system high pressure fluid supply when
the pumps are operating and reduces pressure surges and
pulsations. It also furnishes hydraulic flow to supplement
the pumps during excessive actuator demands. The reservoir
stores the system low pressure fluid supply, acts as the
system fluid heat sink, and provides initial inlet head to
the hydraulic pumps for starting.
The accumulator-reservoir is the moving piston type. The
accumulator side of the assembly has two coaxial pistons
with vented seals. The gas side is precharged through the
gaseous nitrogen fill valve with gaseous nitrogen at
8-77
SATURN S-IVB
ENGINE DRIVEN HYDRAULI C PUMP'
8 GPM AT 3650 PSI 8000 RPM
28 VDC
K5-1
MAIN ENGINE DRIVEN PUMP MODULE
HYDRAULIC SYSTEM SCHEMATIC
[ :: J PRESSURE
t:l C RETURN
~fLEX LINES
COMMAND AUX HYD PUMP fLIGHT MJDE
Off SS 074
CHAN 29
GJ S-IVB SS 174 SWI TCH
CHAN 28 SELECTOR
56 VOC
TEM"E RA TURE RESERVOI R 01 L
OVERBOARD DRAIN
BALANCED RELIEf IIVALVE (CRACKS
AT 275 PSIG)
LQ-PR SERVI CE QUICK DISCONNECT IXb-=::an
HI-PR SERVICE QUICK DISCONNECT
COUNTDOWN - THERMAL SWITCH (LOW TEMP) ("NO GO" AT -15°f)
AUX HYD PLMP ASSY
1.5 GPM AT 3650 PSI
PUMP CASE DRAI N
AUX PUMP MODULE
1500 TO ~500 PS~A
DPIBQ-13-05-00 ~
PSI)
1500 TO 400 PSIA
~IBO-IH6-to ~
Propulsion - S-IVB Hydraulic System
PISTGJ POSITIGJ
AI R CONTEr rT:;ES!lTc:~~RI!lQsIZiDm~;;~t ...
RESERVOIR HYDRAULIC PRESSURIZATIGJ PISTON
RESERVOIR PNEUMATIC
PRESSURIZATlf PISTON e.:;::~
ACCUMULATOR NITROGEN PRESSURE GAGE
ENG Yi>l.1 PLANE POS I
±7.5 DEG I
DPIBO-23-02-00
'-----"""
ACTUATOR MODULES
SLV AS-503N
FIGURE 8.3.9
8-78
SLY AS-503
2,350 ~50 psia at 70° F, and is monitored by a 0 to 4,000 psig
gage. The inner piston serves as a pneumatic ram to provide
reservoir pressure at the auxiliary pump inlet, thus preventing
cavitation during start. The reservoir is pressurized to 170 psig
by the "bootstrap" action of the accumulator fluid during
operating periods of the pumps and to 63 psig by the pneumatic
action of the accumulator gaseous nitrogen during non-operating
periods of the pumps.
8.3.10.4 Pitch and yaw servoactuators.- Two servoactuators, located 90°
apart with respect to the longitudinal axis of the S-IVB stage
provide pitch and yaw control.
The hydraulic servoactuators are piston type, linear, double
acting units capable of delivering 42,000 Ibf at a pressure
of 3,650 psia in the extend or retract position. They are
positioned by commands from the instrument unit and can operate
separately or in unison. Mechanical feedback on each actuator
indicates the position of the piston.
8-79
8.3.11 Auxiliary Propulsion (Drawing 8.3.10)
SLV AS-503
The auxiliary propulsion system provides attitude control for
the S-IVB stage during all operational phases and provides
propellant settling thrust just after J-2 engine cutoff and
prior to J-2 engine burn. System components are contained in
two separate modules placed 1800 apart on the aft skirt. Each
module contains a cluster of liquid bipropellant hypergolic
engines, a positive expulsion propellant feed system, and a
helium pressurization system. The engine cluster in each
module consists of three 150 Ib attitude control engines and
one 70 Ib ullage settling engine.
The APS modules receive command signals from the IU and per
forms the following functions:
A. Roll control during J-2 engine burn.
B. Attitude stabilization after J-2 burn.
C. Maneuvering attitude control.
D. Propellant settling (first and second burn cutoff and
second and third burn start).
The instrument unit provides all firing commands. These
commands actuate fuel and oxidizer solenoid valves to release
hypergolic propellants to the engines. Roll deviation is
corrected by firing an engine in each module, both simultaneously
in opposite directions. Yaw correction is accomplished by
firing two engines simultaneously, one in each of the modules,
in the direction opposite the error. Pitch correction is
provided by firing one of the two APS pitch engines in the
direction opposing the error. (Pitch and yaw corrections are
provided by the APS only when the S-IVB stage, J-2 main engine
i~ in the non-operational mode.) The engines operate in
short pulse type bursts ranging from 65 milliseconds to as
much as required. The APS ullage (propellant settling) rockets
8-80
SLV AS-503
(one in each module) are first enabled during the J-2 engine
first burn cutoff. Firing continues for approximately 87 seconds,
through the engine cutoff transient decay and the activation
of the LH2 tank propulsive vent system. The ullage engines
also fire for 17 sec after second cutoff. This assures that
the LOX and LH2 propellants are positioned aft in the S-IVB
stage tanks during coast. The APS ullage rockets are again
energized at the end of the two coast periods prior to restart.
Propellant settling is thus assured to provide liQuids to the
pumps during the chilldown process. It is noted that propellant
settling for first burn start is provided by another propulsive
system and is explained in subsection 8.3.3.
8-81
SLY AS-503N
TVP ATTITUDE CONTROL RELAY MODULE
~~~~4~Dl~,2~1,~.~.~~~
CONTROL
PITCH POSITIVE
PITCH NEGATIVE
COMMAND
3/P
liP
__ __ QUAD II , 03S-.IS"Yr,g ~ /037-4lf' CHECK
_~ROLL NEG PRESS HElIUM _ tl PRESS HElIUM' VALVE
~_3 12 ~3/2 2-:1 REG 000 II r= REG MOD I I ~ I-
liP , I 3/P \ 0 - 400 PSIA I m 0 - '00 PSIA I 'ij m: ON SS 136 CHAt! 42
70 LB ULLAGE ENGINES COI.l:.lAND OFF ON COICt4AND
NO.1 SS 176 SS 066 NO 2 CH~~ 43 ~';!. ~N 101
OFF SS 046 C~~102
---d ---- --- -- ~-«M ~ < ~iiiL,
---- - ________ I--_L_~ o---J K3 L.
- -- ---- --- --+- ._-~K4L,
ROLL POSITIVE 114&3/2
ROll NEGATIVE 112 & 3/4
YAW POSITIVE 1/4 & 3/4
YAW NEGATIVE 1/2 & 3/2
ULLAGE POSITIONING llU & 31U
1-2 I 1IU},,·r---+---1~3/U III r;l~g=ll=~~ CPlBO-\3-ij8~ I ~
1---==--'------+----'.:-----1 '~2 ~ I \ DPlBO-13-j)8-00 - - - .. - PRESSURE MONITOR, AMBIENT SENSING I 11 1(9-1
1-1 114 2_4 314 2-3 ~ ~ ORT DD7 I PORTS .M: I 1-4 I ~ ~ r1' ' 4D13 K9 ~ K9
IV ROLL POS I I WI. 'I' !- -HELIUM PRESS • ri*t-. Ip- f.iL-r _____ ~~~~~~~~~~~V.;.;IE;;.;W.-...;.F.;.;RO.:;.;,;;M..;A,;;F..;T.. ~ ~ REGULATOR PRESSURE MONITOIt-;,.,1 -- - ®.
fliGHT CONTROL COMPUTER QUAD ,-.f"\ PORT CC"",",\ \!::I R CHECK : -= MCl12-3 FUEL ~ ~ ;;-
CMD CfoII CMD CMO CMD VALVE '--• =II BLADDER COLLAPSE.. II = IIIp I~I~I IIIIV Ip III & VENT ~ . -r. ;
K12-1 * I
~:-\--~ © ~®
~TOMOOULE NO 2
HE LOW PRESS MOD I 4~~~~~ :~ ~ ~ (PRESS HELIUM \ HELIUM {PRESS HELIUM \ I l!'-=i::::' ~~~=~ MC172-4 OXIDIZER
: I SUPPLY MOD II SUPPLY MOO I I I. BLADDER COLLAPSE & VENT FUEL :: 0 - 3SOO PSIA ~~: 0 - 3500 PSIA I :
~_J 3 C 2
r.-. TO ROll A ~ ANDYAW
'--.,-----~I MOTOR '-----'I-....J MOTOR VALVES
RELAY MODUL[
, +
RELAY MODULE .-
RELAY MOOULE
T,
RELAY RELAY TANK I: IJ'~4 -100 DP~-l3-j)J-I!l II i MODULE MODULE I __ . __ I
HE LOW PRESS. MOD
I I ,CIS7-41S" PSIA /e23-.I." : I T GROUND T I ~ I TEMP HELIUM \ &., j::: I f TEMP HELIUM' \.:,L, OXIDIZER
FLUSH aUD H~~----""'i i-' MOO II V .IJ---;i- 000 I I ~ 'I". TANK 1M! GROUND (TYPICAl)
12 JULY 1968
.-l. /KI34-404"'>..
EvENT 1\ APS ENG 2-112-3 FO VLV OPN
\ OT05VOC J CPlBO-26-OO-j)O DP IBO·26-OO-OO
-/0,0-41.'
(PRESS-FUEL \ MAN APS I I-
\ 0 TO ')0 PSIA OP IBO~Ol-02-00 ---~
PRESS-FUEL \ I
MAN APS II t-J \ 0 TO '00 P~A J DPIBO-j)H'~ -
\ OTOSVDC 7 CPJBO-2'-00~ OPIBO-24-OO-j)!
~ EVENT \
( APS ENG ~:.2 FO VLV OP. OTO 5 VDC
CPJBO-27~~ OPJBO-27~~
~
(TEMP 'UEL , MODI l-
'60 TO 590° R J CP 180 -1I-j)6-OO O"'IBO-II-06~
~ TEMP FUEL \ MO~ II l-
\ 460-590° R I CPIBO-IH7-OO DPlBO-11-j)7-OO
~ ( PRESS-APS I-I \
\ OT0200PSIA J CPIBO-17-OO-OO --
, TO MOTOR VALVES
"" - mom I [..,. \ m066O'R I JI~~~~=~;;;;;;;;,"~~=!i=:FLUSH AND IN FIN III APS MODULE VENT OUTLET BUBBLE IPl[l!HlJLOl;,IIO':" OP~-J1~-OO VENT OUTlET
FUEL 12 TRANSF~
fA1: TO -= ESE -
FUEL LINE PURGE
GROUND REMOVAL - [~ I ~ ~ BUBBLE 1=] FUEL [ l ~...... ~ rml- REMOVAL
RECIRCULATION (TEMP OXIDIZER _~ I f PRESS HE , TO " I ~ GROUND MOO II HEUUM 'i SUPPLY MODI J ESE ~nt===crl:D===mi~;}OXID
(PNEU)
If -/071414"'>..
PRESS-OXIO MNi\ MODI .-
'I~ TO ESEJl
FUEL CONTROL MODULE
\ 460"TO 590"R I FILL \ 0 TO 3500 P~A I I RECIRC CPJBO-ll-j)s-uJ CP~-J3-0).-lIO
IJ'JBO-ll-j)s-uJ OXID ~ OXID LINE \ OT0400P~A
DP laQ-j)7-J!l-OO ,C'iiHi1'... ~ CONTROL~rm;~mrlIIIJ$mr==:n:ciIqg PURGE frEMP.2;.IDIIZER \ f PRESS HE' MODULE r'3 I !::l (PNEU) _ I - I- -( lIJPPLY MOD II I -A Fl OXID /m:l-415'
DE' JOO-11-j)4~ \ 0 TO 400 P~A J \:::O~~:;::( ~;~~~J [I~'~E I ~TRAN~pSrF_E_R_~(F~~~S~I;_O_XIO_M.,-Ni-1N\-
~ ~ DP~
~ m J ITO MODULE NO 1 I ~
~~Zf6zIr~~~~,~~r2~2~2~2~'2~,~~:r~2~22~?~?~lhzzzu~~~~,i'~!!~II~!!~I~~!I~~.~~I~~"~!!~!I~!!~I!~I!~I!~lnl~l:i~!!J~~~,~~~~~~~~f:~~~~~,~~~~~,1t~~~~tl~~~~::TITITITITTI::::~Ncr====~~~~~~~\:~~~~~~ ~ E ---#--- f
~ )!'f11-- NC N C - - fI'I!I", ~"'= "'=(9
.? ~--- NC NC~ --~ ~-- Ne NC ~ --.f@ <D'!--- NC N: -t'fu @"t-- NC NC --.r@ Z lID~:. @t-~ NC N~~ --.f® ~ -- NC NC --:f1'1. J!T!t-- NC NC --ft J!fI1.-- NC NC -:ffRl. .fl'll-- NC NC --P!l _- NC NC __ A'm I J!fll--- NC NC -:1!"'l. ft--- NC NC --fl o " -= <.!) (!) -= -= ® CD -= -= <.!) (!) -= -~ -= ® - f· . W 0 -= ~ -{ "<.!) ® -= ~ '" ®
~ , ~ / ~ ~, /~ i.2 ~ " ,., / /oiHJ5' J .\ "<2ZZj II: :®' .\ J ., ,., n: lY ( PRESS ULLAGE\ ~ULLAGEfpRESS ULLAGE\ ~ ~ f :\
PRESS-APS 2-J \~ -mROLL AND PRESS-APS 1-2 l PRESS-APS 2-2 t-:]l Jii'I':PITCH CHAMBER MOO I I P )MOTOR" CHAMBER 000 II I ROLL A:N:g~ I PRESS-APS 2-3 l \ 0 TO 200 ~SIA J ) YAW \ 0 TO 200 P~A I \ 0 TO 200 PSIA I ILJ.) MOTOR 0- 200 PSIA I ( \ 0 - 100 PSIA I Y Ail P \ 0 TO 200 P~A I CPIBO-J1~-OO MOTOR CPJBO-JS~-OO CPJBO-2J-OO-j)O DP~-j)s~-oo 1-4 2-4 DE'1ll9-lJ8~-OO MOTOR I CP~-22:5ll-=OO
- 1-1 2-1 - --- 1-2 2-2 T -r- 1-3 2-3
AUXILIARY PROPULSION SYSTEM - 503N FLIGHT
DRAHING 8.3.10
8-82
*
Figure 9.1
To be provided later.
9-3
SLV AS-503
* SECTION 9
EMERGENCY DETECTION SYSTEM
9.1 GENERAL NOTES
To be provided later.
9-1
SLV AS-503
9 EMERGENCY DETECTION SYSTEM
SLV * AS-503
9.2 SC-SLV INTERFACE REQUIREMENTS
To be provided later.
9-2
*
Figure 9.2
To be provided later.
9-4
SLV AS-503
*
Drawing 9.2.1
To be provided later.
9-5
SLV AS-503
*
Drawing 9.2.2
To be provided later.
9-6
SLY AS-503
*
Drawing 9.2.3
To be provided later.
9-7
SLV AS-503
*
Drawings 9.2.5 through 9.2.10
To be provided later.
9-9
SLV AS-503
*
Drawing 9.3.1
To be provided later.
9-14
SLV AS-503
SLY AS-503
9.3 S-IVB RANGE SAFETY SYSTEM
9.3.1
The flight termination system consists of a range safety
antenna subsystem, two secure command receivers, two range
safety controllers, two secure range safety decoders, two
exploding bridgewire (EBW) firing units, two EBW detonators
and a common safe and arm device that connects the subsystems
to the tank-cutting charge. Electrical power for all elements
appearing in duplicate is supplied from separate stage batteries.
Range Safety (Drawings 9.3.1 and 9.3.2)
The antenna subsystem consists of two folded-sleeve antennas
mounted on diametrically opposite sides of the stage.
Longitudinally, both antennas are mounted at the midsection
of the forward skirt. The two antennas are individually
connected to a hybrid ring power divider by coaxial cables
of eQual phase length. The power divider is a 3-db hybrid
ring in a strip line assembly that separately supplies sum
and difference-signals to a directional power divider.
The directional power divider is essentially a 24-db directional
coupler and a power divider combined into one strip-line
assembly. Its function is to provide a means of applying a
secure closed loop checkout signal to the receivers from the
GSE. Two outputs of the directional power divider are separately
applied to two secure command receivers.
The antenna radiation pattern coverage is basically omnidirectional,
providing adeQuate gain over 96 percent of the spherical solid
angle representing ground station look angles during powered
flight. The station losses are approximately 3 db and the
SUbsystem VSWR is 1.5:1.
Each secure command receiver is a double conversion, crystal
9-10
SLV AS-503
controlled, solid-state, super-heterodyne frequency-modulated
(FM) receiver having two isolated audio outputs of a nomlnal
I-volt rms level with a bandpass characteristic of approximately
300 cps to 250 kcs. The receiver has an internal power supply
to provide power, isolation, and regulation.
Commands to the secure system consist of a message format of
two words; an address word and a command word. The address
word consists of nine characters; the command word consists
of two characters. Thus, the total message comprises eleven
characters. Each character consists of two simultaneous tone
pairs in the range of 7.35 to 13.65 kcs as follows: 10th 11th
Command Character Tones Character Tones
A. Destruct 1 and 2 1 and 3
B. Fuel Cutoff 2 and 3 2 and 4
C. MSCO/ASCO (Saturn Spare No.1) 4 and 5 4 and 6
D. Spare No. 2 3 and 4 3 and 5
E. Safe 5 and 6 5 and 7
The decoder accepts the demodulated tone pairs from one of
the audio outputs of the receiver. Seven tone filters and seven
threshold detectors detect the presence of a particular tone
and establish a decision level. The data is processed through
21 AND gates to the input of a code plug. The code plug sets up
the chosen code-of-the-day configuration and unscrambles the
code for use by the sequencer register which determines if
the address is correct and sets up the enabling circuits to
accept the command. If the address is wrong in timing or
sequence, the enable circuits are inhibited and the unit resets
to wait another address. If the address is correct, the com
mand word is processed through the filters and enables the
9-11
SLV AS-503
closing of the appropriate relays which supply 28 Vdc power
to the controller.
The code plug supplied with the decoder is a "test" plug and
will be exchanged for a "code-of-the-day" plug upon arming
of the vehicle.
The receiver and decoder are supplied by 28 Vdc from either
a ground source (external) or by an internal source. The
source used is determined by the setting of a relay in the
range safety controller.
The range safety controller is a relay package that controls
the input to the receiver power supply and the output of the
receiver and provides inputs (charge and fire) to two range
safety EBW firing units.
Output of each EBW firing unit is fed to the EBW detonators
on one side of an electromechanical safe and arm device. When
in SAFE position, the device prevents accidental activation of
the range safety ordnance devices during prelaunch activities.
The safe and arm device arms the range safety flight termination
system on command by aligning two explosive leads with explosive
trains. The tank-cutting charge leads are connected to the
various destruct ordnance devices located on the S-IVB stage.
The safe and arm device consists of a 28 Vdc solenoid-operated
unidirectional shaft that contains two explosive charges placed
in SAFE or ARM position when the solenoid is activated. The
shaft is mechanically attached to the solenoid by a ratchet
and is powered through 90° of clutch travel by the solenoid.
At the 90° point, power is removed from the solenoid by a
CAM-operated microswitch. The solenoid then returns to the
starting position, because of the ratchet action of the clutch
and is held in this position by a spring-loaded detent. Each
9-12
SLY AS-503
subsequent application of power causes the shaft to rotate
90° clockwise. SAFE to ARM to SAFE, et cetera. Prior to
launch, the safe and arm device is set to ARM position by
ground support equipment in the blockhouse. After umbilical
disconnect during launch, there is no control of the safe
and arm device.
Ground initiated commands are transmitted in the form of
tone signals. The tone signals are received by the receiver
and decoded by a decoder network which energizes relays In
the receiver and range safety controller. The relays supply
28 Vdc for the destruct arm cutoff, destruct, and turnoff
events.
The Destruct Arm/Cutoff command word activates a relay in the
range safety controller. The controller relay actlvates the
engine cutoff circuits in the sequencer thereby cutting off
the engine. At the same time, power is supplied to the range
safety EBW firing unit storage circuits, charging the units.
The system is then ready for a destruct command.
As a result of the destruct command word, 28 Vdc is routed
from the range safety receiver controller to the trigger circuit
in the EBW firing units, thus ending the stage flight and
dumping the remaining propellants overboard. If no destruct
command is generated (successful launch), the turnoff command
word is initiated. Controller response to this command ener
gizes a series of relays, switching the system from internal
to external power position, thus cutting off power to the range
safety flight termination system and thereby returning it
to safe state.
9-13
*
III
Drawing 9.2.4
To be provided later.
9-8
SLY AS-503
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* SECTION 10
INTERFACE SYSTEM
This section will be provided at a later date.
10-1
SLV AS-503
t01NTERFACE SYSTEMS
MSC-1514-69