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'JET PROPULSION LABORATORY
California Institute of Technology
Pasadena, California
This work wa. performed for the Jet Propulsion Labor-atomy,
California Institute of Technology, sponsore_ by the
National Aeronautics and Space Adm_i_'_o_ under
Contract NA_7.100.
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https://ntrs.nasa.gov/search.jsp?R=19680009921 2020-03-24T22:42:03+00:00Z
SRS TECHNICAL REPORT
TR-DAI522 A
JPL CONTRACT 951290
DESIGN STUDY OF THE JPL S-BAND
TURNAROUND RANGING TRANSPONDER
FINAL ENGINEERING REPORT
1 November 1967
Submitted to:
JET PROPULSION LABORATORY
California Institute of Technology
Pasadena, California
This work was performed for the Jet Propulsion _,California Institute of Technology, sponsored by the
National Aeronautics and Space Adminlst_tlom tmde_Contract NAS7-100.
Prepared by:
PHILCO CORPORATION
A Subsidiary of Ford Motor Company
SRS Division
Palo Alto, California
PHILCO.I=O _ _ CORPORATION
SDace _ _B-entry
Systems Division
Section
1
2
4
pKEGEDING "PAGB BLA_, I_IOT: FIU_ED.TR-DAI522A
TABLE OF CONTENTS
INTRODUCTION
SLH_IARY
2.1 Original JPL Transponder Design Deficiencies
2.2 Phase I
2.3 Phase II
2.3.1 Ranging System Evaluation
2.3.2 S-Band Phase Evaluation
2.3.3 Analysis and Study
2.3.4 Recommended Changes
EVALUATION TESTS (Phase II)
3.1 Transponder Overall S-Band /"VCO"/ Ranging
Phase vs Temperature
3.1.1 Entire Transponder
3.1.2 Six Packs (3)
3.1.3 Individual Modules (13)
3.2 Diagnostic Tests
3.2.1 _dule
3.2.2 Special
ANALYSIS AND STUDY (Phase II)
4.1 Ranging Delay and Ranging Delay Variation
4.1.1 Ranging Delay due to Interstage
Coupling Networks
4.1.2 Delay Variation Produced in the
Demodulation Process
I-i
2-1
2-1
2-3
2-5
2-5
2-6
2-6
2-7
3-1
3-1
3-9
3-15
3-32
3-55
3-55
3-78
4-1
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4-4
4-13
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TR-DAI522A
TABLE OF CONTENTS (Cont 'd)
Section
4.2
4.2.1
4.2.2
Transponder Phase Relationships
General Relationships
Ranging Delay Produced by VCO
Crystal Temperature Characteristic
4.2.3 "Cog" Phase Jumps
4.3 Frequency Ratio Study
VIDEO AMPLIFIER
5.1 Functional Description
5.2 Specification Requirements
5.3 Problems in Mariner C Design
5.4 SRS Module Design
5.5 Test Data
5.6 Comparison with Mariner C Module
CONCLUSIONS AND RECOMMENDATIONS
6.1 Discussion and Review
6.2 Recommendations for Future Work
4-18
4-18
4-21
4-24
4= 27
5-I
5-1
5-1
5-3
5-6
5-6
APPENDIX (PHASE IX)
I
IV
V
VI
VII
IpH,-=oj pHIL.I=O.FOR O CORPORATION
Phase Shift and Group Delay vs Detuning for Single
and Transitional Coupled Double Tuned Filters
Demodulations of a Trapezoidal Phase Modulated Carrier
Delay Produced in the Demodulation Process
3.1 Distorted Ranging Signal
3.2 Detector Reference Signal
Spectrum Analysls of a Trapezoidal Modulated Carrier
Transponder Phase Analysis
Frequency Ratio Study
Ranglng Test Information
iv
A.I-I
A.2-1
A.3-1
A.3-5
A.4-1
A.5-1
A.6-1
A.7-!
Space I_ ReentrySystems Division
SECTION 1
TR-DAI522A
DESIGN STUDY
OF THE
S-BAND TURNAROUND RANGING TRANSPONDER
FINAL ENGINEERING REPORT
1.0 INTRODUCTION
JPL Contract 951290 provides for a design study program of the JPL S-Band
Turnaround Ranging Transponder directed toward improving the Transponder
performance. The program was divided into two parts: Phase I and Phase II.
The required overall effort is divided into three broad areas which include:
ae A review of all the transponder circuitry directed toward
improving the unit's performance, stability, efficiency,
and reliability.
b, A detail analysis of specific transponder problem areas which
have evolved through previous use of the unit in the Mariner
C Mars Mission.
Ce Transponder in-lock ranging and S'band carrier phase
stability as a function of temperature, using JPL-supplied
transponder.
The "Interim Engineering Report," WDL-TR3066, provides the results of the
/
I-I
DHILCO-FO_Q CC)RPO_ATDON
Space & Re-entrySystems Div|s|on
TR-DAI522A
Phase I effort which accomplished "a" and %" above. Included is a complete
presentation of the design investigation, analysis and testing accomplished
in the Phase I effort.
This 'Tinal Engineering Report" provides a summary of the Phase I effort plus
the results accomplished in "c" above.
1-2
l -col _HILCO-_Om 0 _Om POTATION
Space & Re-entry
Systems [Division
j-
i
TR- DA15 22A
SECTION 2
SUMMARY
2.1 ORIGINAL JPL TRANSPONDER DESIGN DEFICIENCIES
The original JPL S-band transponder was developed during 1962 for an S-band
Mariner-Mars Mission in 1964. Some of the circuitry was left identical to
its L-band predecessor designed in 1959. Although the transponder has per-
formed exceedingly well, there have been a number of problems which have
occurred during calibration, test and mission operation. In addition, many
improvements have been made in component technology and reilabilitywhich
should be incorporated to update the design.
Of specific concern are the following items which have received specific
attention during the program:
l•o Self lock - the mechanism by which the Transponder
receiver is caused to phase lock onto a Transponder-
generated signal when the turnaround ranging module
is turned on was studied and analyzed.
e Turnaround ranging response - the turnaround response to
modulation was analyzed for purposes of both improving
the phase stability over the operating temperature range
and providing reproducibility from unit to unit.
. Modulation bandwidth - the •required modulation bandwidth
was difficult to achieve and required very careful and
time-consuming alignment of the exciter stages.
2-1
IpxL=oj pHILCO.FC)_ 0 CO_P_ATI_N
Space & R_ntrysystems Division
TR-DAI522A
. Phase modulator - the sensitivity and stability of the phase
modulator was studied and methods for improvement recommended.
. Automatic galn control (AGC) - the AGC circuits and the AGe-
controlled circuits were analyzed to improve performance and
stability over the operating temperature range.
. Receiver best-lock-frequency drift - the receiver best-lock-
frequency which drifts extensively with time and temperature
was studied and improved.
. Auxiliary oscillator frequency - the auxiliary oscillator
frequency was sensitive to the value of the transfer command
voltage.
. Power supply and monitor point lead filtering - the power
supply and monitor point lead filtering and decoupling was
analyzed for possible reduction in low-frequency feedback and
radio frequency (RF) leakage.
. Varactor multipliers - the design of the varactor multipliers
was analyzed to improve the reliability and minimize spurious
outputs from the exciter.
10. Part Selection - by adequate design and tolerance analysis,
a reduction in the number of parts which required selection
of parameters during the assembly and testing phase was made.
Ii. Receiver noise figure - the receiver circuitry was analyzed
to reduce the receiver noise figure within the constraints
of the conventional circutry now used.
12. Component type reduction- where possible by adequate design,
a reduction in the number of types of components required was
ma_e .-2-2
p_.I|LCO.FO R D CORPORATION
Space & ]::_e_ntrySystemm [_ivi_ion
S
TR-DAI522A
In addition to the detailed analysis of these specific transponder areas a
review was performed of all the transponder's circuitry. This effort was
directed toward improving the units performance, stability, efficiency,
and reliability.
2.2 PHASE I
Phase I of this program was divided into two major areas of detail module
design and transponder system analysis.
Table 2-1 provides a summary of the module study, design, and test efforts
completed.
The transponder system analysis, design, and test was divided into five
major areas as follows:
a.
b.
C.
d.
e.
Transponder Self-Lock
Ranging Delay and Bandwidth
Automatic Gain Control System
DC Power Considerations
Reliability Improvement.
Specific details of the Phase I effort are included in WDL-TR3066, "Design
Study of the JPL S-Band Turnaround Ranging Transponder, Interim Engineering
Report" dated 19 September, 1966.
2-3
[ pHILCO _PHILCG-FO_O _o_pO _ATIQN
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TR-DAI522A
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TABLE 2-I
/
S-BAND TRANSPONDER DESIGN STUDY PHASE I MODULE EFFORT ACCOMPLISHED
Module Analyzed Tested RedesignedAnd Tes ted
Mixer Preamplifier
47 Mc IF Amplifier
9.56 _ IF Amplifier
Phase Detector
AGC Detector
Frequency Divider
VCO
X36 Multiplier
Auxiliary Oscillator
X30 Multiplier
Isolation Amplifier
Video Amplifier
X
X
X
X
X
X
X
X
X
X
X
X
X
X
X
X
X
X
CZ)
X
X
(2)
(2)
X
(i) Mixer Portion Only
(2) Oscillator Portion Only
PH|LCO.POR O C(_I ._O _ATt (_N
2-4
Space & ReentrySystems [Division
TR-DAI522
/I
2.3 PHASE II
A major part of the Phase II effort was spent in a test program with the
purpose of evaluating and isolating the causes of S-band carrier phase
shift and ranging delay variation in the Mariner C transponder, as a
function of temperature.
In addition to these tests, specific diagnostic tests were performed on
several of the modules.
The principal goal of the analysis and study effort was to relate the
ranging delay and S-band phase temperature data to transponder circuit
functions. In addition to this, a study was made to determine the optimum
transmlt-to-recelve frequency ratio, from the transponder viewpoint, for
the proposed change in the DSIF band occupancy.
Finally, an SRS version of the Video Amplifier was developed as part of
the Phase II effort.
2.3.1 RanEinz System Evaluation
Measurements show that the major cause of ranging delay variations in the
JPL Mariner "C" transponder under temperature varying conditions is due to
the following two conditions:
a.
b.
Distortion of the ranging signal.
Variation in the alignment of the ranging detector reference
phase relative to the carrier.
The combined effect of these two conditions is to produce an incremental
range delay that varies nonlinearly as a function of the misalignment.
2-5
IPHLCOI PHILCOoFOR _) CO;t PORATION
Space £, ReentrySystems Div|aicn
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TR-DAI522
The major cause of distortion is due to reactive loading at the second
mixer, due to the input impedance of the crystal filter. The 9.56 MHz
I.F. Amplifier is the major cause of reference phase variations in the
ranging detector.
2.3.2 S-Band Phase Evaluation
Measurements show that the S-band Phase shifted fairly linearly with
temperature in the case of the entire transponder. The total variation
throughout the temperature range is 22.2 cycles.
Four modules were mainly responsible for the phase shift.
order:
ao
b.
C.
d.
VC0 and X3 Multiplier (13 cycles)
Aux-Osc., Mod., and X4 Multiplier (5.1 cycles)
X30 Multiplier (4.4 cycles)
X36 Multiplier (3.5 cycles)
These are, in
The large variation in S-band phase caused by the VCO was not expected.
One reason for the large variation is due to the fact that the phase
multiplication following the VC0 is 120 times.
The results of the S-band phase measurements are summarized in Table 2.3.1-
2.3.3 Analysis and Study
The analysis and study efforts combined with the various measurements made
in the program indicate that:
2-6
I, PHILCO 1_PH|_=CO*FO RO CORPQRAT_ON
Space _ Reentry6ystern_ Division
TR-DAI522
/3
a. Group delay in RF stages due to bandpass interstage coupling
networks, and phase shift of the fundamental component of thet:
498 KH z square wave in video stages, is responsible for almost
all of the measured ranging delay time in the transponder.
These are normal, unavoidable delay phenomenon and result mainly
from bandwidth limiting requirements.
bo Ranging delay variations measured in the JPL transponder are
produced principally in the demodulation process, and are caused
by variations in the reference phase relative to the carrier.
This phenomenon can be corrected to acceptable limits.
A module-to-module analysis was performed in order to obtain calculated
values for nominal ranging delay and ranging delay variation due to inter-
stage coupling networks so that expected and measured data at normal
operating temperatures and temperature varying conditions could be compared
directly when possible. The overall transponder expected ranging delay
and ranging delay variatlon due to interstage coupling networks is then
taken to be equal to the sum of the individual module values. The results
are presented in Table 2.3.1-2.
2.3.4 Recommended Chan_es
The recommended design changes are listed as follows:
a.
b.
Isolate the crystal filter from the second mixer by adding a
unity gain isolation amplifier in the 47.8 MH I.F. module.z
Tighten the phase specification of the 9.56 MH I.F. modulez
to_ I0 degrees over the operating temperature range.
2-7
JPHL=oI PHILCO-FORO =ORPO_ATION
Bpace & ReentrySystems Division
TR-DAI522
C.
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ee
f.
g.
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i.
Specify the Frequency Divider module phase variation between
its three outputs: + 3 degrees over the operating temperature.
Specify that 4.78 MH z output of the Frequency Divider shall be
at least -60 db below the 9.56 MH output.Z
Control the overall misalignment between reference and carrier
in the ranging detector to_ 20 degrees over the operating
temperature.
Provide adequate isolation to impedance variations at the
input of Frequency Divider module and the output of the VCO
module.
Provide a transient-free bias source to the varicap in the VCO
module.
Eliminate the switching transient caused by turning on the
ranging channel.
Replace the JPL Video Amplifier module with the new SRS version.
DHtLCC)._O ;_ D CORPORATION
2-8
Space & I=le_ntry
Systems Division
TR-DAI522A
SECTION 3
EVALUATION TESTS
3.0 GENERAL
A major part of the Phase II effort was spent in a test program with the
purpose of evaluating and isolating the causes of S-band carrier phase shift
and ranging delay variation in the Mariner C transponder, as a function of
temperature. The transponder used was JPL-supplied; a list of pertinent
serial numbers is given in Table 3.0-I.
In addition to these tests, specific diagnostic tests were performed on
several of the modules of the above mentioned JPL-supplied transponder.
A block diagram of the Mariner 'C' transponder is presented in Figure 3.0-1,
and is intended for general reference purposes for the various sections of
the report.
3.1 TRANSPONDER OVERALL S-BAND/'_CO"/RANGING PHASE VERSUS TEMPERATURE
The transponder was connected in a normally operating condition for each of
these tests, and the various component parts of the transponder were separ-
ately subjected to temperature variations, with all of the remaining compon-
ent parts held at constant temperature. The test set up block diagram is
shown in Figure 3.1-I. As shown in this figure, a transponder (REFERENCE
TRANSPONDER) similar to the subject transponder (TEST TRANSPONDER) was held
at constant temperature and used to provide stable phase coherent reference
signals for the measurement of the S-band and '_CO" phases. The reference
and measured signals are taken at corresponding points in the two transponders.
The major points of interest are listed for convenience as follows:
• S-band phase shift is the carrier phase shift of the 2295_z RF
output of the Exciter, relative to the S-band reference signal.
The data at +25°C is used as a reference point. In effect, this
measurement is equivalent to an S-band input to output overall
transponder phase measurement.
3-1
• DHtLCO-_O_O CORpOrATION
; Sp_ce _- R_-entry
Systems [Division
TR-DAI522A
No.
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5.
6.
7.
8.
9.
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12.
13.
14.
15.
16.
JPL -
Table 3.0-I
Supplied Transponder Serial Numbers
Identifying Name
Preselector
Mixer-Preamp Module
47.8 Mc I.F. l_mdule
9.56 Me I.F. Module
X36 Multiplier Module
AGC Detector Module
Phase Detector Module
VCO Module
Frequency Divider Module
Isolation Amplifier P_dule
Video Amplifier Module
Auxiliary Oscillator Module
X30 Multiplier Module
Receiver, Six Pack No. i
Receiver, Six Pack No. 2
Exciter, Six Pack
15
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(obscured)
4
4
4
4
4
5
5
4
8
21
4
4
4
The following units were also supplied, but were notused in the tests.
17.
18.
19.
20.
Auxiliary Oscillator Module
X30 Multiplier Module
Power Supply
Power Supply
7
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3
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• Two quadrature-related measurements are used in order to avoid
ambiguity and provide greater accuracy in the S-band phase readings
(S-band pha_e shifts typically exceed 90 degrees for each tempera-
ture increment).
• "VCO" phase shift is the phase shift of the 19-1/8 MHz VCO
output signal (i.e., the exciter input drive signal) relative
to the '_C_' reference signal. In effect, this measurement
is equivalent to an S-band input to VCO output overall receiver
phase measurement.
• The ranging delay measurement technique is based upon comparing
the phase of the fundamental component of the delayed 498 KHz
ranging signal with a reference signal in the test set. See
Figure 3.1-2 for further details. Note that the reference
transponder is not involved in the ranging measurements.
Further information on test methods and procedures is presented in
Appendix VII. A llst of pertinent serial numbers for the test set are
presented in the appendix; Table A.7-1.
In the tests to be described next, the temperature increments were,
in the order taken:
a. -10°C e. +40°C
b. 0°C f. +50°C
c. +10°C g. +60°C
d. +25°C h. +75°C
S-band and "VCO" phase data were taken at input signal levels of -70 to
-140 dbm in I0 db steps, and ranging phase data were taken at -70, -90,
and -II0 dbm.
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The order of the temperature tests were as follows:
a. Entire Transponder
b. Individual Six Packs (3)
c. Individual Modules (13)
The results of these tests are presented next. The module arrangement
within the six-packs is shown in Figure 3.1-3 for reference purposes.
3-7
P_ILCO-FORO CO_PO_ATJON
Space _ Re-entryE_ys1=em9 Division
EXCITER
SIX PACK
TR-DAI522 A
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9.56 MHz IF
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PREAMP &
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RECEIVER,
SIX PACK NO.2
Figure 3.1-3
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LOOP
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19.125 MHZ
VCO
9.56 MHz
ISOLATION
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AMPLIFIER
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Module Arrangement Within the Six Packs
PHILC:O-FORO CORPORATION
3-8Space I_ Re-entrySystems Division
_'3
TR-DAI522A
3.1.1 Entire Transponder Evaluation Test
/
Figure 3.1.1-1 indicates that, in the case of the entire transponder, the
S-Band phase shifted fairly linearly with temperature. The total varia-
tion throughout the temperature range is 22.2 cycles. This large phase
shift is the result of many small phase shifts resulting from circuit
detuning which are multiplied by various factors in the frequency multi-
pliers. Figure 3.1.1-2 is the phase shift measured at the VCO signal
input to the Auxllary Oscillator module. Since the Exciter Six Pack
multiplies this frequency (and therefore phase variations with temperature)
by 120, the total VCO shift noticed in this figure can be used to deter-
mine what portion of the total S-Band phase shift was caused by the
Receiver Six Packs. In this case, the total VCO variation of 40.3" multi-
plied by 120/360" equals 13.4 cycles variation at S-Band. The remaining
8.8 cycles variation was caused by the Exciter Six Pack.
The values for the VCO phase shift were read directly from the Wiltron
phase meter. Since the transponder will lock to the incoming signal at
many different VCO phases (see Section 4.2.3), only the relative shift
with temperature should be considered. This explains the difference in
the absolute value of VCO phase shift that will be noticed in these
graphs in the following sections.
As seen in Figure 3.1.I-3, ranging delay did not vary linearly with temp-
erature. Most of the ranging delay variation was determined to be caused
by the subsequent misalignment between the reference and the signal at
the ranging detector as temperature varied (see Section 4.1.2).
Figure 3.1.1-4 and 3.1.1-5 show the comparison of S-Band phase shift and
ranging delay variation measured directly while the entire transponder
was under test and the sum of the data measured while the individual six
packs were under test. The contributions of each module toward these
variations are quite dissimilar in direction and magnitude. This means,
3-9
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since there is good correlation between the data from the entire
transponder and the sum from the six packs, that the delay variations are
a result of many cancelling effects.
Ranging delay was also noticed to vary as a function of input RF attenua-
tion. In most cases, the delay becomes shorter as the input RF level is
decreased. This is probably the result of the reduction in the 498 KHz signal
content as the S/N ratio is decreased. Separate ranging delay tests show
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Video Amplifier (see Figure 3.2.2-8).
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results were an almost linear response of about +2.5" of S-Band shift per
DB of RF input attenuation. The S-Band phase shift divided by 120
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by the receiver portion of the transponder.
Each time the temperature of the test environment was changed, a minimum
of one hour was allowed for stabilization. In thirty minutes, essentially
complete stabilization was noticed to have occurred.
3.1.2 Six Packs Evaluation Tests
Figures 3.1.2-1, 3.1.2-4, and 3.1.2-7 show the change in S-Band phase as a
function of individual six pack temperature changes. Figure 3.1.2-1
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Pack No. i undergoing temperature testing is opposite to that of the other
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two six packs. HowevEr, its contribution to phase shift is small, onlyl
+4.55 cycles total, Compared with the contribution of the other six
packs, -17.78 cycles for the Receiver, Six Pack No. 2 and -9.48 cycles
for the Exciter Six Pack.
Figures 3.1.2-2 and 3.1.2-5 show the VCO phase shift as a function of the
receiver temperature. The total deviation indicated in these graphs will
equal the S-Band phase shift for the respective six pack when multiplied
by 120/360". This is natural since the VCO phase shift represents which
portion of the S-Band phase shift was caused by the receiver, and the
receiver was the only portion undergoing temperature test at this time.
There is no VCO phase shift for the Exciter Six Pack because the receiver
didn't contribute any of the S-Band phase shift at that time.
Figures 3.1.2-9 through 3.1.2-16 show comparisons between data measured,
while individual six packs were in the oven and the sum of the data
measured while the respective six pack's modules were in the oven. The
sum of the data from the modules correlates fairly well with the data from
the six packs. The variations are believed to be due mainly to interaction
effects between modules when the individual six packs were being tested.
Again, each time the temperature of the test environment was changed,
stablllzatlon was essentially complete in thirty minutes and a minimum of
an hour was allowed.
• 3.1.3 Modules Evaluation Tests
The graphs in this section are presented in a similar manner to those in
the previous section, that is the S-Band phase variation first, the VCO
phase variation next, and then the ranging delay variation. The main
dlffere_ce is that a separate set of graphs was not made for each module.
Rather, the modules were grouped for convenience and comparison between
modules. The order of presentation then is a set of S-Band, VCO, and
3-32
I l!Jpl,.ll LCO.FOR D CORPORATION
Space & Ro-entrySystems Division
TR-DAI522A
ranging comparison graphs of the modules for each of the three six packs.?
Figures 3.1.3-1, 3.1.3-4, and 3.1.3-7 show the S-Band phase variation
associated with the temperature change of each module of the transponder.
The X36 Multiplier is responsible for nearly all of the S-Band shift of
the Receiver, Six Pack No. I, except the X36 Multiplier will appear at
S-Band in the ratio of 240/221. Phase shifts originating in the X36
Multiplier will appear at S-Band in the ratio of from 240/221 to (36)
(240/221) depending on where in that module the phase shift occurs.
(See Appendix V and Figure A.5-1). Note that the phase shift caused by
the X36 Multiplier is opposite in slope to that of the entire transponder.
This agrees with the data taken for the Receiver, Six Pack No. I (Figure
3.1.2-1).
The VCO Module caused most of the S-Band phase shift for the entire
transponder varying a total of 12.96 cycles. This is because phase
shifts appearing at the output of the VCO Module are directly multiplied
by 120 before appearing at S-Band. The contribution to S-Band phase
shift caused by the Frequency Divider is believed to be due to input
impedance changes effecting the phase at the output of the VCO Module.
Again, these changes are multiplied directly by 120.
The two modules of the Exciter Six Pack contribute about equally to the
S-Band phase shift. Phase shifts originating in these modules appear at
S-Band in a ratio of from I:I to 120:1 depending on where in the modules
the phase shift occurred.
The VCO phase shift for the modules of the receiver six packs (Figures
3.1.3-2 and 3.1.3-5) agree closely to the S-Band phase shift for those
modules when multiplied by 120. The modules of the exciter didn't effect
the rece%ver phase shift and so no graphs of VCO phase shift are in that
group.
3-33
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Comparing the ranging delay variation graphs (Figure 3.1.3-3, 3.1.3-6, and
3.1.3-8) with the S-Band phase shift graphs for these modules (Figures
3.1.3-1, 3.1.3-4, and 3.1.3-7) it can be seen that there was no smooth
relationship between the way the S-band shifted with temperature and
the way the ranging delay varied. Most of the delay variation for the
transponder was caused by the 9.56 MHz I.F. Module, which isn't in the
ranging loop. However, because of an unusual effect of the ranging
phase detector, carrier shifts occurring in this module result in signi-
ficant video phase shifts (see Section 4.1.2).
The Isolation Amplifier caused most of the ranging delay variation in the
Receiver, Six Pack No. 2. This variation was due to the same effect as
observed in the 9.56 MHz I.F. Amplifier. This effect is the result of a
shift in phase between the signal and the reference at the ranging
detector.
The contribution to ranging delay variation caused by the Frequency Divider
is due to this same ranging detector effect. This indicates again that
most of the ranging delay variation is caused by the unusual operating
characteristics of the ranging phase detector.
The only module which apparently had a significant contribution due
to group delay was the X30 Multiplier.
Figures 3.1.3-9 through 3.1.3-19 are S-Band phase and ranging delay graphs
of specific module tests. They are presented to give a better view of the
phase shift and delay variations caused by those modules which had signif-
icant effects. The S-Band graphs are usually shown on a larger scale than
the combination graphs noted previously. The ranging delay graphs show the
effect of R. F. power level changes into the transponder during the testing
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of those modules which contributed most to ranging delay variations.
These graphs are useful for more closely observing the major S-Band and
phase delay contributions.
Stabilization was noticed to be essentially complete after twenty minutes
from the time of temperature change. As a result of the faster stabiliz-
ation for the modules, only a minimum of forty five minutes was allowed
between temperature points.
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3-54
p_| LCO.ItO R D CORPORATION
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3.2 DIAGNOSTIC TESTS
In order to better understand the effects producing ranging delay
variations, several tests were made in addition to the evaluation tests
in the previous section. These additional tests, described in this
section, were tests made on modules removed from the transponder system.
They show the characteristics of some of the modules which produced the
most delay variations.
3.2.1 Module Tests
The first module to be investigated separate from the transponder system
was the 9.56 M}{z I.F. Module. The block diagram showing the setup for
the testing done on this module is shown in Figure 3.2.1-10. As can be
seen, the crystal filter was disconnected from the module to allow
measurements to be made with and without the crystal filter.
Figures 3.2.1-1 through 3.2.1-5 show the phase and amplitude as a function
of temperature. The phase variation with temperature for both the linear
and limited outputs of the 9.56 Mllz I.F. Module differed only slightly
between the crystal filter connected and disconnected.
However, the absolute phase shift through the I.F. Module was changed
considerably with the crystal filter added. The linear to limited phase
shown in Figure 3.2.1-4 shows about a 50" variation with temperature.
This means, since the transponder receiver locks to the limited output,
that the AGC detector becomes rather badly mlsallgned as the transponder
changes temperature. The specification for linear to limited phase shift
over temperature is ±15".
Figure 3.2.1-5 shows that the gain roll off for the linear and the
limited output of the 9.56 MIIz I.F. occur at opposite temperature limits.
3-55
IpHILCO I_DHILCO-_ORO COmp_RATION
BpaQe & Rm_ntrySystems Division
TR-DA1522 A
The amplitude and phase response of the 9.56 MHz I.F. Module shown in
Figures 3.2..1-6 through 3.2.1-9 were obtained with the test setup shown
in Figure 3.2.1-10. These measurements were made at room temperature.
The graphs indicate that the phase and amplitude response of the 9.56
MHz I.F. is normally almost entirely determined by the very narrowband
crystal filter.
Phase and amplitude response measurements were made of the I.F. stages of
the 9.56 MHz Isolation Amplifier. In order to facilitate this test, a few
minor changes had to be made to the module. Figure 3.2.1-12 indicates the
changes made for the phase measurement. Fifty ohms were added to the
emitter of the emitter follower so that a small sample of the signal
could be monitored for this measurement. This prevented the phase meter
from loading this stage. The signal then had to be amplified to permit
phase measurement with the Wiltron.
Being a high impedance meter, the Boonton RF voltmeter was used to monitor
the output of the emitter follower directly, Figure 3.2.1-14. This
permitted an absolute gain measurement of the I.F. stages of the 9.561dHz
Isolation Amplifier. The results of these tests are shown in Figures
3.2.1-11 and 3.2.1-13. Note that although the amplitude response changes
only slightly with temperature, the nominal gain varles by about 17 DB.
Figures 3.2.1-15 through 3.2.1-21 show the phase and amplitude character-
istics of the Frequency Divider Module. Although conslderable phase
variation occurs with temperature, the phase relation between the three
outputs of this module remain essentially constant which should mean
that the reference to all the detectors maintains alignment. Actually,
although not shown on the graphs, there was a variation of from 2" to 5°
between 33 and J4 over temperature. This slight misalignment of the
ranging phase detector accounts for some of the ranging delay variation
with temperature.
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Space & I::le-en_;rySystems Oivision
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Figure 3.2.1-13
-lO°C
25°C
60°C
75°C
7 8 9 10 Ii 12 13
FREQUENCY (MHz)
Amplitude Response of the 9.56 MHz Stages of
the 9.56 MHz Isolation Amplifier at Several
Temperatures.
The Gain Specification is + 3 db Over the
Temperature Range of -10°C--to +75oc.
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3-69
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i--,-co :.....]I_HII_O-PC) N_) _ONWONATION 6paoe & Reentry
8ymtems Oivi,,Ion
TR-DAI522 A
Output power is shown as a function of input power for the three
Frequency Divider outputs in Figures 3.2.1-17 through 3.2.1-19. The test
setup for the measurements made on the Frequency Divider is shown in
Figures 3.2.1-20 and 3.2.1-21.
3.2.2 Special Tests
Tests were made to see what effect reflections from the 9.56 MHz Crystal
Filter had on the signal from the 47.8 MHz I.F. output to the Isolation
Amplifier. Figures 3.2.2-1 through 3.2.2-7 are all associated with these
tests. Figures 3.2.2-1 and 3.2.2-2 show the amplitude and phase response
measured by the test setup shown in Figure 3.2.2-3. These graphs are
plotted with an unusual frequency scale to show a detailed view of small
frequency deviations and at the same time permit plotting of large
frequency deviations. These figures indicate that with ample isolation
between the 47.8 MHz I.F. and the 9.56 MHz Crystal Filter, very little
amplitude and phase variation would be observed in the ranging channel.
Table 3.2.2-1 was made from the graphs of Figures 3.2.2-1 and 3.2.2-2 by
considering a modulation frequency of 500 kHz.
Figure 3.2.2-4 shows the results of the test made in Figure 3.2.2-5. This
test was a normal ranging delay test of the transponder with the phase of
the reference to the ranging phase detector as the independent parameter.
Figure 3.2.2-4 shows that the slope of the curve of ranging delay vs
reference phase can be greatly reduced by isolating the 9.56 HHz crystal
filter from the 47.8 MHz I.F. output to the Isolation Amplifier between an
isolated and non-lsolated 9.56 MHz cyrstal filter.
Figures 3.2.2-8 through 3.2.2-I0 show the effects on ranging delay due to
mlscellaneous factors. Figure 3.2.2-8 shows the effect on ranging delay
due to dlmlnishlng the slgnal level to various modules. It should be
noted that in modules such as the Video Amplifier, the attenuator reduces
• signal and noise together thus maintaining a constant signal to noise
ratio. Temperature variation of the transponder may change the signal to
3Ilkil I.(;0. P D It D GI)RPORATIDN
3-78
Space & RemntrySylteml [31vision
TR-DA1522A
noise level in some of the modules and therefore change the shape of
some of these curves in actual operation. The signal level input to the
modules shown is not expected to change nearly as much as the variations
used in this test.
Figure 3.2.2-9 shows ranging delay variation as a function of several
unrelated factors. Modulation level of the up-link signal is seen to
have little effect on ranging delay. Power supply variations on the
other hand have a significant effect. During all testing here, the
transponder power supply voltages were monitored and observed to be very
well regulated. However, this test shows the importance of well regulated
supplles being used in the space craft. The SPE offset curve was measured
by changing the test transmitter frequency to obtain a SPE. Because of
this change in frequency, the curve shown is not Just an effect of SPE
as would occur if the transponder VCO crystal changed nominal frequency
with temperature, due to the phase characteristic of the crystal filter.
Figures 3.2.2-11 through 3.2.2-18 are concerned with spurious levels
within certain modules. Figures 3.2.2-11 through 3.2.2-14 are shown
mostly to illustrate the effect of the f/4 harmonic of the VCO frequency
when it is generated in the Frequency Divider module. It can be seen
that when generated, the f/4 harmonic goes right through the video
amplifier with considerable amplitude. The important thing to note from
the spectrum pictures is that the magnitude of the f/4 harmonic was with-
in the JPL specification limits for the Frequency Divider module. It was
discovered that careful tuning would eliminate this harmonic. It was
noted that the ranging delay vs ranging detector reference phase (Figure
3.2.2-4) showed an increase in slope ofl.5 times with the f14 harmonic
being generated (this result is not graphed). Thus, the importance of
tuning the Frequency Divider not to within spurious specification, but
for the elimination of any f/4 harmonics can be seen.
3-79
_NILCO-PORO CORpORAT)ON
Bpace & ReentryBystems Divl,,don
TR-DAI522A
Figures 3.2.2-16 through 3.2.2-18 show the output spectrum of the
Frequency Divider with the f/4 harmonic eliminated. Figure 3.2.2-15
is a time waveform of the video signal at the output of the Isolation
Amplifier when the Frequency Divider was not generating a f/4 harmonic.
Note here the large 9.56 MHz component of the video waveform even during
normal operation of the transponder.
Figure 3.2.2-19 is presented as extra useful information. It shows how
the harmonic content of the 9.56 M}{z I.F. varies as a function of reduced
input signal.
A 400MHz spurious (not shown) was also observed but did not appear
to affect the various test results. A slight power supply voltage
reduction was noticed to eliminate this spurious.
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3-80
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3-83
Space & Re-entrySystems Division
TR=DAI522A
TABLE 3.2.2-I
EXPECTED RANGING SIGNAL SPECTRUM DISTORTION
DUE TO CRYSTAL FILTER INTERACTION
SIDEBAI_ FREQUENCY AMPLITUDE (db) PHASE (Deg)
fo " 4 fm +1.6 -14
fo " 3 f +1.2 -18m
f - 2 f +0.6 -22O m
fo " f -2.1 -I0m
fo 0.0 0
fo + f +4.3 0m
fo + 2 f +4.0 -9
fo + 3 f +3.3 -15m
fo + 4 fm +2.6 -18
NOTES:
1.
2.
3.
fm " ranging modulation frequency
f = 9.56250MHzo
The AMPLITUDE and PHASE values shown above were taken
directly from Figures 3.2.2-I and 2. The ranging spectrum
is altered from normal values by the values shown.
3-84
PMIL£O-_OmO _ORPOAATIONmpaoo _ Ro_ntry8ymtemm Division
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SCALE: 498 KHz_ 17 MINOR DIVISIONS
Figure 3.2.2-6a Normal 9.56 MHz Ranging Signal
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Figure 3.2.2-6b 9.56 M_z Ranging Signat with Crystal FilterIsolated by 20 db Pad
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Figure 3.2.2-8 Ranging Phase Delay vs Attenuation of the Normal
Power Levels to The Modules Indicated.
3-89
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TR-DAI522 A
F _ _ m M m u _ m I
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I ,"-,L_oJi.;-:J_PHILCO-_QRO CORPORATION
Figure 3.2.2-I0 Method of attenuating the Input to
Modules to Determine Delay vs
Input to Various Modules
3-91
Space & ReentrySystems Division
TR-DA1522A
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Figure 3.2.2-ll Spectrum of X½ output to Ranging Phase Detector Due
to improper alignment of the Frequency Divider. Note
the presence of _F harmonics. The harmonic content,
although troublesome, met JPL Specs. (F = 19.125 l_z)
Note 1:
Note 2 :
The alignment condition became evident after changing the
number of turns of one of the toroids in the divider, so
as to achieve stable divider action over the required
temperature range. The unit was subsequently aligned sotha_ the f/4 harmonics were absent.
All the data shown in this report is Eor the properly
aligned case. except where so noted.
3"92
l'H'L=ol3 Space & R e.-entry
_-DA1522A
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3-93
_H|_|_PORO CORPC) R&TION
Spa_e & I_e_entry
Systems Division
TR-DAI522A
DBM
o-F--i
-10-
i
-20 --
-30 -
[
-40 -
-50-L ............
f/4
Figure 3.2.2-13a
f/2 3f/2 f s£_4 3f/2 7f/4
Video Amplifier Spectrum with Transponder
Locked to Test Set but no Modulation; X½
Improperly aligned
DBM
-I0--[
-20 -!_
-30 -
i:
-4O-!:
-50-- : !:i!, i
t : "_-_ _ "
f/4 f/2 f/4 [ 5 t/4 .-it/z
Figure 3.2.2-13b Same as above but with 9.56 MHz Filter Inserted
in REF to ISO AMP in Transponder.
3-94
"[ PHILCOSpace r., ICle-entrv
TR-DAI522A
Figure 3.2.2-14a Output of Video Amplifier. Scope Synced to 498 KHz
Clock from Code Monitor Panel. Pin = -70 dbm, with
Ps = 9 db. The X% was Improperly Aligned: Note
4.78 MHz Content.
]
Figure 3.2.2-14b Same as above, but with 9.56 MHz B.P.F. in the
Reference Leg of the Ranging Phase Detector.
3-95
i pHILCO l_ Space & P e.-entry
YR=DA1522A
............ _ .%_T_=L_-_" "_•_: _%__"_ " _- ........ • ................ ._ ,, .... =_.
Figure 3.2.2-15 Upper Trace:Lower Trace:
Condition:
Input to the Video Amp1.
Output of the Video Ampl.
Normal
Note: The Photos are Intended to Show the Large 9.56 MHz
Content Which is Normally Present at the Input to
the Video Amplifier (X½ Properly Aligned).
3-96
Space & ;_e-entry
TR-DAI522A
410.0
0.0
-!0.0
Emn
zm
_. -20.0DnPDO
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-50.0
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Figure 3.2.2-16
i
. . . . .
m
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i..... ...... t
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t
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_ f f 3f 2 f 5f2 2 2
SPECTRUM ( f = VCO FREQUENCY)
Frequency Divider. Frequency Spectrum For 3 2 Output(_C),
3-97
. IIHILCO-FORD _ORPO;_ATIONSpace ¢ Re-entrySystems i'_ivision
TR-DA1522A
-_!0.0
0.0
-!0.0
:£ -20.0mD
Zim
I'-Dn
I-D -30.0O
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_f f 3_f 2 f
SPECTRUM (f = VCO FREQUENCY)
• Figure 3.2.2-17
i
i •i
]_.__L___
i " "
i
Frequency Divider. Frequency Spectrum For J3 Output(¢ DET).
IIH I LC; 0.1¢0 R (:1C Oli PQ I_iA, TI (;I N
3-98
Space & ReentrySystems Division
TR-DA1522A
[]O
z
D
DO
n,hl
+I0. O.
0.0
-I0.0
-40.0
-50.0
-60.0
" ; " " ; ; , L . " " " ' : , " " "
..... " L i _ ! _ , ; ! _ • 1 ; _ ! i i , ".......... : ' - -! .... ._...... I ,-,4-. _-_-,. ;4 .--,+,-_---_-1.i _.--_-,-: L-_
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....... I .... :" • : _ I-_-_ t _-I-"-" _'-- _--_+--_-_ ..... ,--_ I-;--_-*--_ .... _.... | ...... ." " " t " ' _-'_ .......... " "_" ......... ''''I ....... _' .... !"-
....... t ......... t • _ + , _ _---_ .... -. _-..... _ • _..... ; . ._ . , , ,..i ..... _.... _, , +.-_-_ . i- ': i , _ .... . . . .
................ • ":.i--._:,:- j_-:'' ..... i.:l:.; ..... _'i............... , . _ _.. _ . " . . -_ _ : . • _ _ .... ,... , . _,
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.......... ..... [
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I
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........ |. ,__; ...... ,,, ..... , ............. " i ...._ . i ..... : ..._._..... ] .......
• ' ........... T ........ I ............. " ......... _-_'" _' ..... I " " ! .....
.... __'_.
" " I i ij', "i':'i J:'r: ""?Ti'': ..........
If If 3_f 5_f 3 f 7_f4 2 4 f 4 2" 4 2f
SPECTRUM (f = VCO FREQUENCY)
Figgre 3.2.2-18 Frequency Divider. Frequency Spectrum For J4 Output(_SO AMP) .
3-99
I,--,-=o li JIBNILC(_II_R O COR _(_ RATION
Space & ReentrySystems Division
TR-DAIS22A
//L/
mrl
I-DO.I-D0IZ
hi
0o.
+15
+I0"
-I0
-20
-30
......_ ..... lt .................! " " " ' _" " , _, , , _ , . F
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i ..... _._ , F• i --_:...._ _ , ! -2--L.! ..i_; I _ _ _i
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, _-.. _,,_....,._/_. _ . _ ._. ..
4 ..: ............ ; , i:
F _ _-| ........ ! .... _ . . ._5_-_ .. ...... t" ...... : ...... I
L. _ " !;' ........ ! ...... ,_i .... ii " J ' • _ i .... Y
7 i !ii! iJi!! !-! l!i?!i::: ',il i ......... 6
-i .... I ........ i ....... ' ...... i
-86 -81 -78 -76 -74 -71 -66
POWER INPUT (DBM)
Figure 3.2.2-19 Power Output vs Power Input of the Fundamental
and Harmonics of the 9.56 MHz I.F. AmplifierModule.
IPH,LCoIIHII.CO-IIORI3 I:ORPORATION
3-I00
Space & ReentrySystems Division
TR-DAI522A
SECTION 4
ANALYSIS AND STUDY
4.0 GENERAL
The principal goal of the analysis and study effort was to relate the
ranging delay and S-band phase temperature data to transponder circuit
functions. In addition to this, a study was made to determine the optimum
transmit-to-receive frequency ratio, from the transponder viewpoint, for
the proposed change in the DSIF band occupancy.
4.1 RANGING DELAY AND RANGING DELAY VARIATION
The various measurements made in the program, combined with the analysis
efforts indicate that:
a. Group delay in RF stages due to bandpass interstage coupling net-
works, and phase shift of the fundamental component of the 498 KIIz
square wave in video stages, is responsible for almost all of the
measured ranging delay time in the transponder. These are normal,
unavoldable delay phenomenon and result mainly from bandwidth
limiting requirements.
b. Ranging delay variations measured in the JPL transponder are
produced principally in the demodulation process, and are caused
by variations in the reference phase relative to the carrier.
This phenomenon can be corrected to acceptable limits.
The delay produced by interconnecting coaxial cables and module wiring is in
the order of tenths of a nanosecond per inch, and hence are not considered
significant for analytical purposes. The delay due to the active elements
such as transistors and diodes is in the order of tenths of a nanosecond
per unit ....
A functional block diagram of the ranging loop is shown in Figure 4.1-1. A
summary of the measured and the expected ranging delay and ranging delay varia-
tion data is presented in Figure 4.1-2.
4-1
PHIL(_O.leO m O _ORPORATIQN
Space _- ReentrySystems [::)ivision
U
<
m
<
OF-
WI-
ONI--0
O×
I_lt.C_lcOR 0 COR PI:RATIQN
.
4-2
TR-DA1522A
OO>
:EOn,t,
×
Space & ReentrySystems Division
. TR-nAI522A
m
!b_
4' z
^ #_ _ • .,_ • ..: • .,_ ,_ .......... .÷ _ _ _ , _ + _ _ , , _-, -,_-- ,_-._ ._I.-._ _ ' '.__.o_o:o o o o ° o o.., o
• • i • ¢_ _ • • t • _ • • , • • • , • , • , •
• ,,a
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6-3
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= =
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_ _ _ ,_ _ ..,-__ _ _ "_ _ ";.,
_ _._ii ,
IrPN'LCOI p_ll I_¢O*FO R r_ I_rl RPO RATION
Space & Re-entrySystems Oivision
TR-DA1522A
4.1.1 Ransing Delay and Ran_in_ Delay Variation,
Due to Interstage CqupllngNetworks
A module-to-module analysis was performed In order to obtain calculated
values for nominal ranging delay,and ranging delay variation due to inter-
stage coupling networks so that expected and measured data at normal operat-
ing temperatures and temperature varying conditions could be compared
dlrectly when possible. The overall transponder expected ranging delay
and ranging delay variation due to Interstage coupling networks is then
taken to be equal to the sum of the Indivldual module values. Three simpli-
fying assumptions are used in the analysis:
a. The interstages are either of three types; 1-pole bandpass or
low pass, or 2-pole Butterworth bandpass
b. Similar interstage types in each module can be grouped
together as m identical n-poles.
c. The ranglng signal is not coded. (Measured rangln E delay
change from code ON to code OFF was -25 nanosecond at PIN = -90 dbm).
In computing the expected nominal ranging delay for each module, the
pertinent data was obtained from the "Transponder Parameter Summary" given
in Table 4.1.1-1.
The expected ranging delay variation due to insterstage coupling networks
was computed on the basis of group delay variations in RF stages. This was
done by relating carrier phase shifts in the interstage to circuit detuning,
and then relating group delay variations to the circuit detuning. Thus a
relatioship was established between measured carrier phase variations and
expected ranging delay variation.
Expressions were derived for nominal group delay and group delay variations
as a function of circuit detuning. These are presented in Appendix I and
were used in the calculations which follow.
• pMILCO.FOnO CORPORATtDN
4-4
Space & ReentrySystems Oivis|on
/(? +i
Table 4.1.1-1
TRANSPONDER PARAMETER SLP_4ARy
TR-DAI522A
_D_E
RANGING LOOP
Preselector None 5-Pole Cavity
Mixer Preampl. 4 Transistors 2-pole
1 Diode Pair (Mixer)
47.8 IF & 2rid 8 Transistors 2-poleMixer 1 Diode Pair (Mixer)
IsolationAmpl. 7 Transistors 1-Pole
1 Diode Pair (Detector) 1-Pole
Video Ampl. 4 Transistors 1-Pole
2 Diode Pairs (Llms.)
Aux-Osc, Mod.&X4 2 Transistors 2-pole
1 Diode Pair (Mult.)
X30 Multiplier
INTERSTACE
Type i No.(n-pole) (m)
Bandwidth
TOTAL per
BAND_qDTH Seage
(sn)
4 Transistors
1 Diode Pair (Mult.)
2 Diodes (Multa.)
2-pole Cavity
1-pole
2-pole
4
4
2
4
2
1
4
3
30 MHz (1) 30
8.1 MHz (2) 11.4 MHz
12.0 MHz (2) 18.2 MHz
8.0 Mltz (6) 18.2 )_z
2.1 MIIz (4) 3.28 HHz
3.3 MHz 7.50 MHz
(5) 6.45
(3)
2.5MHz(5)(2) 22.7 M_z (4)
6.45 _z (4)
9.56 MHz IF
(J30utvut)
X36 Multiplier
ACC Detector
Phase Detector
vCO & X3 Multiplie
(J4 Output)
Frequency Divider
(J3 Output)
Aux. Ose.,Mod. &X4
7 Transistors
2 Transistors
1 Diode Pair (Mult.)
2 Diodes (Mults.)
4 Transistors
3 Transistors
I Diode Pair _ult.)
1 Transistor
2 Diode Pairs (Switches)
OTHER
2-Pole 1
X-TAL Filter
2_P01e 5
2-pole Cavity I
_11-j)ole ..... 3 _
2-pole 2
l-pole 1
2-pole 4
1-pole 22-pole 3
2-pole 2
4.90 KI_ 4.90 l_z
600 lqHz 968 MHz
(3) (3)(3)(3),
(3)
(3)
(3)
(3)(3)O)(3)(3)
NO'_'3: 1. Specification value
2. JPL - supplied data for S/N 4 transponder, dated 1964.
3. Data not known
4. Interior ensineerin g report values
5. Composite Aux-Ose And X30 value
6. Extrapolated value
All other data is contained in this report.
4-5
I PHILCO _ Soa=e&Re-_ne._
TR-DAI522A
Refer to Figure A.I-I which is a plot of phase shift and fractional
change in group delay vs relative detuning, for one-pole and two-pole
Butterworth bandpass Interstage coupling networks.
Tank circuit overall temperature coefficients can also be deduced from
carrier phase shift data through the formulas presented at the end of
Appendix I. This could not be done however, in the allotted budget.
The results of the computations which follow are tabulated in the "Ranging
Delay and Ranging Delay Variation Summary" given in Table 4.1-2.
Preselector
lo7j A dj = phase slope at
= dw oQ
Using the Bode approximation for phase slope,
.
(2,) (30x106 rad/sec)
vd _ 40 nsec
This simplified model does not show the change in phase slope
for deviations from band center which actually are present in
a Butterworth filter, so that delay variations cannot be shown
from this model. However, the variations should be nil, since
the carrier phase shift over the temperature range is nil.
4-6
IP-,L=oPH_L_O-_O_O CORPOAATION
Space & Re_sntrySysternm Division
TR-DA1522A
Mixer-Prea_p
le
7 ¸
/
"d = m_n = .total nomlnal expected group delay
" (no. of Interstages)(delay per interstage)
2J-F"d" 3"2" 3(--2% > seo
where B2 is the bandwidth per 2-pole Interstage in hertz.
"d" 3¢ J__xll"4xlO" 6 ) " 3(39.4x10 "9) " 118 nsec
2. A,d = mAVn = m(Vn) (An) - total expected group delay variation
o)(,2)(_) - ,d(+ 1/2 el)
where _2 is the carrier phase shift per 2-pole interstage,
in radlans.
=_= total carrier phase shift due to temperature_2 m No. of Interstages
:" &Vd _= + ('d 1/2
Since
.221.&8 < • (2_) (0.01) (2_) tad
_'d < + (118)(½)(5"77; 10"2)2 - +0.I0 nsec.
4-7
IP.,Lco.]!7PHIl.CO-FOR D CORPORATION
Space & IRe-entrySystems Division
TR-DA1522 A
47.8 t4Hz IF
,
e
Td = 4_2 = 4( 0.4518.2x10" 6 Isec
" 4(24.7 x 10 -9 ) = 99 nsec
I+29.81 2A7d(- AV) = +(99 nsec) (1_) 57.34 7
" +0.8 nsec
where -A7 signifies that the carrier phase shift, and hence the
group delay variation, occurs in the temperature range below
+25°C.
L n_(-nv) j
.-46.4. 2= +(0.8 nsec)(+2--_--_.8) ffi +1.8 nsec
Isolation Amplifier
I. _d = (_d)RF + (_d)vld
2
-4( 0.3_8 )-4c17.s _ _0"9)- 70_.eo18.2xlO" 6.
= nse% (Ael)(Td)vi d (m) (320 r-"ad--;
- total delay of fundamental component (i.e., 498 KHz)
4-8
iPH,.col jDM ILCO-FI_IqO CD R P(:] RATION
15pace & ReentrySystems Division
TR-DA1522 A
Ae I . tan-l( 498 KHzfl )rad
= phase delay of fundamental per Interstage
498 KHz 498x103ffi - 0.152 rad
fl 3.28x106
nsec_l O(md)vl d = (2) (320 r--_-'" "152 rad) = 97 nsec
Cd " (70 + 97) = 167 nsec
2. _Td = (ATd) RF + ( ATd)vid
But due to lack o£ phase shift versus temperature data on the
video portion, only the delay variation (ATd)RF was computed.
/ +16.6___.__2
_d(-_T) "-(70 nsec) _ 5_.3_
- -0.5 nsec
13 o 2
_Td(+A_) - -(0.5 nsec)C
+16.6 J
" -0.05 nsec
4-9
i-H,Lco]F3PH|LCO._OR(_ CO_I PO_IATION
Space & Re-entrySystems Division
TR-DA1522A
Video Amplifier
Io 7d = (m) (320 nseC_rad,(AS1)
498X103nsec_(4)(320-f ad (
7.50x106
(4)(21.3 nsec) = 85 nsec
2. ATd was not computed, due to lack of phase shift versus temperature
data.
• k
°"
i'!.
.L
Auxi.llary Oscillator
I. 7d 2"r2 2(0''450 )m = sec
6.45x106
= 2(69.6 x I0-9) = 139 nsec
+28.8
2. A7d(-AT) " +(139 nsec)(1) [ 57.32
= +4.4 nsec
.,/-32.4A7d(+AI") = +(4.4 nsec7_,_._ _J
= +5.5 nsec
X30 Mu.lt!p1.1er
2
Io
7d " (Td)l.pole s + (Td)2.pole s
(Td)l.pole s = 471 - 4 _20,r318.7xi06) sec
= 4(14.0 x 10.9) " 56 nsec
4-10
pHIt.CO._ORO COrn mORATION
Bpa¢e & ReentryBystems Divislun
(_d)2.poles = 3v2 = 3(. 0.450 ) sec6.45xi06
ffi3(69.7 x 10"9) = 209 nsec
vd - (56 +209) = 265 nsec
2. d - (A,d)2.pole s
I+ 677 ,_ 230x57.3)A_d(-AV ) = +(209 nsec)( ) 3
= +1.8 nsec
(-900)2e_d(+A_) = +(1.8 nsec)
- +3.2 nsec
TR-DAI522 A
The expected total nominal ranging delay due to interstage coupling
networks is 913 nsec. Adding about 5 nsec for all the active elements
brings the final total to 918 nsec. That this figure is higher than the
measured value by about 17Z is not too surprising, since the second assump-
tion at the beginning of thls section would tend to cause a cumulative error
on the increased delay side. This follows from the fact that the narrowest
interstage dominates the overall bandwidth of a group of similar inter-
stages, and that all but the narrowest Interstage is then over-charged in
the group delay.
However, this effect is somewhat compensated by two cavity filters (see
Figure 4.1.I-i) which were neglected in these calculatlons, due lack of
data.
The expected -AT and dr ranging delay variations due to RF Interstages
is -I-6.5 and +10.5 nsec, respectively.
4-11
IIH II.CO.l[OmO CORPOmATION
Space & RemntrySystems Division
TR-DA1522A
Comparing these flgures to the measured values indicates that the nomlnal
group delay is due toithe Interstage coupllng networks but that the
measured variations under temperature are mostly caused by other factors.
See Table 4.1-2 for complete derails.
pH|LCO.I_O RO COIqDORATION
4-12
Space & Reentry
Syatema Division
TR-DA1522A
4.1.2 Delay Variation Produced in the Demodulation Process
As mentioned prevlo_sly, ranging delay variations in the JPL transponder
are produced principally in the demodulation process, and are caused by
variations of the reference phase relative to the carrier in the ranging
phase detector.
4.1.2.1 Description of the Phenomenon
The phenomenon is described in the sequence outlined as follows:
1. Figure A.3-4
Schematic diagram of the ranging phase detector; for reference
purposes.
2. Figure 4.1-1
Ranging channel loop functional block diagram; for reference
purposes.
3. Figure A.5-2
Transponder phase detector(s) block diagram; useful for
describing the phase relatlonshlp between reference and
carrier in the ranging phase detector.
4. _ Figure 3.2.2-4
Graph of ranging delay versus reference phase shift; this is
the chief exhibit in describing the ranging delay variation
phenomenon. The phase slope, with and without the effects
of crystal filter interaction are as follows:
(_Bd/SBref) = 0.44 deg/degnorm
(_ed/_%ref) = 0.12 deg/deg
Iso-amp
[pH,-col _HIL_Q-POmO CORI°ORAT_ON
4-13
Space _- ReentrySymtems [:)ivision
TR-DAI522A
5. Figure 3.2.2-6a and 6b
Photographs of the ranging signal in the time domain show!
the distortion of the ranging signal caused by the crystal
filter.
6. Figure 3.2.2-3
The cut-out section of the second mixer schematic diagram shows
that the crystal filter input impedance can effect the
ranging signal; the isolating pads are not adequate to
prevent the interaction effect.
7. Figures 3.2.2-1 and 2, and Table 3.2.2-1
These figures and the accompanying table show the amplitude and
phase distortion in the frequency domain, caused by the crystal
filter.
Figure 3.2.2-4 shows that a significant reduction in susceptability to
ranging delay variation can be obtained by effectively isolating the
crystal filter input impedance from the second mixer output that feeds
the ranging loop.
A limited effort was made to explain the ranging delay variation produced
in the ranging phase detector due to reference phase shift relative to the
carrier. The results of these studies are outlined as follows:
I. Appendix II.
This is a mathematical model of the demodulation of a
sinusoidal carrier which is phase modulated by a symmetrical
trapezoidal modulating waveform. The carrier frequency
relative to the frequency of the modulating signal is
infinite. The results show that for any peak phase devi-
ation or any slope, the phase of the fundamental component
of the demodulated signal is invariant. More importantly,
it shows that the phase of fundamental component of the
demodulated signal has only two discrete values, 0 and 180
degrees, relative to the modulating signal. The curve shape
4-14
I PHILCO ,l_i'"_-_->_pHILCO-_ORO COmPORATJON
Space & ReentrySystems Division
TR-DA1522 A
I
,
,
PHILCO-FORO CORPORATION
shown in Figure 3.2.2-4 is not predicted in this model.
Appendix III_ll
The mathematical model described in the preceding paragraph
was augmented so as to include a complex amplitude modula-
ting waveform superimposed on the trapezoidal phase modulated
carrier. The periodicity of the complex A.M. is assumed to
be the same as the modulating signal. The results show that
the variation of the reference phase can produce the type
of curves shown in Figure 3.2.2-4, providing that there is
a large fundamental component of A.M. and that there is an
appreciable phase difference between the A.M. and P.M. wave-
forms. The A.M. component on the ranging signal due to crystal
filter interaction shown in Figure 3.2.2-6a appears to contain
a large second harmonic content, indicating that the A.M. content
may not be responsible for the large ranging variations shown
in Figure 3.2.2-4.
Appendix III.2
The fact that the 498 IOiz ranging frequency is appreciable
with respect to the 9.56MHz RF frequency was considered,
with the result that reference phase variations relative to
the ranging signal carrier phase do produce small ranging
variations. Figure A.3-3 illustrates how this can happen,
in a qualitative way. From the figures it appears that the
ultimate value of slope, for small reference variations is
• (Aed/L_ref) _ 0.05 deg/degult
Further effort on this concept could easily lead to a curve
similar to the ones shown in Figure 3.2.2-4, thus defining
the limiting ranging delay variation susceptability to reference
phase variations. The concept of ranging delay variations in
, the demodulation process illustrated in Figure A.3-3 appear
to be equally applicable to the mixing processes shown in the
4-15
Space & ReentrySystems r_ivision
TR-DAI522 A
ranging loop functional block diagram, Figure 4.1-1. Even
if true, the effect would be quite small, since the two
LO injection frequencies are 6 and 72 times higher than
the 9.56 KHz reference frequency.
This concludes the description of the ranging delay variation phenomenom
that is attributable to the demodulation process.
4.1.2.2 Causes of Reference Phase Shift
The causes of reference phase shift relative to the carrier are listed as
follows, in the order of importance as indicated by measurement data:
.
e
e
9.56 MHz IF; input to limited output:
The phase variation over the temperature range is about 76
degrees; Figure A.5-2 shows that a phase shift in the 9.56
MHz IF causes the reference phase to shift in a 1 to 1 manner.
Figure 3.1.3-14 shows that the greatest ranging delay varia-
tion, 177 nsec, occurred when the 9.56 MHz IF was subjected
to temperature variations.
IsolationAmplifier:
Figure 3.2.1-11 shows that the carrier phaseshift over
temperature is about 20 degrees. Figure A.5-2 shows that
this is equivalent to a negative reference phase shift
relative to the carrier. The measured ranging delay varia-
tion is about 64 nsec.
Frequency Divider:
The phase shift between the output to the ranging phase
detector and the APC phase detector causes the reference
phase of the ranging phase detector relative to the ranging
carrier to shift in a 1 to 1 manner; see Figure A.5-2.
4-16
PHILCO-_OAO CO mmOc_ATION
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TR-DA1522 A
.
,
.
VCO Crystal:
The frequency versus temperature characteristic of the VCO
quartz crystal is responsible for causing an SPE versus
temperature variation. The result is that the ranging phase
detector reference relative to the carrier is affected on
a 1-1 basis; see Figure A.5-2. This effect is discussed in
Section 4.2.2.
The crystal filter:
The phase versus frequency slope is sufficiently steep so that
variations in S-band input frequency can cause the reference
to shift noticeably; the phase slope is approximately 0.04
deE/hertz. This effect is discussed in Section 4.2.2.
APC Phase Detector Slope:
The conversion factor _ of static phase error (SPE) to error
voltage is a function of the S/N. Since the APC loop actuat-
ing error is a fixed value under locked conditions, the phase
error must follow any change in KD, on a 1-1 basis. The net
effect then is a variation in ranging phase detector alignment,
and hence a variation in ranging delay.
This concludes the section on the causes of reference phase shift relative
to the carrier in the ranging phase detector.
4-17
["HL=Oi IBMILCO.FOA [3 CC) IN PO _ATIO N
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4.2 TRANSPONDER PHASE RELATIONSHIPS
/'
This section concludes the analytical efforts Which were made in predict-
ing and explaining the results of the S-Band/"VCO"/ranging phase versus
temperature test measurement program.
4.2.1 General Transponder Phase Relationships
The block diagram shown in Figure A.5-1 was created in order to facilitate
the effort, This block diagram depicts the pertinent APC loop "locked"
phase relationships. It takes into account module input-to-output phase
shifts, which may be thought of as being functions of temperature, time,
or input S-Band frequency.
The equations derived in A.5-2 using this basic block diagram, predict
transient as well as steady state performance. The equations were used
primarily to predict the direction of, and in a qualitative sense the
magnitude of, the steady state value of the measured S-Band phase varia-
tions versus temperature. The APC loop mixing and frequency multiplying
processes can, and do, alter the S-Band phase deviations as compared to
the module (or module group) input'to-output values.
An example of how the equations of A.5-2 were used is as follows:
I. The steady state performance to step inputs is found by use of
the final value theorem of Laplace Transformation Theory; i.e. :
lim 8vco(t) - lim SOvco(S)
t "*_ S'*0
.where 8vco(S) = equation A.5;2.6
_t__.'. 8vc ° steady state - 110%
4-18
pN|LCO.I[OA 1:3 C(]RpOIqATION
6pace _ ReentrySystems Division
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e Let _ be evaluated for the 9.56 MHz I.F., for example:
/!
where _ ; equation A.5.2.4
• 6 steady state ="" vco II0_
3. Finally, from equation A.5.2.7:
(SS)ou t = 120 8 = . _240)vco 2--_ 89.56
Thus it is apparent that the module input-to-output phase variation, B9.56 ,
will be modified in reaching the S-Band output by a -(240/221) factor•
Since the module phase deviation is expected to go negative with increasing
temperature, the S-Band phase will go positive with increasing temperature.
In addition, the magnitude of the shift is expected to be a small fraction
of a cycle. These observations are borne out by actual measurement (see
Figure 3.1.3-1).
This method of predicting the S-Band phase variations iS accurate to the
extent that interfacing driving point impedances do not vary. An example
of this is the apparent effect of the Frequency Divider input impedance
variation under temperature and power input varying conditions. The curve
of phase shift versus temperature and input power, Figures 3.2.1-15 and
3.2.1-16, along with the calculated multiplication factor, +(240/221),
predict only a fraction of a cycle of deviation at S-Band, compared to
the measured value of about 2.3 cycles. See Figure 3.1.3-11; note that
the phase shift curve is not monotonic, llke all of the others.
The only other example of the failure of the analysis given in A.5-2 to
explain measured S-Band phase variations is the test results of the VCO
module. ,The phase varied opposite to the expected direction, and the
magnitude was much greater than expected (13 cycles). A llst of possible
4-19
IPHL=°I _M|LCO=IIORO CO mPO_/_TION
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explanations include the following, in order of expected importance:
7/i
1. The last isolation amplifier of the VCO shown in Figure
3.0-1_ which Is not taken into account in Figure A.5-1
and the derived equations, is responsible for much of
the S-Band phase deviation, since its phase deviation
is multiplied by 120 times.
e The output power of the JPL VCO module is known to
vary by about 3 db over temperature. This coupled
with the fact that the input stage of the frequency divider
is normally driven in a limiting condition, and that
the tuning is effected by the input level, leads to the
conclusion that the input impedance of the Frequency
Divider is being varied by the VCO module. The
variation in impedance varies the carrier phase angle
at that point, which then is multiplied by 120 ti_es in
reaching the S-Band output. This interface problem,
along with the VCO last isolation amplifier phase shift,
is believed mainly responsible for the large Variation
measured.
o Either or both of the two X3 multipliers and/or the
other isolation amplifiers (see Figure 3.0-1) could
be providing a positive phase shift with increased
temperature; this is not thought to be the case.
The two exceptional cases need further tests to determine the facts.
PHILCO,FORO CORPORATION
4-20
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4.2.2 RanRinR De_laT_Variation Caused by the VCO Crystal
Temperature Characteristic
As mentioned in Section 4.1.2.2.4, the frequency versus temperature
characteristic of the VCO quartz crystal causes a variation in the
relative phase between reference and carrier in the ranging phase
detector. This in turn causes a variation in the ranging delay as a
function of temperature.
Figure 4.2.2.1 shows the expected ranging delay variation as a function
of temperature, due to this effect. The following steps show how the
curve was obtained (Note: brackets are used exclusively to indicate
functional dependence).
I. Aeref = -SSp E
2. %Sp E = VSPE/K D
.3. Vi(T)
4 • YSp E
5. VI(T)
(See Figure A.5-2)
Hypothetical internally generated bias
voltage which is equivalent to the frequency
pulling effect of temperature
= -VI(T)
= APC loop correction voltage
= Vvco[fvco(Z)_
• fVco(T) = VCO frequency versus temperature
characteristic curve; Figure 4.6-2
of "Interim Engineering Report"
4-21
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• Vvco(_vco) = Inverse of the VCO frequency versus bias
voltage curve; from data taken during this
program, but not appearing in this report.
I__ x v fVco(T)6. ASref = KD C
3. _9 d = f(A@ref) (Figure 3.2.2-4)
The curve, Figure 4.2.2.1, is hence obtained by determining the para-
meters in the given sequence, until the AOref parameter is obtained.
Then the ranging delay variation curve, Figure 3.2.2-4, is used to
compute AO d.
The curve shows an expected ranging delay variation of about 3.1 degrees,
or 17.3 n sec, as opposed to the measured variation of about 13.3 n sec.
Note that Figure 4.2.2-1 predicts a small hysteresis effect.
4-23
[ PHILCO I_PHILCO-FORO ¢OMPDRATiON
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TR-DAI522 A
4.2.3 "Cog" Phase Steps
At the beginning of the S-band /"VCO"/ ranging phase versus temperature
testing program, it was noticed that the measured 'WC_' phase (i.e.,
the VCO output signal relative to the corresponding signal in the reference
transponder) would take discrete phase steps whenever the ranging channel f
was turned "on." These "Cogs" are explalned as follows:
le
e
Reference to Figure A.5-2 shows that the APC loop is
controlled at its phase detector; hence one cycle "slipped"
here should result in one "cog" of 'WCO" phase Jump.
The magnitude of one "cog" is computed by noting that the
APC converts an incremental phase change in eVCO, as defined
in Figure A.5-2, by 111 times at one input to the APC phase
detector, and by 1/2 times at the other input. Hence, for
a one cycle or 360 degree advance of the upper input relative
to the lower one
+ lll(Aeo) - [ = 360 °
• 360 ° A.. A9° = 110---_= 3.26 ° ffi1 "cog."
.
.
l..,L=ol IBHILi:O-FI=¢I CI CIO m IICIRATt(:3N
A half "cog" is theoretically possible, since the Frequency
Divider has two stable modes. Its output waveform relatlve
to the input drive signal has been observed to take either
of two phases, 180 degrees apart, due to a momentary interrup-
tion o£ the input drive.
The 'WCO Loop" shown in Figure A.5-3 is very sensitive to
VCO blas voltage transients having fast rlse times relative
to the loop filter response Clme (see Figure A.5-5). From
this Figure, a step input results In a 'WCO" phase overshoot
which Is approximately 3.2xi03 times the steady state value.
From equation A.5.3.2, the steady state value is
V i
(_evco)s. s.= (IIoD (KD) •
4-24
Space & ReentrySystems Division
TR_DAI522A
The amplitude of V i that will cause the SPE to reach a
90 degree "knee" of the phase detector defines the stable
limit of V i. The incremental variation in the "VCO" phase
for this condition is:
(A@VCO)max 110% "
The final result is hence
= (3.2xi03)r vi( evco)max (ILO%>= [(llO%) (20) ]
I0_(Vi)ma x = _ I0 milllvolts peak.
3.2x103
5. The transient created in the +15 volt test power supply and
its associated leads was found to produce the "cog" phase
steps, whenever the ranging channel was turned "on," but
not "off."
6. Switching the ranging channel "on" involves only applying
D.C. power to the Isolation Amplifier module.
7. Both transponders were affected about equally, since the power
supplies were common. The measured "cogs" were predominantly
about 1.6 degrees, which is the equivalent of one-half of an
expected "cog".
8. When the transponders were connected to separate power supplies,
only the test transponder was affected. The phase Jumps were
in the order of 30 to 60 degrees, or the equivalent of many
"cogs."
9. Power supply isolating tests revealed that only the VCO module
was affected, and that isolating it eliminated the phase Jumps
altogether. Heavier transients were additionally applied to
the remainder of the transponder without any sign of "cogs."
4-25
IlIM I P.CO*PO R I_ CORPORATION
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The conclusions drawn from these observations are as follows:
I. Power supply transients are suspected of upsetting the VCO
via the frequency pulling varlcap. The biasing of this
varlcap should be transient-free. Further effort is required,
however, to verify that only the varicap biasing is affected.
2. The Frequency Divider can switch between the two bl-stable
modes in the APC loop "pulllng in" process.
4-26
.IpH,LcoJ DHILCO-POAO CORPDRATION
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TR-DAI522 A
4.3 FREQUENCY RATIO STUDY
The results of this effort indicate a usable ratio of the transponder
transmlt-to'receive frequency as follows:
Transmit Frequency ffifd
Receive Frequency f
80
63 "
The objective of this study was to develop an analytical approach and to
use it to select an optimum value of r. It is apparent that a particular
set of constraints, when applied to the frequency relationships in a given
order will produce a value of r which is optimum in a particular sense,
The sections which follow present the analytical approach and the results
of applying one particular set of constraints in a given order.
The basic transponder configuration analyzed is presented in Figure 4.3-1,
and the significant results are presented in block diagram form in
Figure 4.3.-2.
General Discussion
The relationships presented in Section 4.3.1 comprise an independent set
of basic equations which govern the transponder frequency.relatlonships.
These relationships were used to derive the working formulas pre-
sented in Section 4.3.2, and used throughout the analysis which is
presented in Appendix VI. The analysis is presented in outline form.
The constraints which were applied in the analysis reflect the desire
to change the existing S-band transponder configuration as little as
possible, particularly the APC loop mixer signs.
4-27
PH|LCO-FORO CORPORATION Space & Re-entrySystems nivision
/ f J
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TR-DAI522 A
f
B.P.F.
(Bu)
7l
fd_ H TRANS.B. P.F. FREQ.
MULT.
<Bd) (Xd
IST
MIXER
I1STFREQ.MU LT.
t ,
IST IF
AGC 1NET.
2NDMIXER
(Xb)
2ND IF
LIM.
B
--a
fo
DET. K d
f2 t LAG• COMP.
_ [ V.C.O.
(INTEGRATOR)
Figure 4.3.-1 Basic Configuration
4.3.1 Basic Frequency Relationships*
4.3.1.I r - fd/f__
4.3.1.2 f_" afo "I" fl
• = • _" f24.3.1 3 fl bfo
4.3.1.4 f2 " Cfo
4.3.1.5 fd " dfo
*All frequencies and multiplication factors are positive quantities.
4-28
PHILCO-FO_O COR POTATIONSpace _ I::le-entrySystems Division
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4-29
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4.3.2 Derived Formulas
The following formulas are obtained by straightforward algebraic
means, from the basic frequency relationships given in Section 4.3.1.
4.3.2.1 fu/fo = [a • (b_c)]* i
4.3.2.2 fu/f2 = [a • (b_c)]/c
4.3.2.3 fu/fl = [a • (b_c)]/(b + c)
4.3.2.4 fl/fo = (b_c)
4.3.2.5 fl/f2 = (b:kc)/c
4.3.2.6 f2/fo = c
4.3.2.7 fd/fo = d
4.3.2.8 fd/f2 = d/c
4.3.2.9 fd/fl = d/(b_c)
4.3.2.10 fd/fu = d/[a+(b_.c)] =A r
Sign choices: .
2.
3.
4.
+c ........ fl > bfo
-c ........ fl < bfo
+(b_c) ...... fu > afo
-(b_:c) ...... f < afU 0
*Derived by Substitution of Equations 4.3.1.3 and 4.3.1.4 into
Equation 4.3.1.2.
4-30
ioH,.coi Space & IRe.entry
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, /./
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SECTION 5
VIDEO AMPLIFIER
5.0 GENERAL
The following describes the SRS Video Amplifier which was developed as part
of the Phase II effort.
5.1 Functional Description.-
The video amplifier accepts the detected ranging modulation from the
isolation amplifier, amplifies the signal to a llmlted output level, and
provides separate outputs (isolated from one another) to each of the two
phase modulators. A block diagram of the video amplifier is shown in
Figure 5.1-1.
5.2 Speciflcation Requirements.-
The performance requirements for the SRS Video Amplifier module are
summarized in Table 5.2-1.
5.3 Problems in Mariner C Design.-
a. Both output level and pulse symmetry vary excessively
with variation in input level.
b. As a function of temperature, gain variation and pulse
asymmetry cause ranging distortion and error.
c. Rise and fall times are a function of bandwidth.e
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d. Isolation between the two outputs (6 db) is marginal.
7I
e. Gain is too high both at 9.56 MHz and at 19.1 MHz.
f. Output impedance is too low and is not'controllable.
g. Insufficient bandwidth results in undesirable ranging
errors,
5.4 SRS Module Design.-
The video amplifier module has been completely redesigned to overcome the
above difficulties. The schematic diagram of the new module is shown in
Figure 5.4-1.
The incoming signal is amplified approximately 20 db by the first stage
(QI, 2N917) and then goes through a flve-pole Butterworth filter. The
3 db bandwidth of the filter is 40 Hz to 4.0 MHz. The steep attenuation
above 4 MHz assures adequate suppression of any components at the second
IF, VCO, or first IF frequencies. After the filter, the signal is
amplified approximately 20 db by the second stage (Q2, 2N917).
The third stage of amplification is a differential amplifier consisting
of a pair of 2N916 transistors CQ3 and Q4), that amplifies linearly at
input levels up to -60 dbm, then limits at all higher input levels. The
next stage is another differential amplifier (Q5 and Q6, also 2N916's) that
limits the output regardless of whether the input to this stage is linear
or has already been limited by the first differential amplifier.
The output stage for each of the two outputs is another 2N916 (Q7, QS) in
a con=non collector configuration. The gain provided at this stage brings
the signal up to the required 0 dbm output level. Separation of the out-I
p_t stages of the signals to the two exciters provides 50 db isolation
between the two outputs.
5-3
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TABLE 5.2-1
]i
VIDEO AMPLIFIER MODULE DESIGN SPECIFICATIONS
Modulation Frequency
Impedance
Input
Output
Video Power
Input
Output
Limiting (for 3 db drop in input power)
Rise and Fall Time
Transient Response (-70 db squarewave)
Overshoot
Undershoot
Gain
9.56 MHz
19.1MHz
Current Drain
Voltage Supply
Power Output Variation
Temperature
70 Hz to 3.0 HHz
50 + 5 ohms resistive
50 + I0 ohms resistive
-70 dbm to -5 dbm
0 dbm + I db
I db max
80 nsec max
5% max
5% max
25 db max
I0 db max
50 ma max
+15 volts +3Z
+0.4, -0 db
-20°C to +75°C
IPHILCO _pPiiLCO._O RO COR pORATIQN
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5-5
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5.5 Test Data.-
7J!
Performance of the breadboard video amplifier module is summarized in
Table 5.5-1. Figures 5.5-1 and §.3-2 show representative oscillograph
traces from which time delay measurements were made. Figures 5.5-3 and
5.5-4 show output vs input of 9.56 and 19.1 MHz signals, respectively;
Figure 5.5-5 shows the module bandpass characteristic. Table 5.5-2 shows
the attenuation of 498 kHz harmonics.
5.6 Comparison with Mariner C Module.-
Table 5.6-1 summarizes the significant differences between the Mariner C
and the SRS Video Amplifier modules.
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TABLE 5.5-1
SRS VIDEO AMPLIFIER BREADBOARD TEST DATA
Current Drain (15 vdc supply)
Input Impedance
Output Impedance
Limited Gain (-70 dbm input)
Linear Gain (-85 dbm input)
Bandwidth (-85 dbm input)
Lower 3 db point
Upper 3 db point
Rise Time
-70 dbm input
-55 dbm input
Fall Time
-70 dbm input
-55 dbm input
Power Output in dbm (-55 dbm input)
43ma
48 ohms
50 ohms
70 db
85 db
40 Hz
3.4 MHz
50 nsec
50 nsec
50 nsec
50 nsec
Supply Voltage -20°C oOc +25°C +50°C +75Oc
14.5 vdc -.50 0.00 +.25 +.50 +.50
i5.0 vdc -.25 +.25 +.50 +.75 +.75
15.5 vdc 0.00 +.50 +.75 +I.00 +I.00
Limited Output Level (15 vdc supply, +25°C)
input Level Power output
-70 dbm +.50 dbm
-60 +.50
-55 +.50
-50 +.50
-40 +.50
-30 +.50
5-7
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TABLE 5.5-1 (Continued)
SRS VIDEO AMPLIFIER BREADBOARD TEST DATA
Time Delay from Input to Output (25°C) - See Figure 5.5-1
Input Level Rise Time. Delay (nsec) Fall Time D_elax_(nsec )
-70 dbm 245 240
-60 240 235
-55 240 230-50 235 230
-40 230 230
-3O 20O 240
Time Delay from Input to Output (-55 dbm input) - See Figure 5.5-2
Temperature Rise Time Delay (nsec) Fall Time Dela_(nsec)
-20°C 235 220
O°C 240 220
+25°C 240 230
+50°c 240 230+75°C 240 250
Note : No change in time delay was observed due to supply voltage variationsof +0.5 vdc.
9.56 MHz output level (-70 dbm input)
19.1MHz output level (-70 dbm input)-52 dbm (See Figure 5.5-3)
-76 dbm (See Figure 5.5-4)
Linear Frequency Response at -85 dbm input (See Figure 5.5-5)
Frequency Output (dbm) Attenuation (db)
30 Hz -8 -640 Hz -5 -3
60 Hz -3 -I
100 Hz -2 0
50 kHz -2 0
500 kHz -2 0
1.0 l,a.Iz -2 02.0 -2 0
2.8 -3 -I
3.4 -5 -34.0 -8 -6
J PHILCO F_I_]PHILCOoFORD (_O R PQRATI ON
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(continued)
Frequenc 7 Output (dbm). Attenuation (db)
4.6 MHz -14 -12
5.0 -19 -17
5.5 -29 -27
6.0 -32 -30
7.0 -43 -41
8.0 -52 -50
9.56 -68 -66
TABLE 5.5-2
ATTENUATION OF 498 kHz HARMDNICS IN DB
498 kHz
Input
(dbm) 1.0 1.5 2.0 2.5 3.0 3.5 4.0 4.5 5.0 5.5 6.0 6.5 7.0
-70 -30db -20 -50 -40 -50 -50 -50 -50 -50 -50 -50 -50 -50
-60 -30 -I0 -30 -20 -30 -20 -30 -30 -40 -50 -50 -50 -50
-50 -40 -I0 -30 -20 -30 -20 -30 -20 -30 -30 -40 -50 -50
-40 -40 -10 -40 -20 -40 -20 -40 -30 -40 -30 -40 -30 -40
Note: Attenuation is given in db below 0.0 dbm of 498 kHz output, e.g.,
-50 indicates that attenuation is at least 50 db below 0.0 dbm.
5-9
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IP.,Lc°I_ Space & Re-entry
TR-DAI522A
j:
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j
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o
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),,4
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5=ll
PHILCO _-_] Sloace & Re-entry
Systems Division
TR-DAI522 A
-I0NO 498 KHz
SIGNAL
-20
:£mEl
Z
i'-D
I--DON
2toIn
-4(
50
---- _0
498 KHz
SIGNAL
-70 DBM
-30 DBM
-60 DBM
-40 DBM
-50 DBM
-Tq
-80
NOISE
LEVELS
-----' I L-70 -60 -50 -40
9.56 MHz INPUT IN DBM
FIGURE 5.5-3 9.56 MHz OUTPUT VS. INPUT
5-12
-30
TR-DAI522A
-I0
-2O
-3O
NO 498 KHz
SIGNAL
-40
:EmO
Z -50N
I-
lLI-::)O
N -60"r"
--
-80
I-70
I I I-60 -50
19.1 MHz INPUT IN DBM
FIGURE 5.5-4
-40 -30
19.1 MHz OUTPUT VS, INPUT
5-13
.... I ......
f i:
i
'! .... i
_I " iI ..... -T'---- ::r .... ;-,I ! i
: ': .2
-_:{,7_:uLili-_
;=] ......_, -T-I--77-
...... ; ]' i ' i. ,, : ,:1
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:!i![[iiit i!i i ill
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llIil!i-i!
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++-]-+Ii+!+:411!I!i;+
+
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+ I +
----r+ =T +l i;
' I_a+ ?f+li :, 13. o_
-',+_ +!I,-T-:: iii[iii i++t_iliili -t+it
: !i+I++ +i::
.-:_i!iiii _ii". . . : ; [, ..i .
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"+"+'" :+_+--m _i?!+,,,,-+: ++ .....li-:-l-i;rl:l-_t-I_l _ +
............. ...._+., :+.+-l+-+.,-++ _ +_-+-i.
........... I-++-+;! "? ?t't-;-t'-: ......... +..
...... t Tllltt _ ::f +"
I ' " ? .I i i:[+iP+ +i++ Ili: ++,++
.ii t; I-N.-: Li i i_i J-i+i_ i!iiLi! l+';i i.il_il+_++:,, _:'i_
; .k' : : t I '_,++,.+:I++i_I.:... ++-+I+ ,i _+J++'x++i:i-++.+, ++ :+,+,+++.+,.,++I+_ +'++!i_!+ i!+ +++_i_+_! ++.L+
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0 t I I
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!i!! .:illi:!:l : "
i,:i il _, il.!I11_i,
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:+'_ +i ++
, i , ; ,_ , I .... i;
tttth+,t ,_,:tili4i _ii I
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_i:,.ili_ili:ii": "' I: _ _t+
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i:,iil_,i_!iiii' I.l ........-+,:,.-'._ ; _t: =Itt j'-;,l_t ' ,I t+ ;
:_=;+__c_| + ,+'..:'I, ; t+ ', ;_1:_-+cmlr',q !.l : ::T+
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5-14
PHILCO _IIHII.¢:O+I=O_I 0 GOUlIIICI_ATION
i!: i
; I ,
11:
+ ; !fl.l
',!I
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!!!!! N-
14_LL.
tit .+
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!!i.!
TR-DAI522 A
o
L__c;
I
• O
']i I-: : i (J)
, i _= ,,,E
' ' ' ill:;! <
I!: "r, ; _)
if+ =
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dhi
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!+-:: E
Ii,+
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! !:-i iill:
i',i4
iii: _
!: :-
, . "T"
, , + +
Ipaoi & Rm_IntryIIyitsmI r_lvliIon
TR-DA1522A
TABLE 5.6-1
l
VIDEO AMPLIFIER CHANGES FROMMARINER C
Mariner C SRS Version
le
2.
e
o
e
e
7.
8.
9.
I0.
11.
12.
Gain Variation vs Temperature
Output Level vs Input Drive
(-5 to -70 dbm)
Pulse Symmetry Variation
vs Temperature
Pulse Width Symmetry
Rise & Fall Times
(-70 dbm Input)
Output Impedance
Isolation Between Outputs
Bandwidth at -85 dbm Input
Gain at 9.56 MHz
Gain at 19.1 MHz
Symmetry Variation vs P.S.
Voltage Variations (_5 volt)
Current Drain
+2db
+ldb
50 ns
500 ns
80 ns R;90 ns F
35 ohms
6 db
1 kHz to 3.3 MHz
34 db
34 db
25 ns
21 ma
+ldb
+0.25 db
30 ns
10 ns
50 ns
50 ohms (Adjustable)
50 db
40 Hz to 3.4 MHz
18 db
-6 db
Unmeasurable
43 ma
pHt LCO.FOIR (_ COFII_O RATIO N
5-15
Space _ Re-entry
Systems Division
TR-DAI522A I
SECTION 6
CONCLUSIONS AND RECOMMENDATIONS
6.1 DISCUSSION AND REVIEW
The design study of the S-Band Turnaround Ranging Transponder was divided
into two parts, Phase I and Phase II. The Phase I effort was directed
toward general circuit and system performance improvements, and thePhase
II effort was directed towards evaluating the ranging system mainly, and
secondly towards evaluating the input-to-output S-Band phase stability
over temperature.
Due to the fact that the Phase I effort covered a broad spectrum of
topics, no attempt will be made in this section to discuss the conclusions
or recommendations resulting from that effort. A brief summary of the
design deficiencies and the proposed module and system design changes to
correct these deficiencies is presented in the Summary, Section II. For
further details, refer to the "Interim Engineering Report", WDL-TR3066.
6.1.1 Ran_inK System
Table 2.3.1-2 summarizes the ranging delay and ranging delay variation
evaluation study. In it is presented measured and expected values, for
the Mariner "C" transponder. The expected delay variation performance
can be improved greatly, as it will be shown, if the following
conditions are met:
I. Crystal filter interaction is eliminated
2. Ranging detector misalignment is held to _.20 degrees.
.iPH,.=oi iJ_M|U_O-PORO CQR_OnATIO_
Spa¢e _ Reentryiynterna [:)ivia|on
TR-DAI522A
/
DASref AT d
I (deg) (n sec)/
-20 -12.3
+20 +14.0
This data, plus the expected total group delay variation obtained from
Section 4.1.1 provide the following design goals in ranging delay
variation:
Temperature (ATd) min (ATd) max
Range (n sec) (n sec)
-AT -5.8 +20.5
+AT -1.8 +24.5
Note that now the delay variations due to group delay is now an appreciable
factor, compared to that due to misallgnment in the ranging detector.
The new maximum expected spread is then about 30.3 n sec, as compared to
measured value of 84.3. The improvement is all the moresignlficant in
view of the reduction in cancellation effects, not to mention the reduc-
tion in ranging signal distortion.
6.1.2 S-Band Phase Shift
The S-Band phase shift can be reduced to about one-half its present value
by correcting only the impedance interface problem between the VCO and the
Frequency Divider. This can be done by replacing the present VCO output
stage and the present Frequency Divider input stages with temperature
compensated, broad-band isolation stages. (Note: The preceding statements
hinge on the verification of the assumption that an impedance interface
problem exists; time and funding did not permit proper investigation of the
problem.)
6-2
iPHL=Oi pHILCO-FORO COMPORAT)ON
Bpace & ReentryISymtems O|vislon
TR-DAI522 A
It is estimated that the input-to-output S-Band phase shift can be reduced
to about five cycles. This Is equivalent to a time delay equal to 2.18 n
sec. Use of the S-Band carrier In range measurements is attractive from
the standpoint of fine range resolution, but would be complicated by "lost"
cycle counts in the mission. "Cogs" would also result in small ranging
errors, since the "VCO" phase has 221 equally probable locked states,
relative to the input S-Band signal.
6.1.3 Spectrum Analysis
Table A.4-1 lists the expected spectral amplitudes of the ranging signal
at the input and the output of the transponder. The values are based on
the mathematical model presented in Appendix IV. This analysis was a
by-product of the demooulation analysis presented in Appendix If, and was
funded on another related program. Measurements indicate that the results
are valid for the values of the parameters chosen, and are useful in
checking for unwanted variations in the input or output signals of the
transponder. Note that the test set output spectrum is non-symmetrical,
and that the transponder output spectrum indicates over-devlatlon, and
limited bandwidth as evidenced by the high value of the even sidebands.
DMIL=O-FORD COA PDRATION
6-3
6pace & ReentryBysterns Division
6.2 REcOML_NDATIONS FOR FUTURE WORK
TR-DAI522A
In order to achieve the ultimate in performance of the JPL transponder,
the following areas are recommended for future effort:
Modules
Existing Mixer Preamplifier Design lacks gain and stability.
e The Frequency Divider should be redesigned to increasestability
and give added filtering to subharmonics.
Redesign the VCO to provide isolation between frequency divider
and auxiliary oscillator outputs, and improve oscillator bias
stability.
S_stem
A transponder detail system analysis should be made to determinex
optimum gain, bandwidth, and slgnal/reference level distribution.
A review should be made to determine the optimum transponder
functional configuration.
Ranging and doppler measurements should be made on the new module
designs to verify the expected improvements. It is recon_nended
thmt modules be tested as is, at first, then updated according to
the design recommendations arising out of the Phase II effort,
and then given a final test. The tests sould be done with a JPL-
supplied transponder on an SRS module, SRS six-pack, and a com-
plete SRS transponder basis. This would allow JPL to evaluate
and accept only those changes deemed necessary.
T_e technical know-how and experience exists at Philco-SRS Division for
• efficiently investigating these areas, due to the invaluable experience
•derived from the design study progr_, JPL Contract 951290.
6-4
I"H''=OI pH|LCO.I_OR O CORDORATION
Space _ ReentrySystems I_ivision
TR-DA1522 A
APPENDIX I
PHASE SHIFT AND GROUP DELAY VS RELATIVE DETUNING
SINGLE AND TRANSITIONAL COUPLED DOUBLE TUNED FILTERS
PHILCO-FORO CQIqPORATION
Space & ReentrySystems Division
TR-DAI522A
APPENDIX I
PHASE SHIFT AND GROUP DELAY VS RELATIVE DETUNING
SINGLE AND TRANSITIONAL COUPLED DOUBLE TUNED FILTERS
A.I.I Relative detunlngAw o
B B = X
Aw= w - w =A detunlng in rad/sec0
B = filter BW.3db in rad/sec
B 1 = BW.3db of 1-pole
B2 = BW 3db of 2-pole, transitionally coupled
B2 =_-2 B 1 for two identical 1-poles having B 1
and transitionally coupled
A.I.2 Phase Shift
_I = phase shift of 1-pole
_2 = phase shift of 2-pole
_)I = "tan" I(2X)
_2 = -tan- [_]
A.I-I
iDNiLCO.FORO CORPORATION
Space & Re-entrySystems nivision
From the preceeding expressions:
X
0.0
0. I
0.2
0.3
0.4
0.5
0.6
0.7
_1(. de g) " _.2,(. des.)
0.0
11.3
21.8
31.0
38.7
45.0
50.1
54.4
0.0
16.4
34.0
52.9
72.3
90.0
104.6
115.9
TR-DAI522A
This data is plotted in Figure A.I-I.
A.1.3. Group Delay*
_ d_ d_ d×dee dX dw
'rx= d× d_o= ) ( )
d_2 dX _2d_'-'Ifl'_x 2 I
*Fagot and Magne, Frequency Modulation Theory.
Pergamon Press, New York, 1961.
Note: This theory is subject to the limitation that the filter bandwidth
is large with respect to the modulation spectrum.
A.I-2
iP.,.col IIHILCO-FORO CORPORATION
Space & Re-entrySystems Division
_1 e4
6÷ +
I I i
i
T&-I_1522 k
<1
\0
I
,,,,4
¢=_.._
¢_,
0
0 _0
U _
I
T
A.I-3
IIH i i,,.1¢0. F 0 R 0 CORPORATION
Space & Re-enl=rySy.etem s Division
TR-DAI522A
D A.I.3.1 Fractional Change ln Group Delay Versus Relatlve_Detunlng
Let
&l _ fractional change for 1-pole
_ fractional change for 2-pole
_I _ (_i)(1+ nl)
.,2= (2 J'F"s2 )(1 + _2) .
Then, solving for _ and
I
I + 41 - I + 4X2
1 +4x2I + 16X4
4"/,2 (1-4X2),42 =+
I+I6x 4
The expressions for 41 and _ have been evaluated, and are tabulated in the
following table.
A.I-4
PHILCOIDHI_CO._O R (_ CORPORATION
Space & Re-entrySystems E:)ivi_ion
TR-DAI522A
x 4×2 t+ x4 -t00_ +1000.00 0!0000 0.0000 0.00 0.00
0.02 0.0016 2.56x10 -6 0.16 0.16
0.04 0.0064 4.10x10-5 0.64 0.63
0.06 0.0124 1.54xi0 -4 1.23 1.21
0.08 0.0264 6.97xi0 -4 2.56 2.48
0.I0 0.0400 1.60x10 -3 3.84 3.69
0.12 0.0576 3.32xi0 -3 5.41 5.10
0.14 0.0784 6.15xi0 -3 7.21 6.63
0.16 0.1024 0.0104 9.18 8.26
0.18 0.1296 0.0169 11.3 9.83
0.20 0.1600 0.0256 13.4 11.3
This data is plotted in Figure
A.I.3
A.I-I.
Croup Delay for Small Relative Detunlng, X:
The phase expressions given in Section 2. can be simplified as follows
when X is small
@I _ -2X radlans
_2 _ "2d_2"X radlans.
This results in the following simplified expressions
aI ,_-#2t
I
2j-T(1 + 1 2
ghere the _ values are in radiane, as noted above.
A.I-5
pHII._O.IIOm Q GQRPOmATION
Space & ReentrySyltems Division
A.1.4 Circuit Element Stability
A 1tU =
o
TR-DAI522A
Aw (__!_1 1 )
o J_ n_oC°
o
1
I+ + ) + L'--6-0 0 0 0
ee AL AC -2(_ )_- +_---o o o
Aw Am B_ _ X
o o
AL + 5(: 28 Aw.... (_)L C B-o o o
A.I-6
IIIH|t.CG)-PO RO (_ONPOR&TIQN
Spaca & Re_mtrySystema Division
TR-DAI522 A
To determine the temperature stability coefficient of a 1-pole or tran-
sitional 2-pole when the phase versus temperature characteristic is known.
i.
me
e
2BCalculate --
O
Aw A_Obtain--_ from the _ vs. T
graph or the simplified expressionsAw
(Note: _- = X)
Compute_ + ACo _o and divide by the temperature increment
A.1-7
ipHI LCO-FCI R O CORPORATION
Space & Re-entrySystems Division
TR-DAI522A
APPENDIX II
DEMODULATION OF A TPAPEZOIDAL PHASE MODULATED CARRIER
[-..,LcoI_:_IIHILCO-FORO CO III_OAATION
Space _ Re.em_.rVSystems nivislan
TR-DAI522A
7
I
APPENDIX II
DEMODULATION OF A TRAPEZOIDAL PHASE MODULATED CARRIER
A.2.1 Definitions
e
8R =
M =
2_=
f(e)=
8(t) = w t = Modulation phase variablem
reference phase relative to signal carrier
peak amplitude of phase excursion
period of slope, in assumed trapezoidal modulation
waveform (%ax = w/2)
modulation function
cos[er + f(8)] = phase detector function
eo(8)= video output waveform
Note: The R.F. carrier frequency is considered much greater than the
modulation frequency.
A.2.2 Hathematical Model Analyzed
eo(8) = K cos[e R+ f(e)]
f(e) = -M
M
-rr +e < e =-i_
=-ttt
, = - _(e - _) _- _<e<rr+e
PHILCO-_O_IO (_(_ _ PO RATIO N
A.2-I
Space & Re-entrySystems Division
{/ /
TR-DAI522A
-Tr
f(O)
\ i I
'V
Y'I I
A.2.2.1 Fourier Series for f(8), the Modulation Function
A t
o E A' cos n8 + B' sin n@f(O) =i- +n=l n n
f(8) ffi nS=l B'n' sin 58 ''-
' sin 8 + B_ sin 3A + B 5sin n8 = B I
B'K n : [1.(.l)n](2__M)(_)sln he.
A.2-2
pHILCO._QRD CQmPO_ATION
Space _ ;_e-en_ry
Systems Divi_;on
TR-DAI522A
A.2.2.2 Fourier.Analysis of eo(8), the video output wavegorm:
A :o
oeo(e_.. = _-. + r.n=l A cos n@ + B sin n@
n n
rr Ao = _, e (O)deK o-rr-H_
+_+_rr = (O)cos ngde_" An ,J" e o
-_,_
+r_err
Bn = t e (e) sin nedeo
A
. o_- = cos _. - 2_) cosM + 2_ L
" " +[Z+('Z)n](c°s eR) "L-M+n_ + M-n_. J " _ cos M sln n_K An
-[1'(-1)"](,i, _) ,, i' M._ " M-,_ .uK n -- . -
A.2-3
IP.,L=ol IIHOLCO-FORO CORPORATION Space & Reentry
Systems [Division
TR-DAI522A
A.2.3 Fourier Coefficients
ee
A I = B2 = A 3 = B4 • _ 0
--_B I = -2 sin 8R 2 sin M cos _-K M+_ -
A 2 = +2 cos 8R "I M+2@ + M-2_ I " cos M sin 2_
_.nB3 = -2 sin 8 { 2K R _ sin M rsin_+3@) sin(M-3@) _cos 3@ - _ L M+3_) - M-3_
- -- _ 4_}" A 4 +2 cos 8R i _[sin_+4_)+ s,in(M-4_)] _ cos M sin"g M+4_ M-4_ -K
A.2-4
IpH,L=oJ3PHILCO-ItORO CORPORATION
Space & ReentrySystems Division
A.2.4 Demodulated Output (_ = &JMt)
AO
Co(t) = _--+ B I sin (WMt) + A2 cos (2&)Mt)
TR-DAI522A
+ B 3 sin (3_Mt) + A4 cos (4_Mt)
Note that @R can affect the phase of the fundamental component, B I sin _M t,
by only a change in sign; i.e., by El. The characteristic curve shape of
the ranging phase detector (Figure 3.2.2-4) is not predicted in this model.
A.2-5
IDyll LCO_FO Iq D COrPORATiON
Space & R_-__ntr ySysternm _b_on
TR-DAI522A
APPENDIX III. 1
DELAY VARIATION CAUSED BY REFERENCE PHASE VARIATION IN THE DEMODULATION
OF A RANGING SIGNAL WHICH CONTAINS COMPLEX AMPLITUDE _)DULATION
/
/
J
//
p_PLCO-_OnD COA_OmAT_ON
mpeoa & Rs_ntrySystema Dlvleton
TR-DAI522A
APPENDIX IIl.l
DELAY VARIATION CAUSED BY REFERENCE PHASE VARIATION IN THE DEMODULATION
OF A RANGING SIGNAL WHICH CONTAINS COMPLEX AMPLITUDE MODULATION
A3. I. From Appendix II, let
eofe) = K cosLeR + f(9) = demodulated video waveform
A3.2. Assume K # constant
= 1 + A(O).
That is, assume the ranging signal envelope is amplitude modulated with an
unwanted complex waveformhavlng no symmetry conditions but with the same
period as f(e), the desired phase modulation waveform.
A3.3. Let A(%) be represented by the Fourier series
ao _a
A(e) = _- +mZ=l(amcos me + b sin me)m
A3.4 Combining terms, using the Fourier series for cos[0 R + f(0)] obtained
in Appendix II.
eo(e)= [I+ a° ®Y" + [ A° -(am cos me + bm sin me) _- + nEll(An cos ne + Bn sin ne)]
i PHILCO I_JHILCO-_ORO CORPORATION
A.3-1
Space & ReentrySystems Division
TR-DAI522A
B3
_--(b 2 cos 0 + a 2 sin e)
A2
_-(a 3 cos e + b3 sin e)
A4
_-(a 3 cos e - b3 sin e)
B3
_--(b4 cos e - a4 sin e)
B5
_-(b 4 cos e + a4 sin e)
A3.7 The resultant phase angle is hence
tan Aed ffi
aI b2 a_
_-(A o + A2) +_-(B I + B3) + _(A 2 + A4) + ...
ao bI a2 b3
(I+_--)(BI) +_-(A ° - A2) - _-(B 1 - B3) +_--(A 2 - A4) + • •
A3.8 For _ _ 1 (modulation approaches square wave) and ao/2 _<.i, the
expression simplifies to
alA o 2b2B 1
2 3
biAo a2B 1
B1 +"2 3
tan Aed
where
A _ 0even
B3 _ 1/3 B1
B5 etc _ 0
A •3-3
•I IF ImHILCO-FOPO CORPORATION
Space jr. Re-entrySystems Division
TR-DAI522A
a A a
eo(O ) = (I +_-_)(_-S) + (i +_) l_. (A n cos nO + Bn sln nO)
A
+ (_)E (an cos m9 + bn sin me) +. [Z(am cos m0 +bin sin mS)]
[Z(Am cos m0 + Bm sin n0)]
A3.5 The last term then becomes
O_
n_l_--l<nAncos_o,innO+bBn sin mO sin nO + a Bm n
cos mO sin nO +
b A sin mO cos nO)nn
3, r'" ""mn __ _oosl(_+_)o_ +
a B bA ]}-l, {sln[(m+n)e] sln[(,.-.,)o ]}+ n n{ _"m n . -- s,nL(m_n)el+Sln[(m-n)eJ2 .J
A3.6. Evaluating only for the fundamental term, and noting Aod d
from Appendix II.
(eo)1
a A
= (_ + _)(s I sin e) + --(_)(a I cos e + bj. sin e)
= Beven _ 0
A2
+ _-(a I cos e - bI sin e) -
A,,oh
+ _-_(aI cos e - bI sin O)
B1
+ _-(b 2 cos 0 -a 2 sin 0)
A.3-2
[PH'L=OI pMILCO.FO_O CO I_ PC) _ATION
Space _ Re-entrySystems Division
TR-DAI522A
APPENDIX III.2
DELAY VARIATION CAUSED BY REFER]L_CE PHASE VARIATION IN TH_
DEMODULATION OF THE RANGI_ SIG_AL - AN IDEALIZED MODEL
DNgLCO-FOR D COmPOINATIO_
Bplloe & RS).en_r.y
TR-DAI522A
APPENDIX III.2
DELAY VARIATION CAUSED BY REFERENCE PHASE VARIATION IN THE
DEMODULATION OF THE RANGING SIGNAL - AN IDEALIZED MODEL
A pictorial representation of ranging delay due to reference phase variation
is illustrated in Figure A.3-3. Sketch A.3-3b shows the phase relationship
between modulated and unmodulated carrier. At t=to, the phase deviation
waveform (A.3-3a) advances the phase of the carrier +180 °. Again at
t=I/2 T498 the carrier phase is acted on and caused to shift -180 °.
Of interest is the video output of this phase modulated waveform which is
approximated by reference signal sampling of the ranging signal (A.3-3c).
If the reference signal is exactly at -90 ° with respect to the unmodulated
carrier, then it's output will be as shown in Sketch A.3-3d. However, if
the reference signal is shifted_ say • 45 ° , the video output will undergo a
delay variation as shown.
From Figure A.3-3
45 ° at 9.56MHz ffi 4__5_5 = 2.52 ° at 498 KHz.19.4
The following general relationship can be deduced:
f498 I
Phase Slope = --" i-_.4• f9.56
= 0.0515 degrees @ 498 KHz per degree @ 9.56 MHz.
This simple illustration shows qualitatively the minimum delay in the
• demodulation process due to reference signal phase shifting.
A.3-5
PMILCO-FORD CO_ORATION
Space & ReentrySystems Division
TR-DAI522A
/
oD
N
IIII
I.I
IF-,IIIIIII
IIII
I
II
II
IIIIIII
I
:z;_
\
I\
o
+ I ÷
_A, _ _ _.. |
0 , 0 ,
I1=0
III
III
41t_
4_
0
0
0
I
41
tPH'LCOPHILCO-IIORO CORPORATION
A.3-6
Space 1_ R_-_ntPySystem _ -=;ivision
0.0
00
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!i
i,
A.3-?
DHILCO-_OaO COmPO_T_N8paoe Jr- _-entry
ayatem5 [_ivision
TR-DAI522A
APPENDIX IV
TRAPEZOIDAL WAVEFORMPHASE MODULATION SPECTRUM ANALYSIS, USING
THE RESULTS OF THE D_ODULATIONA}_LYSIS
PHILCO.POAO CO_BOMAT_NBpI©I & ReentrySystems Olv1_ion
TR-DAI522A
APPENDIX IV
TRAPEZOIDAL WAVEFORM PHASE MODULATION SPECTRUM ANALYSIS, USING
THE RESULTS OF THE DEMODULATION ANALYSIS
A.4.1. e(t) = cos[ w t + f(e)]O
= instantaneous R.F. voltage
A.4.2. f(8) and 8, 8R, M, and _ as previously defined
A.4.3. cart + ev S.B.'s vect: [cos f(B)] cos w tO
odd S.B.'s vect: -[sin f(e)] sin w tO
A .4.4.
A.4.5.
0
REF.
+M
Evaluation of cos f(8) and sin f(8) from demodulation analysis (Appendix II)
cos f(9)
,in f(e)
= cos [SR + f(e)]
= cos [eR +
ev. @ BR = 0°
ev. @ eR = -90°
A.4-1
lo.,.=oj 3PMILC¢)-FO_O COAPORATION
9pace £_ R_-etatrySystems D_vis_on
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Cos f(@)
sin f(s) =
Ao
__+ r A cos(n%t)_=2,4,6,"" n
Bn sln(n_Mt)n=1,3,5,-'"
where :
Ao _= I _0 T . 2@) cos M + 2@ sin M
2_]a[sin(M+n@) sin(M-n@)q 2 cos M sin n@}An = _[_L M+n_ + M-n@ -J " n
n = 2,4,6,'-"
n = 1,3.5,-"
A.4.7
Carrier =
Ao
-----cos u) CZ O
ev sldebands" (Z An cos n_MC ) cos w Co
n = 2,4,6,'"
PHI I.CO-FO RO CORPORATION
A.4-2
Space ELIRe_ntrySystems Division
TR-DA1521A
A.4.8. Odd sidbands: -(_ Bn sin n_t) s_.n w t
0
Bn
r..q__sin (Wo + n_)t
B11
z -T- sln(_o - n_)t
A.4-3
L PHILCO I_
PHILCO-FORO CORPORATION
IBpaoo s= Re.entr V8ynutomm Olvlmlon
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Ip-,-=°l_P_'q_CO- _'OqD CORPORATION
A.4-4
Space _ Re-en_rySystems Div_o_
TR-DAI522A
APPENDIX V
TRANSPONDER PHASE ANALYSIS
[PH'L=OI_"PHILCO-_Om_ CORWOAATION
8pace _= IRe_ntrySystems C)ivlgion
TR-DAI522A
7/
APPENDIX V
TRANSPONDER PHASE ANALYSIS
A block diagram, Figure A.5-1, was developed to explain the transponder
carrier phase measurements. Figure A.5.2 is a dlagram of the transponder
phase detection relationships.
Only elements known as significant contributors to phase shifts were noted
In addltlon,only transfer functions are shown. Driving pol,t-lmpeda_ce
interface effects were not taken into account although subsequent tests
indicated interface problems do contrlbute to phase shiftln so=a "instances.
A.5.1 Explanation of Symbols for All F!_ures
I j
O Amplifier
S,--mlng Junction
Amplifier of Galn "N"
Composite representation of an amplifier which contributes
a galn N and a phase shift, Oampllfler, where 6ampllfle r is
the sum of all phase shifts within the amplifier referenced
to an equivalent output value.
A.5.2 Analysis of Transponder Carrier Phase Relatignships
A.5.2.1 a 1 l+'r2S
_.(1+--_1S ) and K " KDK v
A.5.2.20vc o - KG(elV - ellI)
1- ,G{[_ Ovco+ %,]- [3evco + e._- (es_z_,
IP.,.=ol PHII.¢O-FOmO CORPORATION
A.5-1
+ lo8O,co+36e;
mpece & Reentrylystems Divimion
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O
OO
oo
A.5-2
Space & Re-entrySy.ste r_ _ I:_ivision
IP.,.col PMILCOo_ORO CORPORATION
/fL/
:1
0
o_o_
t
r_ .
0
r
<>
/ :
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I
u_
I_d
/_
ftm1.1
I
Ill
I.i04.1I,.III
I1
II10q
"0
0
I
tN
G
A.5-3
"[ Pi.-IILCO :._]Space & R_-_nt:ry
Systems Division
TR-DAI522A
A.5.2.3.
A.5.2.4.
_CO(I + 110% KG) = KG(e% - 8_ + (SS)IV - 368_ - 836 + 847.8
/
A (eS)IN .,(e= " 36 " 047.8 + 09.56)' "
Receiver, N0.1 Six-Pack
(368_ + 8_ - e_)
Recelver, No.2 Six-Pack
- 89.56)
A5.2.5. _KO8Fro= II0_KG+I
A.5.2.6.6VC 0 =
'r2
lto s + tto S2 + .r1 .... ,rl
= _(S) 4.098(S + 13.333)
(S + 13.751) (S + 439.06)
A.5.2.7.(8s)OU T = 120 8VCO + 30(84 +%M ) + 830
Receiver No. I & Transmitter six-pack
No. 2 slx-packs
NOTE:
a. _ = _(S)=ES(S) inputs, these inputs should be considered general
functions having the angular amplitudes designated
b. The APC loop is considered to be "Inlock" for all time
c. System constants are as follows:
T1 ffi276 sec
72 ffi75 Msec
K = 754 radians/volt-secV
KD = 20 volts/radian
d. @_ and Q_' are in the VCO module.
A.5-4
I_:_
IbI'41LCO-_D_D CORPORATION
Space _ Re-entrySystems Division
A.5.2.3.
TR-DAI522A
_co(l + II0½ KG) = KG(O_ - O½ + (es)iv - 36e_ - 036 + 047.8
11
i
A.5.2.4._ A (0S)IN ,(O ,= " 36 " 047.8 + 09.56)
J
Recelver, No.l Six-Pack
(360_ + O_ - 0_) J
Receiver,No.2 Six-Pack
A5.2.5._KG
8VCO = 110%KG+I
A.5.2.6.8VC O =
%%(s+
11o KKD'2+t 110 KKDS2+ S+
= _(S) 4.098(S + 13.333)
(S + 13.751) (S + 439.06)
A.5.2.7.(es)ou T = 120 °vco + 30(04 + 8.M) + 030
Receiver No. l & Transmitter six-pack
No. 2 slx-packs
NOTE:
a. _ ffi_(S)=Z0(S) inputs, these inputs should be considered general
functions having the angular amplitudes designated
b. The APC loop is considered to be "inlock" for all time
c. System constants are as follows:
T1 = 276 Sec
_2 ffi75 Msec
K = 754 radians/volt-secV
KD = 20 volts/radian
d, @_ and @_ are in the VCO module.
A.5-4
• IIHILCO.FOIqO CORPORAT|ONI
Space & Reentry
Systems Division
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A.5.3 An Analysis of the Effect of VCO Crystal Frequency Drifts
Expressed as an Equivalent Input DC Voltage Change
Figure A.5-3 VCO Loop Block Diagram
A.5.3.1evco(S)= G(s)
vi(s) 1+H(s)c(s)
A.§.3.2 evco(S) = S2 +(II0½ KvKDT2+II_ - S'+ Ii0_ KvK D = (S+13.751)(S+439.06)
, vI / vI
NOTE: See Figure A.5-6 for typlcal graph of VCO equivalent D.C.
bias change vs temperature
A.5-5
PHILCO _ORO COAPOmATIONSpace & ReentrySystems Division
TR-DA1522A
I!
I,,I
ILl
h
!
I
?
0
0hi
v
I,-ZI11>hi
Izl
g
o
o_.1
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III
,W
o
o
!
lu
A.5-6
Space & Re-anCrySvstem; _Jiv{siQn
TR-DAI522A
d
.... |
II
A.5-7
0
,q
_ d
_:_pace & i:le-entry
_ys._em s _ivisian
I I I I I I I
I
OD
,-_0
;::> ,.C:
4o
0_
or_ v> o
v
0
!
!
A.5-8
I
• I_
mHIL_O-FO_O =OR_ORATIONSpace & Re-entrySystems Division
TR-DAI522A
7
/
APPENDIX VI
FREQUENCY RATIO STUDY; ANALYSIS OUTLINE
[PH'L=OI pMILCCI. ImO R O CORPORATION
Space & ReentrySystems [::)lvlslon
APPENDIX VI
TR-DAI522A
FREQUENCY RATIO STUDY; ANALYSIS OUTLINE
TENTATIVE RESTRICTIONS
For purposes of analysis let
k = 1,2,3 ... (an arbitrary positive integer)
(R1)6 /1750M= f. ISSOMc 1_2200 Hc _ fd _ 2300 Mc
"2300/1850
2300/1850 =
2250/1800 =
2200/1750 =
fd/fu ¢ 2200/1750 t
46/37 = 1.2432
5/4 = =1.250044/35 1.2571
For reference only
(not part of R1)
R2. * _ f _ 50 McO
(R3)4 * ¢ fl ¢ i00 Mc
(R4) 3 8 Mc ¢ f2 _ 12 Mc
R5. * _ Bu < 2f °
R6. * < B 1 < 2f °
R7. * ¢ B2 ¢ 4.7 Kc
R8. * < B_ < *
R9. * < Bd
• Undermined limits.
PHI&,CO-POIR O CORPORATION
< 2fO
A.6-1Space & Reentry6ys.tems Division
(RI0) I fu # kfo
RII. fu _ kf2
TR-DAI522A
RI2. fu # kfl
RI3. fl # kfo
RI4. fl _ kf2
RI5. f2 _ kfo
RI6. fd = kfo
(R17) 2 fu **= fd - (k & _)fo
(R18) 7
(19)5
a = 'rrk, 2 £ k '_ 5
-A-b = k, 2_;k<
R20. c = kl/k 2, k 2 >k 1
k 1 = 1,2,3,...
k2 = 1,2,3,...
(R21)8 d " rrk, 2 _ k _ 5
NOTE: The brackets indicate only those restrictions actually used,
and the subscript indicates the order of usage.
Locates f midway between harmonics of f .u O
* Undetermined limits.
A.6-2
I PHILCOJ_j
PHILCO-FOg O CO I_PQRATION
Space & Re-en_;r'ySyatam_ Division
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A6.1. A Conditlonsal Choice of "C"
Assumptions:
RI0. f _ kfU O
RI7.1
fu = fd " (k • _)fo
Pertinent Formulas:
fd = dfo
fu/fo = a • (b_c)
Results:
fu/fo = a • (b_c) # k
Since a, b, and k are integers, c is not an integer
1fu/fo = a • (b_c) ffid - (k • _)
1A.6.1.1 C - --
2
A.6.2 Bounds on fO
Assumptions:
R4. 8 Mc
A6.1.1. c = I2
f2 _ 12 Mc
Pertinent Formulas:
4.3.1.4. f2 - C fo
A.6-3
[PH,'=OJ _MtUGO,_O_E) _ORpORATtQN
Spa=e & Re-entry6yste_s [Division
Results:
8 Mc _ I12 fo < I_ Mc?
A6.2.1 16 Mc _ f _ 24 McO
A6.3 Upper Bound on "b"
Assumptions:
R3. * _ fl S I00 Mc
R4. 8 Mc _ f2 _ 12 Mc
1A6.1.1. c _
Pertlment Formulas:
A6.2.5. ft/f2 = (b&c)/c
Results
fl max + I)bma x = c f2 min
= 1/2(-_-+ 1) = 6.7.5
A6.3.1 b = 6max
A.6.4 Lower Bound on fl
Assumptions:
R4, 8 Mc < f2 < 12 Mc
RI9. b = k, 2 < k <*
1A6.1.1 c -_
DHILCO-FOR O COPPO_ATION
A.6-4
J
TR-DAI522A
Space & Re-en_rySystems Division
Pertinent Formulas:
A6.2.5. fl/f2 = (b-_c)/c
Results:
fl mln ffif2 mln (
- (8 Mc)(_)
A6.3.1 fl mln = 24 Mc
A6.5 Bounds on "a" and "d"
Assumptions:
fl _ 1850 M:_R1 750 Mc _ fu
[.2200Mc s fd _ 2300 Mcj
R19 b = k, 2 _ k _*
A6.1.1. c - 1/2
A6.2.1. 16 Mc < f s 24 McO
A6.3.1. b = 6
Pertinent Formulas_
4.3.2.1. fu/fo
4.3.2.7. fdlfo
- a 4. (b_c)
-d
"l PHILCO _i_]IIHILCO-FO I_ O CORPORATION
A.6-5
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Space & Re-entrySystems Division
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Results:
fu mtn
fO maX
fU max
fo mln
fd mln f
< d _ fu max-fo max o mln
f= U mln
[a :_ (b-+-c)]mi n fO max
f_ u max
[a "- (b_c)]max fo rain
d
min
1750: 2_ = 72%
1850 5= l----T=11sg
fd rain = 220_____0= 91 2f 24 3
0 max
fd maxd =
max fo rain
= 230._._.00= 143_16
A6.5. I5
72% _ a • (b:_::) _ 115_
91 2/3 _ d _ 143_
IBounds an "d" using A6.5.1 and C =
A.6.5.2 92 _ d _ 143
Minimum bounds an "a"
A6.5.3 71 g a _ 109
A.6-6
.LPH,-=oI IIH|LCO.FORO CORDORATtON
Space & ReentrySymtems Division
A6.6 Prime Factors
TR-DAI522A
¢i?(*;
Assumptions:
R19. b ffi k, 2 a k a,
AI.1. c =- 1/2
A3.1. b = 6max
A5.2. 92 ¢ d _ 143
A5.3. 71 _ a _ 109
Results:
No.m
1
2
3
4
5
6
7
8
9
10
11
12
13
trait
71
72
73
74
75
76
77
78
79
8O
81
82
83
Prime No.'s
71
2,2,3,3
73
2,37
3,5,5
2,2,19
7,11
2,3,13
79
2,2,2,2,5
3,3,3,3
2,41
83
NO. "a"
14 84
15 85
16 86
17 87
18 88
19 89
20 90
21 91
22 92
23 93
24 94
25 95
26 96
A.6-7
Prime No. 's
2,41
5, 17
2,43
3,29
2,2,2,11
89
2,3,3,5
7,13
2,2,23
3,31
2,47
5,19
2,2,2,2,2,3
NO. "a II
27 97
28 98
29 99
30 I00
31 I01
32 102
33 103
34 104
35 105
36 106
37 107
38 108
39 109
Prime No. is
97
2,7,7
3,3,11
2,2,5,5
101
2,3,17
103
2,2,2,13
3,5,7
2,53
107
2,2,3,3,3
109
ire:pHi LCO.IIIOR D CORPORATION
Space x: Re-entrySystems Division
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No.m
1
2
3
Ilbll
2
4
Prime No._s
J
2
2,2
No.m
4
5
t I'btt
5
Prime No. 's
5
2,3
A.6-8
PHII,.CO.FO RO CORt, mORATfO N
Space & Re-entPySystems Division
No. Ifdt! Prime No 's. NO. II d If
TR-DAI522A
Prime No 's.
I
2
3
4
5
6
7
8
9
10
11
12
13
14
15
16
17
18
19
20
21
22
23
24
25
26
27
28
29
30
92
93
94
95
96
97
98
99
I00
I01
102
103
104
105
106
107
108
109
II0
III
112
113
114
115
116
117
118
119
120
:121
2,2,23
3,31
2,47
5,19
2,2,2,2,2,3
97
2,7,7
3,3,11
2,2,5,5
101
2,3,17
103
2,2,2,13
3,5,7
2,53
107
2,2,3,3,3
109
2,5,11
3,37
2,2,2,2,7
113
2,3,19
5,23
2,2,29
3,3,13
2,59
7,17
2,2,2,3,5
ii,Ii
31
32
33
34
35
36
37
38
39
40
41
42
43
44
45
46
47
48
49
5O
51
52
122
123
124
125
126
127
128
129
130
131
132
133
134
135
136
137
138
139
140
141
142
143
2,2,31
3,41
2,2,31
5,5,5
2,7,9
127
2,2,2,2,2,2,2
3,43
2,5,13
131
2,2,3,11
7,19
2,67
3,3,3,5
2,2,2,17
137
2,3,23
139
2,2,5,7
3,47
2,71
11,13
A.6-9
PNtLCO-_OmO CO_OO_AYlON
_pace _ Re-entrySystems _ivi_ion
TR-DAI522A
Summary 0f usable values:
Assumptions:
RI8. a - _k ,
RI9. b = k ,
R21. drink ,
A6.1. c = 112
A6.3. b = 6max
A6.5.2. 92 <
A6.5.3. 71 <
d < 143
a _ 109
2 _ k _ 5
2 _ k _; 5
• No. a b d,.,. J,. , • • ,,, ,
1
2
3
4
5
6
7
8
72(2,2,3,3_
75(3,5,5)
80(2,2,2,2,5)
81(3,3,3,3)
90(2,3,3,5)
96(2,2,2,2,2,3)
100(2,2,5,5)
108(2,2,3,3,3)
2
3
4(2,2)
5
6(2,3)
.96(2,2,2,2,2,3)
100(2,2,5,5)
108(2,2,3,3,3)
120(2,2,2,3,5)
125(5,5,5)
128(2,2,2,2,2,2,2)
135(3,3,3,5)
mMIt.CO-_O_O COAPOPATION
A.6-10
Space & ReentrySystems DivisiQn
TR-DA1522A
A6.7 Tentative Choice of fd/fd = r
t
As ions /sumpt :
A6.1. c m 1/2
A6.6. See table, summary of values on previous page
f > a£u o
fl < bfo
Pertinent Formulas:
Results:
fu/fd = d/[a "4"(b::_)] A r
(Using Mariner C sign choices)
r = dlEa + (b-c)]
A6.7.1 Table o£ a+(b-c) for usable values of a,b, and c.
No__ a a+2__ _ a_ - _ a+5 - _ a+b.-
1 72 73_ 7_ 75_ 76_ 77_
2 75 76_ 77_ 78_ 79_ 80_
3 80 81b 82_ 83_ 84_ 85_
4 81 s2_ 83_ 84_ 8_ 86_
5 90 gl_ 92½ 93_ 94_ 95_
6 96 97_ 98_ 99_. i00_ I01_
7 100 I01% I02_ 103_ I04_ I05_
8 108 109% ilO_ I11_ I12% 113%
A.6-11
PHILCOJ_._pHI_CO-_OAO CorPORATiON
Spaa:e _ Re_sntrySystems oivision
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A6.7.2 Prime Factors of 2[a+(b-c)]*
No__;. a+(b-c) 2[a+(b-c)]
1 73% 147
2 74% 149
3 75% 151
4 76% 153
5 77% 155
6 78% 157
7 79% 159
8 80% 161
9 81% 163
10 82% 165
11 83% 167
12 84% 169
13 s5% 171 "
14 86% 173
15 9{% 183
16 92% 185
17 93% 187
18 94% 189
19 95% 191
"[a + (b - c
for r =
• Prime Factor
3,7,7
3,3,17
5,31
3,53
7,23
3,5,11
13,13
3,3,19
3,61
5,37
11,17
3,3,3,7
I
)J is multiplied by 2 in anticipation of a rational fractionfd
f •U
A.6-12
phi I.CO.I_OA D CCIRPO RA'rlON
Spm=e _ ReentrySymtems [Division
TR-DAI522A
A6.7.3
.o._._ a+(b-c) 2Ca+(b'c)1
20 97_ 195
21 98_ 197
22 99_ 199
23 100_ 201
24 101_ 203
25 102_ 205
26 103_ 207
27 104_ 209
28 105_ 211
29 109_ 219
30* 110_ 221
31 111_ 223
32 112_ 225
33 113_ 227
Tentative Choices of a+(b-c)
No..._.:.. a+(b-c) __a
1 112_ 108
2 94_ 90
3 73_ 72
Present S-band value.
5 1/2
s 1/2
2 1/2
A.6-13
•Prime Factor
3,5,13
3,67
7,29
5,41
3,3,23
11,19
3,73
13,17
3,3,5,5
] PHILCO I_PHILCO-PORD CORPORATION
Space & ReentrySystems Division
TR-DAI522A
Prime Factors:
/
2(112_) = 225 = 3 x 3 x 5 x 5
2(94_)
2(73_)
a
a, m
a =
ffi 189 ffi 3,3,3,7
= 147 ffi 3,7,7
= 108 = 2 x 2 x 3 x 3 x 3
90 = 2 x 3 x 3 x 5
72 = 2 x 2 x 3 x 3
A6.7.4 Resultant fd/fu = r
No. a+b-c d r
1 I12_ 135 I.2000
2 94_ 120 1.2698
3 73_ 96 1.3061
The best all-around choice is No. 2, and the final results are as follows:
fd d 120
f _b-c 9_U
2x2x2x3x5 8Oz
(2x3x3x5) + 5 - I/2 63 "
The final transponder configuration is shown in Figure 4.3-2.
[!i aPMILCO-FOq O COAPORATJON
A.6-14
Space & ReentrySystems Division
TR-DAI522A
A6.7.5 Loss In Tuning Range
r =_ .5 (This value provides optimum tuning range)
u mtn ffi 5 fd mtn = (2200) = 1760 Mc
ffi4 fd ffi 4(2300) " 1840 Mcfu max max
r = 80/63:
80 80(1750) 149000 2,222_fd mln ffi_ fu min ffi63 = 6---_ =
f 63 63 _ 1,811%u max =8"6 fd max =_(2300) ffi 4
Result:
r fu mln f BW fd-- u max _ mln
5/4 1760 1840 80 2200
80/63 1750 1811% 61% 2222_
Loss of BW = 80 - 61% = ldMc
fd max
2300
2300
BWd
I00
A6.7.6 Transponder Nominal Frequencies
fd mi___n= fd mi__dd= fd ma_.._x= r
_umln _umld <max
fu mln/ max/
A.6-15
PHILCO.FORO CO I_1PO RATIO NSpace & Re-entr¥
Systems Divi_ion
TR-DAI522A
fd mid Sfd rain fd max
fU told _fu min fu max
fd mid "_/ fd rain fd max
_J_140,O00, 2300 =J5,111,1119 ,, 2260.6963
fd mid = 2260.79 Hc
2260.79fu mid =
1.2698
= 1780.43
fu mid ffi 1780.43 Mc
fd 2260.79f lit _ I
o d 120ffi18.840
f - 18.840 Mc0
1£2 " Cfo I _'(18.840) = 9.420
f2 " 9.420 Mc
fl" ('_)f2 " 5-'_ (9"420) " 84.780
fl " 84.780 Mc
A.6-16
• _r.._'_:-_
PHIt.(:o,Fr_ m O ¢;0 m _0 RATICI N
Space & Re-entrySystems Division
I,:,,...=,:,I!pMIt.CO-ROAD CORWOmAT#ON
1
2
3
5
7
11
13
17
19
23
29
31
37
41
43
47
53
59
61
67
71
73
79
83
89
97
101
103
107
109
REFERENCE
PRIME NUMBERS
A.6-17
113
127
131
137
139
149
1.51
157
163
167
173
179
181
191
193
197
199
211
223
227
229
233
239
241
251
257
263
269
271
277
281
TR-DAI522A
6paom & Reentrygymtemm Division
TR-DAI522A
APPENDIX VII
TEST INFORMATION FOR S-BAND/"VCO"/RANGING PHASE SHIFT VS TEMPERATURE
IDHIL=O-FOmD =ORPORATJONSpace _ I_._-mntrySystem_ O_v.L_I on
TR-DAI522A
APPEI_IXVII
TEST INFORMATION FOR S-BAND/"VCO"/RANGING PHASE SHIFT VS TEMPERATURE
The test information that follows describes the application of the ranging
equipment as utilized for the measurements made in this study. Information
on theory and procedure of operation for the MotorolaMariner S-band trans-
ponder Test Set, can be found in Motorola documents 68-26429C and 68-26430C.
A.7.1 GENERAL POINTS OF INTEREST
1. The equipment was connected as shown in the test setup block
diagramFigure 3.1-1.
2. The part of the transponder to be temperature tested was placed
in the test environment. In order to insure that room tempera-
ture variations did not cause the rest of the test transponder
to be the source of phase variations, the remaining portion of
the test transponder was placed in a reference oven.
3. After connecting the module with the rest of the transponder,
via appropriate interconnection cables, a preliminary check was
made to see that everything was operating correctly (seepreliminary
transponder checks Section A.7.3)
4. The test set was left on continuously because, at the early
pert of the program,the daily log of ranging delay showed
about • two day stabilization time after weekend shutdowns.
The transponder was only shutdown during the time a different
pert of it was placed in the test oven.
5. The Rustrak recorder charts were adjusted at the beginning of
each temperature test to correlate with the actual time of the
day. Two other recorders, used to monitor room temperature
and AC line voltage, were also adjusted to correlate with actual
A.7-1
[pN,L=ol PHII.Ct3-1cORD COIq pDImATDI3N
Space & ReentrySystemn Division
TR-DAI522A
.
.
A.7.2
time so that any variation observed on the S-band charts .-
could be corrected for posslble room temperature and
llne voltage effects. The recorder speed was one inch per
hour which permitted convenient recording of the S-band phase
changes.
Two transponders were used for the test. One was used only
to supply coherent reference signals to the "VCO" and S-band
phase detectors. To insure a phase stable reference, the
temperature and power input of the reference transponder were
maintained constant. A reference temperature of 45°C was
used to ellmlnate a need for refrigeration to maintain constant
temperature.
The DC supply power to the isolation amplifier of the reference
transponder was disconnected to turn its ranging channel off.
This made the S-band chart recordings trace smoother because
of reduced phase noise in the reference signal. The ranging
channel of the test transponder was left on continuously
because the switching action caused cog Jumps of the "VCO"
phase. (See Section 4.2.1) The phase noise on the S-band
recordings was only about a pen width in amplitude.
HIGHLIGHTS OF TEST METHOD
le
.
With the part of the test transponder to be tested placed in
the test environment and properly connected to the rest of the
test transponder in the reference oven, the test was begun
by lowering the temperature tO-10°C and allowing at
least a two hour stabilization time. The chart recorders
were not started at this time.
After stabilization, ranging phase was measured at three power
levels, -70 DBM, -90 DBM, and -110 DBM. This measurement was
done by first making a doppler phase reading with the transponder
connected to the test set. Then, the frequency converter was
A.7-2
P_UCO-FORO _OR_OmATION
Space & ReentrySystems Division
TR-DAI522A
,
.
.
connected to the test set, and, by means of the test receiver
input attenuator and the ranging modulation level control,
the test receiver AGC and the ranging correlation voltage,
respectively, were made to match those recorded while the
transponder was being measured. The doppler phase reading
of the frequency converter was subtracted from the transponder
reading to give the transponder delay. Since the delay
through the frequency converter wasn't actually zero, the
absolute delay of the transponder is in slight error. However,
since the frequency converter reading was taken at each power
level at all temperature being tested, the relative ran_In_
delay change with temperature is accurate.
The S-band phase voltages were read on a digital voltmeter as
a function of input power to the test transponder. '_CO"
phase shift was also recorded at the same levels which was
from -70 DBM to -140 DBM in I0 DB steps. At the same time
all the data asked for on the data sheet (Figure A.7.1) was
recorded.
The input power was then returned to -70 DBM and the S-band
chart recorders were fixed to record. The temperature at this
time was changed to the next higher value. If the S-band
phase changed considerably with temperature, 5°C temperature
steps were made to keep the recordings legible. If little
S-band phase change was noticed with temperature, the complete
temperature change was made in one step. When whole six packs
were being temperature tested, an hour was allowed for stabili-
zation, while only 45 minutes was used in module tests.
At the end of the stabilization time, the S-band recorders were
set to stop recording, but allowed to keep running to keep the
chart correlated with the actual time of the day. The ranging
S-band and 'WCO" phase measurement were made at this time and
upon setting the charts to record, the procedure repeated until
75°C was reached.
A.7-3
IpH,L=°DI_|L(=O.WO R D (::O I_1_ORATIO N
Space & Re-entrySystems [Division
TR-DAI522A
A. 7.3 PRELL_IHARY TRANSPONDER CHECKS
I. All connectors tight (especially microdot)
2. X30 output spectrum
3. (a) Receiver in, and out, of lock
(b) Ranging on, and off
3. No signal receiver SPE < _100 my.
4. Receiver phase noise maximum peak _ 9 °, uasurad at
transponder receiver SPE test Jack; Pin = -70 dbm
5. Transmitter phase noise maximum peak > 6@. measured
at test set receiver SPE test Jack
6. Receiver AGC curve (approx. values)
Pin VAGC
(dt_) (vdc)
-70 -7.0
-90 -6.5
-110 -5.8
-152 -2.0 (threshold)
-" +1.8 (no signal)
7. False lock Is indicated if VAGC is some negative value
8. Check X36 spectrum (2.0655Gc) at transponder invut
Check TLMmodulatlon sensitivity
Check frequency for "O" volts SPE
a. "receiver phase error"
b. "transmitter phase error"
A,7-4
DNILCO.POIIIID £ONWOMAY;ON
|pill=| ; Re.entrymVmtemm [Division
J
TR-DAI522A
A.7.4 Stability of the Test Set Frequency
7 _
!The manner in whlch the stability of the test set VCO was determined
was by the observation of the transponder SPE. During the testing of
the transponder when the VCO module was in the test oven, the SPE was
noticed to change only .02 volts throughout an entire temperature test.
The manual setting of the test set VCO frequency was not changed during
any particular temperature test. Since the temperature of the trans-
ponder VCO was kept constant in a reference oven, any SPE change will be
due to test set frequency changes. The VCO frequency sensitivity is 120
Hertz per volt. This means, for a .02 volt change, there is only a 2.4
Hertz drift in the transponder VCO frequency due to the change in test
set VCO frequency change with varying room temperature.
A.7=5
tPH'L°O,I _tt.co.womo CC]_pOmATION
Space _- Reentry6ystems [:)ivisiom
TR-DAI522A
TABLE A.7-1
JPLMARINER S-BAND TRANSPONDER TEST SET SERIAL NO. 12
I. 1362 Dynamics Microvoltmeter
2. Type M TEK Plug In (Scope)
3. 45A TEK (Scope)
4. RAN. RCVR
5. 802 B HARR (Pwr. Sup)
6. TP-12 Pwr. Sup. (CCC)
7. TP-12 Pwr. Sup. (CCC)
8. BL-IO Card Files
9. B6-10 Card Piles
10. 122AR Scope
II. Test Xmit
12. Test Revr.
13. Conv. RF
14. R-100B Philbk. Pwr. Sup.
15. 480M Lambda Pwr. Sup.
16. QR. I0-I0 NJE-Pwr. Sup.
17. 802B Harrison Pwr. Sup.
32-13423
J2-19778
J2-22612
J1-862
32-19541
J2-12003
J2-11994
32-11981
J2-11985
J2-13422
J1-863
J1-839
Ji-29461
32-33325
32-33324
32-33326
J2-33327
[PH,L=O] IBl.,t I L, CO. FO R IO CORPO ¢:IATION
A.7-6
Space _ Re-entrySystems Division
TR-DAI522A
TE_ °C POWER
SUPPLIES
RCVR -15
+15
EXCITER 15
-25
S-BAND
(Cycles) SPE
!POWER S-BAND
LEVEL O °
Volts
-70DBM
-80
-90
-i00
-ii0
-120
-140
S-BAND
Degrees
8 0 AGC I.F. ATTN
No.
MOD.
90 °
I
CORR.
VOLTS
NOTES:
I. S-band cycles are measure from the preceedlng temperature
2. (+) above at S-band cycles means advancing
Figure A.7-1 JPL Transponder Temperature Test
(Sample Data Sheet)
A.7-7
IPHILCO FO_ _ORPORATION
Bpace & Re-entrySystems Division