hypersonic research vehicles - nasahypersonic research vehicles ? space division ... -cost the...
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'" ,f '!'\f • ~~-----
-~--~-
! PEN00254
HYPERSONIC RESEARCH VEHICLES
? Space Division ~ ~ North Arnencan Rockwell 82PDl14303
..... • .,.. • ••••• ~... ,. t ",
PURPOSE:
II • • • .To separate real from imagined problems & to make known the overlooked and unappreciated problems"
H. D ryde n Octobe r 1956
- FOCUS & STIMULATE TECHNOLOGICAL DEVELOPMENT . TOWARDS POSS I BlE/ PROBABLE SYSTEMS OF THE FUTURE
-VALIDATE AND/OR DEMONSTRATE SIGNIFICANTLY CR I T I CAL TECHNOlOG I ES
? Space Division ~ ~ North Amencan Rockwell 82PDl14304.
"' .. , '
X-I5 IMAGINED PROBLEMS
• ASYMMETRICAL WING COOKIE SHEET DEFLECTION DURING HEAT-UP OF RE-ENTRY
• FLIGHT STABILITY & CONTROL BEING OTHER THAN THAT INDICATED IN LANGLEY II-INCH HYPERSONIC TUNNEL WITH II-INCH MODEL
• UNSATI SFACTORY LANDI NG CAPAB I LlTY WITH LOW LID UNPOWERED CHARACTER I STI GS
• UNCOMPENSATABLE ROLL-OFF DURING B-52 LAUNCH
• UNSATISFACTORY STRUGTURAL INTEGRITY BETWEEN COLD L02 TANKS & WARM INSTRUMENTATION BAY DUE TO THERMAL STRESSES & DEFLECTION
~ Space Division ~ ~ North Amencan Rockwell 82PDl14305
X-IS OVERLOOKED - UNAPPRECIATED PROBLEMS
• WINDSHIELD GLASS RETENTION & PERFORMANCE
• WING LEADING EDGE SLOT AERO-HEATING EFFECTS
• SIDE'FAIRING THERMAL BUCKLING
.. AUXILIARY POWER UNIT LUBRICATION IN RARIFIED ATMOSPHERE
• NOSE GEAR SHOCK ABSORBTION UPON RAPID EXTENSION - OIL FOAM
• B-52 FLAP CUT-OUT ACOUSTICS
• FLIGHT CONTROL AT HIGH ~S
• AIRFRAME" GYRO DYNAMIC COUPLING PRIOR TO RE-ENTRY
• CONFIGU~ATION EFFECTS ON LATERAL-DIRECTIONAL DYNAMIC STABILlTV •
? Space Division ~ ~ North Amencan Rockwell 82PDl14306 .
f·
METHODOLOGY FOR DEFINING HYPERSONIC RESEARCH VEHICLES
-IDENTIIFY POSSIBLE-PROBABLE HYPERSONIC SYSTEMS
tlDENTIFY SIGNIFICANT AND/OR PAGING TECHNOLOGIES
- IDENTIFY THEI R APPROPRIATE SPEEDS, ALTITUDES, TEMPERATURE ETC.
- I DENTI FY THEI R TEST TIME OR TIME HI STORY REQUI REMENTS
-IDENTIFY THEIR SIGNIFICANT SIZE REQUIREMENTS
-INTEGRATE THESE TECHNOLOGIES INTO A VEHICLE, OR "FLYING-FACILlTY" CARRIER SYSTEM
• I DENTI FY THE LAUNCHI NGSYSTEM, AI R LAUNCH OR GROUND TAKE-OFF & ITS OPERATIONAL ENVI RONMENT
-COST THE "FLYING-FACiliTY", THE LAUNCH SYSTEM, THE OPERATIONAL SYSTEM & THE PHASED TECHNOLOG I ES
- RE-COST, REITERATE & RESELECT
-FINAL SELECTION OF TECHNOLOGIES, RESEARCH AIRPLANE, OPERATIONAL SYSTEM .
? Space Division . ~ ~ North Amencan Rockwell 82PDl14307
OVERALL PROGRAM CRITERIA
• COST-EFFECTIVE TECHNOLOGY ELEMENT SELECTIONS
• APPROPBIATE ~UNDING FOR SYSTEM DEVELOPMENT & TO FIRST FLIGHT
• EARLY SIGNIFiCANT FLIGHT RESULTS & CONTINUING PHASED FLIGHT RESULTS
• CONTROLLED ANNUAL FUNDING REQUIREMENTS
• UTILIZE· ENGINEERING "SPIN-OFFS" FROM OTHER PROGRAMS-e.g., SHUTILE, RL -10 ETC
• DEVELOP RESEARCH VEHICLE AS "FLYING-FACILITY", WIND TUNNEL MODEL 'ADAPTABILITY, "BOILERPLATE" FEATURES AS APPROPRIATE
• I MPLEMENT COST -PERFORMANCE TRADE-OFFS FOR VEH I CLE, TECHNOLOG I ES & SUBSYSTEMS
?' Space Division ~ :. NorthAmencnnAockwell
82PDl14308
ALTITUDE (1000 FT)
. 400
300
200
100
POSS I BLE I PROBABLE HYPERSON I C SYSTEMS
MILITARY SYSTEMS RE-ENTRY RE.:ORBIT
AIRBREATHING LAUNCH VEHICLES HYPERSONIC TRANS~ORTS
MILITARY SYSTEMS MANNED-UNMANNED INTERCEPTORS
O~--~--~--~--~--~--~--~--~--~~~~~~--~~ o 4 10 12 14 16 VELOCITY (1000 FT/SEC)
? Space Dlvtsion ~ ~ North Amencan Rockwell
82PD114309
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L SURFACE LAUNCHED INTERCEPTOR MISSILE HYDROCARBON,UNMANNED
INTERCEPTOR, HYPERSONIC TRANSPORT, HYPERSONIC METHANE METHANE BOOSTER MANNED MANNED MANNER
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82PDl143'10-1
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PRINCIPAL PROPULSION SYSTEMS/FUELS,
SUB· RAMJET, HEAVY HYDROCARBONS) Ii; I",
i . . i SUB· RAMJET, HYDROCARBONS " 'j
I: "k,
'<I) t '/' I ... ------------:-:---------, - - - - - - , LI __ ~ __ O_UA_l_M_O_O_E _SU_B_/S_U .... P._R_AM_J .... E_T ___ --'1_ _...!-'2. __ '..J
I C·t) \ ... -
\ I 'j
SUBSONIC RAMJETS, lH2
1 ,'r} I C EJECTOR RAMJETS, METHANE FUElS
I . i C GAS TURBINES, RAMJETS, METHANE FUElS
;:0 t· " ; :;: '>. I §URBINE': ENOOTHERMIC FUELS I
; ~ ; : \ \ ! :
1; "
" .. " ,}.'
o LJ .. ~_.,,,/.L. ... __ -.. L.,-,.- .. ,,.-t.-~ .. -.-.. J. . ___ ...... J""_"_"., .. J., .... ~ .. ~"._._.L ... _.,.j._,, __ 1 2 J 4 C; Ii 7 :j
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82PD 114330 .. 1
. , ;' , i. , !
MATERIAL APPLICATION TRENDS FOR SIGNIFICANT __ ... ,., .. __ .. , ___ " ....... __ .... ___ ._._._ ... ,,_._.-.. _ .... __ AREAS. OF .REPRESENTAT I VE VEH I CLES
1 .. 41----·------,.../U·:<-;-·,··' .... · ------ ACTIVELY COOLED ALUMINUM ',:.1' : !;"
,.,{ : I
t
t t
t HAVNES25 1500 -1150 f
t
TO·Nier 1150 - 2000 f
. (" .
~ " of _'~~
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....... ~"'_ •• __ .... , ""n', ~, ... , .. , , .. ",." ' •••• - •..•. ,.,...
~r;·!7~:;, ., .;.
~~p:.,ce Divl:.ion ~" :-.)"-:'4-\ ~\rr l'\. 'r ... ~ ~n f ~o::;k. '. ~.'r~H
i 1
.' 82PD 114311-1
PRELIMINARY H.R.A. REQUIREMENTS PROPULS ION SYSTEMS - FUELS
_ RECOMMEND M3.5+ ENDOTHERMIC GAS TURBINES -FUELS RESEARCH . TO YF-12 TYPE AIRCRAFT WITH HEAT PROTECTION
-INCLUDE DESIGN CONSIDERATIONS FOR GAS TURBINES,SUBSONIC JETS, & EJECTOR RAMJETS WITH METHANE .
-INCLUDE DESIGN CONSIDERATIONS FOR SUBSONIC RAMJETS WITH HYDROCARBON & HEAVY HYDROCARBON FUELS
- INCLUDE DESIGN CONSIDERATIONS FOR SUBSONIC, SUPERSONIC & DUAL -MODE RAMJETS WITH HYDROGEN FUEL.
? Space Division ~ ~ North American Rockwell 82PD114312
- ---~.,~-------~
SINGLE
- TURBOJETITURBOFAN
-TURBOJET & PRE·COOLER
- RAMJET
-SCRAMJET
- ROCKET
COMPOSITE . -SUPERSONIC TURBOFAN
- EJECTORAMJET
-SERJ
-TURBORAMJETITURBOFAN
FUELS -HYDROCARBONS
-ENDOTHERMIC
-CRYOGENIC
-METHANE
-HYDROGEN
?' Space OMslon ~ ~ North Amencan Rockwell
o
PROPULS ION CYCLE I FUEL CANOl DATES
.J
I
I
I
1
. r"///////////I
V//////////////A'
I I
I I I I J J 1 2 3 4 5 6
, I I J
I
J
I
. J
I I
I I 7 8
82PDl14313
-----.~.--- ~-------- --, -·---·~·~111
FUEL
J. P. (REG)
METHANE
HYDROGEN
J. P.
METHANE
HYDROGEN
HEAT OF COMBUSTION (BTU'S'LB)
18,600
21,500
51,750
BTU'S I ¢
10,350
10,750
5, 175 (1725)
,~, Space Division North Amencan Rockwell
PROPERT I ES OF FUELS
HEAT SINK (BTU'S'LB)
165
1,100
4,900
BTU'S I ¢
91.5 '
550
490 (163)
DENSITY (LB 'FT3)
50
26.5
4.3
HEAT SINK LIMIT TEMP
(DEG F)
375
1,000
1,000 .
AT 1. 8¢ ILB
AT 2¢ ILB
COST (¢ ILB)
1.8
2.0
10 - 30
AT 10¢ ILB (AT 30¢ ILB)
82PDl14314
FUEL CONSIDERATIONS
M' b ... x :E 30 z
CRUISE EFFICIENCY COMPARISON
a: ~ 20
c( LL
~HV~~~EN ~METHANE
~JP-4 I- 10 ~ C)
~ O~~--.. --~--.• I--~~ !XI 2 4 6 8 10 12
MACH NUMBER
METHANE COULD LOWER DIRECT OPERATING COST
1.2
FUEL
~ :E 1.0
o Ioc( OW
!!! ~ 0.8 W o
0.6
TU~BINE INLET TEMP, of FUEL PRICE, CENT/LO
1.09
JP 2200
1.8
? Space Division ~ ~ North Amencan Rockwell
CH4 CH4
2800 2800
2.0 1.2 (U.K.I (U.S.)
COMPARISON OF DIRECT OPERATING COST
2.0 ~
I
~ w !!! ~ 1.0 z w o g o
o FUEL COST
~ OTHER DOC
LARGE SST SUBSONIC (JPI
(JP)
MACH 6 HST (HYDROGEN)
!XI
15 .:::!. ~ Z
10 ~ w·
5 5:! a: Q..
o N X oJ
DOC FOR AIRCRAFT CRUISING AT MACH 10
4.0
~ I 3.0 z ~ ~ c(
o 2.0 o o
• PRESENT HST STUDIES INDICATE SYSTEM IS FEASIBLE AT 8 ¢ /LB LH2 BUT NOT AT 15 TO 30 ¢ /LB
1.0
• RANGE POTENTIAL & ECONOMICS SUGGEST SIGNIFICANT EVALUATION OF METHANE
E2ZJ FUEL
~ MAINTENANCE
III DEPRECIATION
o CREW, INSURANCE
M = 10
5000 10,000
RANGE (N Mil
82PD1l4315
.~ ~' ... --~---------"-<--------'~'-"-- '-------.-- " .... -~.--" . -" .,.,'
PROPULSION SYSTEMS-FUELS RECOMMENDATIONS
• ACQU I RE UPDATED DEVELOPMENT COST AND SCHEDULES
.. P & W J-58 ADAPTED TO METHANE & HYDROGEN FUELS & AS I~ELATED TO DESIGN MACH NUMBER
• MARQUARDT E.R.J. & S.E.R.J. ENGINES FOR METHANE & HYDROGEN FUELS
• AI RESEARCH H.R.E. FLIGHT-WEIGHT ENGINE WITH HYDROGEN FUEL
? Space Division ~ ~ North American Rockwell
USING ONLY THAT QUALIFICATI.ON APPROPRIATE TO H'.R.A. NEEDS AND FLIGHT TEST APPROACH
82PDl14316
• SHOCK LOCATION • DYNAMIC PRESSURE
INCREASE • LOCAL MACH NO.
DECREASE • BOUNDARY LAYER
THICKNESS • LONGITUDINAL & LATERAL
STREAMLINES DEVIATION
SC RAMJ ET I NTEGRATI ON
• EFFICIENCIES • INJECTORS • MIXING LENGTHS • COOLING REO'S
• EFFICIENCIES • STARTING CHARACTERISTICS • VARIABLE GEOM • INLETS INTERACTION • BONDARY LAYER
INGESTION
• EFFICIENCIES • MODULE INTERACTION • FLOW STATES
~,________________________________ J
- ~,------------------------------~
A I RFRAME - PROPULS ION COMPA TI BI LI TY INTEGRATED'PERFORMANCE WEI GHTS 8. VOLUMES DYNAMI C EFFECTS, ACCELERATION. DECELERATION ANGLE OF A TTA CK C~ PA BI LI TI ES ANGLE OF YAW CA"PA BI LI Tl ES OPERATIONAL CHARACTERISTICS
?' Space Division ~ ~ North American Rockwell
TRADE-OFFS
.82PD 114317
.. ----~---.. ---. . ....... _. -.~,~. --:--;--,--,--------
STKUCTURAL MATERIALS APPLICATIONS RECOMMENDATIONS
INCLUDE DESIGN CONSIDERATIONS FOR INCORPORATING SIGNIFICANTLY LARGE PORTIONS OF THE VEHICLE OR TEST PANELS OF:
• I NCONEL 718
• RENE' 41
.• HAYNES 25
• TD-NiC r
• ACTI VEL Y COOLED
- ALUMINUM
-TITANIUM
- RENE' 41
? Space Division ~ ~ North Amencan Rockwell. . 82PDl14318
----~------------~-----------------
250
200
150
$M
100
50
X-15 MILESTONES
NASA & USAF OPERATING COST ~ • .""e"",e
NAA FLT TEST COMPL
POWERED
GLIDE
e
AGE B-52, PSTS HI RANGE 26.41M
: A/V SUB 9. 15M.
CAPTIVE 1 . 92.0
1 84.0 ... ----62.5 .... ...r--
XLR-99 53.83M
DWG REL 56.0 ~,.
148.5 ~ i¥
. , 19.0 ~ ROLLOUTS
354,000 FT
250,000 FT 1,323F 4,104 MPH
__ ~~ (1) (2) (3)
O~~-~--______ ---L~~L-~--~----~~~--~~-----------1956
? Space Division ~ ~ North Amencan Rocl<well· 82PD1l4319
CURRENT COST STUDY IMPLICATIONS "HYFACS" CR 114322
M6 TURBORAMJET M12 ROCKET MILLIONS $ MILLIONS $
RDT&E 212 (43.3%) 126 (35. 9%)
INVESTMENT 186 (38.3%) 137 (39.1%)
OPERATING 92 (l8.5%) 88 (25.00/0)
490 351
• RE-EVALUATE INVESTMENT REQUI REMENTS TOWARD PROGRAM COST REDUCTIONS FOR ONLY ESSENTIAL DEVELOPMENT TASKS. REDIRECT COSTS INTO AIR VEHICLE DEVELOPMENT & VERSATILITY
• RE-EVALUATE OPERATING COSTS FOR MAXIMUM FLIGHT EVALUATIONS
~H4a::t) . . :!MILLION • 73/FlIGHT. 2~ FLIGHTS = 40 FLIGHTS IVEAR cao'
1"" Space Division ~ ~ North Amenc,ln Rockwell 82PD114320
- -- - , ~' ... -
q
I
_ .,.,... ~ ...... ""_,~"_,~""",,~_,,,,w~· .• '.~' 'W; " •••• _ ....... ~> •• , ....
DESIGN & FABRICATION
CHECKOUT
LR·ll FLIGHT TEST
!,}"' "1";::','T""~:i'j:v I -"~",,. ';:::"!;I':'~',:!, . .,;;,:.l":', ... ~ .,~ '~-.<''''' \,)'~',:.
",,",,: ......... ' ... , .... ". ":.
" \'~
LR·99 FLIGHT TEST
. 1 -" . ADDITIONAL fOLLOW ON
FLIGHT RESEARCH
;,S2PD114321-1
~~-"--~----- ~--~--.--.~~----~-
X-I5 SPACE TRANSPORT SYSTEM
41~ Space Division ' .,.~ North American Rockwell
SCHEDULED EXPERIMENTS THROUGH 1968
v • INDUCED TURBULENCE
V • MICROMETEORITE ATMOS DENSITY, SKY BRIGHTNESS
V .INFRARED SCANNER
V • X·15 UV MEASUREMENTS
• "'~P8Fl 8¥elE- ea8l1P48
v • ADVANCED STRUCTURES & AERODYNAMIC RESEARCH
V • UV STELLAR PHOTOGRAPHY
V • HYCON CAMERA
• BE8ElEFltAtTI8P4 BE'iISE
v' • AIR:BREATHING PROPULSION
v' • UV PLUME, INFRARED EXHAUST SIGNATURE
V • AERODYNAMIC NOISE
v' • ADVANCED INTEGRATED DATA SYSTEM
82PDl14322
ALTITUDE (1000 FT)
160
140 -
120
100
80
60
. 40
20
1
~ Space DiVIsion ~ ~ North Amencan Rockwell
2
H. R. A. SYSTEM DEFINITION DR IVERS
3 4 5 6 MACH NUMBER
• PROPULSION AIRBREATHING ROCKET
eSTRUCTURES .TANKAGE .PROPELLANTS e fliGHT CONTROLS
.WINGS
.AVIONICS eSUBSYSTEMS • LAUNCH SYSTEMS eGROUND SYSTEMS & OPERATION
7 8 9 10 11
82P0114323
. OPERATIONAL CONS I DERATIONS
eAIR LAUNCHED VS GROUND TAKE-OFF
e FERRY RETURN MODE
eGROUND TRACKING
• ONE BASE VS TWO BASE _ ALTERNATE LANDINGS
_ "ALL-WEATHER" OPERATIONS
_AIR LAUNCHED PRE-LAUNCH ROCKET ENGINE CHECK-OUT
2gTURN 160 N MI RADIUS
M8 ---~
2500 N MI RANGE 40 MIN FLIGHT 10 MIN AT M8
? Space Division ~ ~ North American Rockwell
82PD114324
OPERATIONAL EFFECIENCY - X-I5
• EFFECT OF RELIABILITY & MAINTAINABILITY OF VEHICLE SYSTEMS- PROPULS ION
AVERAGE TURNAROUND TIME
( BASED ON AVERAGE OF ) TURNAROUND SUCCESSIVE 5-FLIGHT GROUPS
40 INTERIM ENGINE XLR99 INSTALLATION 0 PROGRAM FINAL ENGINE PROGRAM
30 FLIGHT FREQUENCY
AVERAGE 0 TURNAROUND 20 (DAYS)
10 FLIGHT RESEARCH
PRODUCTIVITY
0 1 0.5 0 0.5
CALENDAR TIME (YEARS)
• LESS SOPHISTICATED ENGINE SYSTEM
• LOWER MACH NO. . FLIGHTS
• WIO R EACTI ON CONTROL SYSTEM
? Space Division ~ ~ North American Rockwell
• MORE COMPLICATED ENGINE SYSTEM
• MORE ENGINE RUN-UP'S REOD
• RECOATING ENGINE NOZZLE
• HIGHER MACH NUMBER AND HIGHER ALTITUDE FLIGHTS
82PDl14325
OPERATIONAL EFFECIENCY - X-I5 (CONT)
-EFFECT OF RELIABILITY & MAINTAINABILITY OF VEHICLE SUBSYSTEMS
SOURCES OF SCHEDULING DELAYS (TO OCT. 10, 1961)
t-------=-....... APUAND FUEL SYSTEM
...... _----' ENGINE ~ __ ... PROPULSION SYSTEM LESS ENGINE
...... _ ... WEATHER
1-----' HEAT AND VENT
o
MISCEllANEOUS
HYDRAULIC
INERTIAL
RADAR AND RADIO
FLIGHT CONTROLS
10 . 20
I
30 40
PERCENT OF TOTAL DELAY TIME
? Space Division ~ ~ North Amencan RocI~weli
50
SOURCES OF SCHEDULING DELAYS SINCE XLR99 INSTALLATION (13 FLIGHTS)
(TO OCT. 13, 1961)
1--__________ ..... ENGINE
...... __ ... PROPULSION SYSTEM LESS ENGINE
~_.-....I MISCELLANEOUS
...... _ ... APU AND FUEL SYSTEM
~--' INERTIAL
o
ELECTRICAL
HEAT AND VENT
TELEMETERING
RADAR AND RADIO
HYDRAULIC
FLIGHT CONTROLS
10 20 30 40 PERCENT OF TOTAL DELAY TIME
50
82PD114326
? Space Division ~ ~ NorthAmencanRockwell
HYPERSONIC RESEARCH VEHICLE OR FLYING FACILITY SYSTEM
CRITICAL ENVIRONMENT
APPLICABLE SYSTEMS
82PDl14.327
SIGNIFICANT DESIGN CRITERIA FROM INITIAL H.R.A. REVIEW
• BASEPOI NT PERFORMANCE REQU'I REMENT AT M6 FOR 10 MI N & TRADE UP FOR MS, M10CAPABI LlTI ES
• PROVI DE FUELS TANKAGE VOLUME FOR J P FUELS, METHANE & HYDROGEN
• ACCOMMODATE JP RAMJETS, METHANE & LH2 ERJ & SERJ ENGINES
• UTILIZE RL-IO ROCKET ENGINES AS PRIMARY PROPULSION & TRADE-OF'F FOR PERFORMANCE & CAPABILITIES OF LR-91 STORABLE ROCKET ENGINE
• INCORPORATE CAPABILITY TO ACCEPT SCRAMJET MODULES DURING THE FLIGHT TEST PHASE .
• EVALUATE COST-EFFECTIVENESS OF GROUND TAKE-OFF & LANDING (WHEELS) VS AIR-LAUNCHED & SKIS FOR LANDING
~ Space Division ~ ~ North American Rockwell
82PDl14328
SIGNIFICANT DESIGN CRITERIA FROM INITIAL H. R. A. REVIEW (CONT)
• PROVI DE FOR VARIOUS TYPES OF STRUCTURE FOR FUSELAGE, WING & EMPENNAGE COMPONENTS
• CONSIDER UPPER FUSELAGE MODIFICATION CAPABILITY FOR LAUNCHING SECOND STAGE VEHICLE EXPERIMENTS
• DESIGN H.R.A. NO.IS 1 & 2 FOR HIGH-CONFIDENCE - LEVEL HOT STRUCTURES OF TITANIUM, INCONEL-718, RENEI . 41, HAYNES-25, TD-NiCr, ETC., AS REQUI RED, & WITH GAS TURBINES, ERJ, SERJ ENGINES, AS SELECTED, & WITH APPROPRIATE FUELS & WITH OUTER STRUCTURE REMOVABILITY CONSIDERATIONS
• DESIGN H.R.A. NO.3 FOR ROCKET/SCRAMJET PROPULSION SYSTEMS WITH ACTIVELY COOLED STRUCTURE DECOUPLED FROM THE TANKAGE - INSULATION FROM A LOAD-CARRYING FEATURE . !.
? Space Division Po ~ North American Rockwell
82PD11432~
'.'",
H.R.A. NO. 1 • HOT STRUCTURE • SERJ PROPULSION • JP FUELS .METHANE FUEL
H.R.A. NO. 2 • HOT STRUCTURE • LH2 FUEL • RL-10 PROPULSION
H. R.A. NO.3' • ACT COOLED STRUCTURE' • LH2 • RL-10 PROPULSION .SCRAMJET PROPULSION
? Space Division ~ ~ North American Rockwell
FLIGHT TEST SCHEDULE PHASING
I . 2 t----....
" M = 2.5 M = 5.0 M = 5.0
I M = 5.0--6.0 ] GROUND TAKE-OFF
I I I M =6.0
• • M=2.5 M = 5.0 M =6.0
AIR LAUNCHED
I: I M = 8.0 I I~._. ~.~~ __ ~ ________ ~_ RL-lO M= 5.0 M = 6.0
I----- RL-10:- SCRAMJET • EXTERNAL TANKS • REUSABLE EXTERNAL
INSULATION
82PD114331
..
HYPERSONIC RESEARCH AIRPLANE PROGRAM PHASING
. 72 73 74 75 76 77 78 79 . I 80 81 I
M = 6.0 TECHNOLOGIES
IPHASE B
DESIGN & FAB NO.1 & 2
C/O
FLIGHT EVALUATIONS I
I M = 10.0 TECHNOLOGIES I DESIGN & FAB NO.3
FLIGHT I C/O
• SCRAMJET PROPULSION • ACTIVELY COOLED STRUCTURE • REUSABLE I NSU LA TIO N
? Space Division ~ ~ North Amencan Rockwell 82PDl14332
S I GNI FI CANT TECHNOLOGIES
M6.0 TECHNOLOG IES ,
I
• PRELIMINARY DESIGN FOR M4.5 - MIO CONFIGURATION
• STRUCTURAL DES IGNS FOR M = 6.0
• INLET - PROPULSION SYSTEM - FUEL INSTALLATIONS
• ALTERNATE PROPELLANT TANKS
• M4.5 - M6.0 ACCOMMODATIONS FOR RADARS, SENSORS ANTENNA, II H I DE ", ElECTRON I CS, FI RE CONTROL, ETC.
• WIND TUNNEL TESTING
• SUB SYSTEMS DES I GNS
MIO.O TECHNOLOGIES
• STRUCTURAL DESIGN INCLUDING ACTIVELY COOLED STRUCTURE
o REUSABLE SURFACE INSULAT~ ON
o PROPELLANT DISTRIBUTIONS SYSTEM: SCRAMJET STRUCTURE ROCKET ENG' NES
? Space Division ~ ~ North American Rockwell
82PD114333
,.'
SYSTEMS ENGINEERING ANALYSIS PROGRAM
CY 1972
INTEGRATED DESIGN I REUMTS & TRADES I. CONCEPTUAL
PROPULSION
PROPELLANT TANKAGE
REUMTS & TRADES I· CONCEPTUAL
• GAS TURBINE • RAMJETS • SCRAMJETS • ROCKET
I .REUMTS & TRADES I CONCEPTUAL
• J.P. FUEL • METHANE
• L02 .• LH2
• AUXI L1ARY (H202, He)
• SIMPLE CYLINDERS • INTERSECTING CYLINDERS • SIMPLE CONES • INTERSECTING CONES
• ALUMINUM • TITANIUM • 1NSULATION
1"" Space DiVision . ~ ~ North Amencan Rockwell
PRELIMINARY
I PRELIMINARY
PRELIMINARY
1976
82PDl14334
\ .
SYSTEMS ENG I NEER I NG ANAL YS I S PROGRAM (CONT)
PROPELLENT MANAGEMENT
CY 1972
REOMTS & TRADES I CONCEPTUAL
• C.G. CONTROL
PRELIMINARY
• DISTRIBUTION SYSTEM (RL-l0, SCRAMJET, STRUCTURE, DYNAMICS) • PURGE SYSTEMS
STRUCTURES I REQMTS & TRADES CONCEPTUAL PRELIMINARY
• PRIMARY • INSULATION • OUTER HEAT SHIELDS .. REMOVABILITY (FIELD BREAKS, ACCESS DOORS) • R.E.I. ADD-ON FEATURES • ACTIVELY COOLED STRUCTURE • MODIFICATION FEATURES
LANDING GEARS I REOMTS& TRADES I CONCEPTUAL
.WHEELS
• SKIS • GROUND TAKE-OFF - AIR LAUNCH
? Space Division ~ ~ North AmerICan Rockwell
PRELIMINARY I
1976
82PD114335
\ .
SYSTEMS ENGINEERING ANALYSIS PROGRAM (CONT)
CY 1972 1976
SUBSYSTEMS [REQMTS & TRADES I CONCEPTUAL PRELIMINARY
• POWER, ELECTRICAL, HYDRAULIC • ENVIRONMENTAL CONTROL SYSTEM
• • FLIGHT CONTROL SYSTEMS - AERODYNAMIC & ELECTRONIC • GUIDANCE SYSTEM -AIRBORNE - GROUND • CONTROLS & DISPLAYS • AVIONICS • INSTRUMENTATION • TELEMETRY • PAYLOADS ACCOMMODATIONS • PILOT(S) ACCOMMODATIONS • "OFF-THE-SHELF"
OPERATIONS [REQMTS & TRADES I OONCEPTUAL PRELIMINARY I • BASING, ONE VS TWO • RADARS TRACKING • GROUND SERVICE EQUIPMENT • AIRLAUNCH - GROUND TAKE-OFF • WEATHER IMPACTS • CHASE, RESCUE
• TURNAROUND
'?' Space Division ~ ~ NorthAmencanAocl~well 82PDl ]4336
!Il-------L--____ ~ __________ _=< .. --~---------
, .
SYSTEMS ENGINEER I NG ANALYS I S PROGRAM {CONT)
CY 1972 1976
WIND TUNNEL TESTS I REQMTS & TRADES I CONCEPTUAL PRELIMINARY
• CONFIGURATIONS } • WING GEOMETRY FORCE & MOMENT, DRAG • PROPULSION EFFECTS • AERODYNAMIC I-!EATING
SCHEDULE/COSTS REOMTS & TRADES I CONCEPTUAL PRELIMINARY I • VEHICLE DESIGN • FACILITIES • OPERATIONS • PHASING
? Space Division ~ ~ North Amencan Rockwell 82PDl14337
\ .
SUPPLEMENTARY INFORMATION
? Space Division ~ ~ NorthAmencan Rockwell 82PDl14338
, .. •
4-5
. CnfJ (PER DEG)
-0.001
I ·0.002 ,
CORRELATION OF PILOT RATINGS WITH Cn{3-C2(3 & ASSOCIATED RESPONSE MODES
176 A UNAUGMENTED UNSTABLE MACH NO.=14 a=34.S DEG SPIRAL MODE BODY AXES
CHR 5-6
BASELINE ~.
7-8
UNCOUPLED ROLL & SPIRAL MODES -INCREASING ROLL DAMPING ·DECREASING SPIRAL MODE DAMPING
~
STABLE COUPLED ROLL/SPIRAL MODE
9·10
• APPARENT CORRELATION WITH LATERAL·DIRECTIONAL RESPONSE MODES
•. Cnf3 PRIME DRIVER
"'·C -D 0
FOUR REAL nfJ DYN ROOTS .
• 0.0050---.-0 ..... 0-00-5--.0-. 0~0-1 0--.0-....... 00-1-5 -.-0 ..... 0-02-0-.-0 ...... 0"-025 Clp (PER DE.G)
? Space Division ~ ~ NorthAmencan Rockwell 82PDl14339
'.. . •
REPRESENTATIVE HYPERSONIC SYSTEM
158 FT
~ Space Division ~ ~ NorthAmencanRockwell 82PD 114340
. ') .
BENEFITS OF HYPERSONIC RESEARCH AI RPLANES
.• PROVI DE THE NECESSARY TECHNICAL & ECONOMIC I NFORMATION, MOVING FROM STUDIES & ANALYSES TO APPROPRIATE SUB-SCALE FLIGHT HARDWARE EVALUATIONS SUCH THAT THE HYPERSONIC PROGRAMS OF THE FUTURE WILL BE ON AN APPROPRIATE BASI S FOR SUCCESS WHEN INITIATED
• NEXT GENERATION AIR-BREATHING LAUNCH SYSTEMS
• HIGH SUPERSONIC & HYPERSONIC TRANSPORTS
- • HIGH SUPERSONIC & HYPERSONIC MILITARY SYSTEMS
• THE H. R. A. I S WI LL AD DRES S THEPOTENTl AL OF CONTI NU I NG TO REDUCE· THE COSTS OF PUTTING PAYLOADS INTO EARTH ORBIT; EVALUATING VARIOUS FUELS & THEIR COMPARATIVE ECONOMIES; & SUPERSONIC COMBUSTION RAMJETS & ITS COMPARATIVE PERFORMANCE, WEIGHTS & ECONOMIES
? Space Division ~ ~ NorthArnencan Rockwell 82PDl14341
., . •
. BENEFITS OF HYPERSONIC RESEARCH AI RPLANES (CONT)
• THE H.R.A.IS WILL ADDRESS THE SIGNIFICANT INDIVIDUAL TECHNICAL ELEMENTS & THE INTEGRATION OF THESE ELEMENTS OF THE HYPERSONIC TRANSPORT SYSTEMS OF THE FUTURE FOR THE PURPOSE OF RETAI NI NG AND lOR I MPROVI NG THE BALANCE OF TRADE I N THE YEAR 2000 +
• THE H. R. A.IS WILL ADDRESS THE REQUIREMENTS OF EVALUATING MILITARY TACTICS & POTENTIAL VEHICLE OPERATIONAL SUBSYSTEMS PRIOR TO COMMITMENT OF A FINAL SYSTEM
? Space Division ~ ~ North Arnf!rlc(ln Rockwell 82PD114342
.. . •
SINGLE - TURBOJET/TURBOFAN
-TURBOJET & PRE·COOLER
- RAMJET
-SCRAMJET
- ROCKET
COMPOSITE -SUPERSONIC TURBOFAN
- EJECTORAMJET
-SERJ
-TURBORAMJET/TURBOFAN
FUELS
- HYDROCARBONS
- ENDOTHERMIC
-CRYOGENIC
-METHANE
-HVDRDGEN
o
? Space Division ~ ~ North Amencan Rockwell
PROPULSION CYCLE/FUEL CANDIDATES
J
J
I I I I
I
J
I
J
I
t'///////////1 . . VL///LL////////A
I I I I
I J I I I I I I 1 2 3 4 5 6 7 8
82PDl14313
• .0; ••
FUEL
J. P. (REG)
METHANE
HYDROGEN
J. P.
METHANE
HYDROGEN
HEAT OF COMBUSTION (BTU '5 'LB)
18,600
21,500
51,750
10,350
10, 750
5, 175(1725)
'.t' Space Division North American Rockwell
PROPERT I ES OF FUELS
HEAT SINK (BTU'S'LB)
165
1,100
4,900
91.5
550
490 (163)
DENSITY (LB 'FT3)
50
26.5
4.3
HEAT SINK LIMIT TEMP
(DEG F)
375
1,000
1,000
AT 1. 8¢ ILB
AT 2¢ ILB
COST (¢ I LB)
1.8
2.0
10 - 30
AT 1& ILB (AT 30¢ ILB)
82PDl14314