I ...."' "'0 0 0 0 <( Q.,. N "ef.ilockheed Advanced Deve/opl116nl Company ADP ORGANIZATION .. CHIEF SKUNK MANUFACTURING QUALITY ASSURANCE ENGINEERING PROGRAMS I j ADMINISTRATION FLIGHT TEST FLYING OPERATIONS ANALYSIS tTEST PILOTS DATA ACQUISTION TRANSPORTATION DATA PROCESSING FLIGHT TEST ENGINEERS AVIONICS TEST FLIGHT MANUALS 24 DA 0002 05 II 91 nu ~ L, ·,., ,.,.• act:s , ta· ' t . 11,.,. t ffl snJtitrt ·a,·.\·c·:' '. •,inrW&f ·~ ....~•~-=~ ...:-1 . ·· ,,"•1:•-t,~-~~-~•lae:.t~«91:&i1t't ,,, ,H· f:tiJr ·1 d(i:?f-f- ., :P· ··•·· .. •!i' - 24 DA 0002 OS ..,\ i,&i1~1Wi!iO?_r·,:.:.,,.,:: .~:AA!\.. "'· .+ , . "'=iJ', Jed A... _,Ced Development Company FLIGHT TESTING - USAF PROGRAMS , IPHASE TESTING - CIRCA 19511 I CATEGORY TESTING - CIRCA 1958 I I JTF/CTF - CIRCA 1951 AIRWORTHINESS SUBSYSTEM DEVELOPMENT TEST - AFR 80-14 ESTABLISHED - CONTRACTORTEST PILOTS AND EVALUATION DT&E/OT&E TESTING AIRWORTHINESS - CONTRACTORTEST PILOTS II CONTRACTOR COMPLIANCE OPERATING - USAF TEST PILOTS - USAF TEST PILOTS CHARACTERISTICS - USING COMMAND PILOTS (PRIMARILYRESPONSIBLE Ill DESIGN REFINEMENT - SUBSYSTEMPERFORMANCE FOR OT&E) - CONTRACTORTEST PILOTS - CONTRACTORTEST PILOTS (USAF CONTROL IN 1963) IV PERFORMANCE & STABILITY - USAF TEST PILOTS II SYSTEM DEVELOPMENT TEST AND - PRODUCTIONAIRCRAFT EVALUATION SPEC COMPLIANCE V ALL WEATHER - WEATHER - USAF TEST PILOTS - CONFIGURATIONREFINEMENT - PRODUCTION AIRCRAFT - MAINTENANCE VI FUNCTIONAL DEVELOPMENT - LOGISTICS USAF OPERATIONALPILOTS - CONTRACTORAND USAF TEST PILOTS - SOME USER COMMAND PILOTS/PER- - USAF TEST PILOTS SONNEL - USAF MAINTENANCE PER- - INCLUDES MISSION EQUIPMENT SONNEL 111 SYSTEM OPERATIONAL TEST AND VII OPERATIONAL SUITABILITY EVALUATION & - USER COMMAND VIII - USING COMMAND . -¥il'ttD,;.71/ ·1 i,l': ,tfl·., ( 24 DA 0003 05 17 · 91 IIG r:: ( 'c..(., .'- __, I I I !i!ii!ii .. ~Lockheed Advanced Development Company BLACKBIRD FLIGHT TEST PROGRAM 26 APR A-12 7 AUG "RECORDS" II 1 MAY 1 YF-12A <1 •··•,···1,,muSZ:.1n1.. ,.. '•·•···,· ..< ..,.,.~;n/ ... s 22 DEC SR-71 i/:!:11=;1;;;::::::::/:;:1:,;:;:1::i:i:::::::l:::::9:~1:~:~:9,~Y::.,!::;:::::::;:::::::?-:'·,:,.,:::_:::.:-:):,.,:=.,_, 1 JULY 1 ,:!ii!Ji1iiiiill/:lil;liii)il!;i;i/il1i:J/lill//l//'i~i~:.g:ijx,.,,1.,:,,/i:/::!iiiiii:i;:::i::::::::':,=,:=-, 1: V( ___,.___r 24-0A 0004 05 17 91 1111 ..... bi:n .... • r: :r ""=U'Loch Advan.._ J.Jevelopmen/ Company SA- 7 I FLIGHT TEST'S EARLY INVOLVEMENT l·N PROGRAM • SYSTEM/SUBSYSTEM DEVELOPMENT - FUEL SYSTEM MOCK-UP - FLIGHT CONTROLS/HYDRAULICS - IRON BIRD - FLIGHT SIMULATOR (RYE) - ENGINE DEVELOPMENT • DRAFT FLIGHT MANUAL AND CHECKLISTS • TEST PLANNING - PLANS - INSTRUMENTATION REQUIREMENTS - EXTEND ANALYSIS CHARTS > 2.0 MACH - ALTITUDE/GAS - ALTITUDE/EAS - -y ~ 1.4 24-DA 0005 05 17 91 IIG -£:, '-"! u1 ~Lockheed Advanced Development Company SR-71 FLIGHT CREW SELECTION & TESTING • FLYING BACKGROUND • TEST EXPERIENCE • PHYSICAL REQUIREMENTS • TRAINING "­-.. U) 24 OA nnn,:;: nc: "In nt ,.,.. Ci'. ~ ?H ................. --- •.c•_.,.___.,. _ __........,, ........~~· ............~ .... --------- =f.rL ed A <1DeVe/o/Jl118nl Company SR-71 FLYING. OPERATIONS • GLOBAL FLIGHT TEST PLANNING • ATC COMMUNICATIONS • TANKER RENDEZVOUS • INLET SYSTEM DEMANDS • CHASE 24 DA 0007 05 17 91 IIC, . -........... (11 .,.__...-,' I - -...,.,.:.»c.,=,-.,_- __.,,,,. ;;,;.,---·, .•.:·._ -:-:· "" '.-.:::::::.:::,·::.."_._,-.:c.-c,·.,,.,,J::.:r-"'-··'-"'-=~•-=-•-,.,~~"f"""'."':'"--:: ·:. -----~- ____m: .......... - =iJ'Lockheed Actvanced Development Company SR-71 FLIGHT TEST • TEST PHILOSOPHY - USE MILITARY SPECIFICATIONS AS GUIDES TEST DESIGN FLIGHT PROFILE FIRST - MAKE OFF DESIGN EXCURSIONS WHERE APPROPRIATE - CONFIRM MISSION READINESS I' Lrt ~ 24· DA 0008 OS IT 91 IIG ~ •----------...~-•--........--•~•,.~w._.·..•--·----...----- ~- ,7tJtXI Advanced Development Company CATEGORY I 24 DA 0009 05 II 91 IIG --S:, ~ -0 \ :!i,}Lockheed AdvanCed Development Company SR-71 CATEGORY I FLIGHT TEST VALIDATION ITEMS • PERFORMANCE • STABILITY AND CONTROL • STRUCTURAL INTEGRITY • SENSOR PLATFORM SUITABILITY ~ a 24 OA-00IO 05-17 91 IIG ,_,...... ~--·~-.,... ... -A. ...... ~---- ....... ---~- ··•. ..•• ....... ••.. ~ ···-~--- ,_1..;i•• ..~ .Jl-lL?_ ~• - .• • ., ,, . ,,r,j~r.}..... .:,_,;i:·•·. .. .. "'=CfLockheed Advanced Development Company SR-71 FLIGHT TEST ~ ·._:: \1Q&~/t::'.:. 22 DEC S/N 2001 1 1 9 64-17950 :111!ll;llillillilll!iliijf~E~~~R~0V8Xt~:.~~~ Ji·tM~iij~ili;A CATEGORY I S/N 2002 1 64-17951 ::i111:1i!ii!!ii//;i\::II}i\:fiii:=1::,i:~\1fs~-~-~itir~1~~-~~:P:_·:•·..:'::_. 25MAR 25JAN S/N 2003 1 64-17952 I!'.!!=:t:]l:i::;l!!;::,1:Ji~~~i:::!i:'.:i\i_.:'i::=. ------------------------------4JUNE S/N 2004 64-17953 CATEGORY II 10 FEB S/N 2005 64-17954 24 DA 0011•05·20·91 CU _[ 0--.. ----·-··---~--- -- -- - . ~Lockheed Advanced Deve/ofJ1116nfCompany SR-71 CATEGORY I FLIGHT TEST TEST SUMMARY • AIRCRAFT PERFORMANCE - AIRSPEED CALIBRATIONS - - SUBSONIC - - TRANSONIC - - 2.0 AND 2.8 MACH (SPOT CHECKS) - AIRSPEED RANGE - - 135 KEAS - MIN. - - 500 KEAS - MAX. - - 3+ MACH - MAX. - CLIMB PERFORMANCE - - CONSTANT EAS ACCELERATIONS - - SINGLE ENGINE - - DIPSY-OOODLE ,- -\-.., 24 OA 0012 OS 11 91 Ill. l, ______________ .. , .... ~~• •• , ,_.,.,._.,. • •• .,..,.._., I .... ,. ••.• ..,..~\-(~-f....,. ~ I 0•1•1 ~nrrtt' ;-.,.·• •.·..-,~1-·~1_.:......'.......::.....:.>...:· ~.L 'ed A, :<i DeVe/opmenl Company SA l CATEGORY I I-LIGHT TEST TEST SUMMARY , ,, (CONTINUED) • AIRCRAFT PERFORMANCE (CONT'D) - SUBSONIC CRUISE - - SPEED RANGE 0.7 TO 0.9 MACH - - ALTITUDE RANGE 20,000 TO 33,000 FEET - SUPERSONIC CRUISE (2.0 TO 3+ MACH) · • STABILITY AND .CONTROL - SAS ON/OFF - NOSE TILT CONFIG. • STRUCTURAL LOADS - 80% TO 2.6 MACH/450 KEAS - 2.8 G SYMMETRICAL - 2.2 G ROLLING PULLOUTS 24 -DA 0013 05 17 91 IIG f""" 0-· CJ ~Lockheed Advanced DeVelopmBnt Company SR-71 CATEGORY I FLIGHT TEST TEST SUMMARY (CONTINUED) • VEHICLE SYSTEMS - FUEL SYSTEM - AIRFRAME - AIR REFUELING - HYDRAULIC SYSTEM - ELECTRICAL SYSTEM - COMMUNICATIONS - FLIGHT CONTROLS - ENVIRONMENTAL CONTROL LANDING GEAR/DRAG CHUTE - INLET CONTROL SYSTEM - PROPULSION • SENSOR SYSTEM TESTING - NAVIGATION INTERFACE - RADAR - CAMERAS MAP PROJECTORS - INFRARED ,--. 6' - ELECTROMAGNETIC - 24 DA 0014 05 17 91 JIG -r '· • ~ • • ,... ..,.,., • .._ r ., •• 'l\'-;-1~ .... a ,n ...~lf'N""'-,l· • .. ,,,~H, ~/ ?ed ; ea Development Company SR-71 PROGRAM "UNSOLVED OPPORTUNITIES" , .. • TEMPERATURE RELATED ~ FUEL TANK SEALING - INLET SYSTEM STABILITY AND CONTROL/SCHEDULING - HYDRAULIC SYSTEM LEAKS - DATA ACQUISITION SENSORS • OTHER - E'NGINE FOREIGN (& FAMILIAR) OBJECT DAMAGE (FOD) - NACELLE EXHAUST NOZZLE MAINTENANCE 24 llA 0015 05 11 91 IIG r- :_" (J"", v-\ -·--··· - . __.: _:;_. - - ... ;!j;f Lockheed Advanced Development Company SR-71 FLIGHT TEST • DATA ACQUISITION CHALLENGES - TEMPERATURE - TRANSDUCER COOLING - - IN PLACE - - MOVE INTERNALLY - TEMPERATURE MEASUREMENTS - - REFERENCE JUNCTIONS - POSITION TRANSDUCERS - - USE VEHICLE HARDWARE - STRAIN GAGE INSTALLATION I'- ,/~••, -~\ !1 24· OA 0016 05 17 91 ll<i .•• :: :-.U11...;.·.~·...--...:.1'J :-: 1/liii&'ir '!!:~l'lt':lt"li'. • ~·•'"' ~LIJ __., 1eed Advanced Deve/op1116ntCompany .. CATEGO.RY II 24 DA 0011 05 II 91 llll ~ ~ ~ -········ ······--·····-·--····-. ·-·-·•-·- -- .. - -----·--··•·-···-. Wlockheed Advancecl Development Company SR-71 CATEGORY II FLIGHT TEST • PERFORMANCE - GROUND PROCEDURES - - STARTING - - TAXING - TAKEOFF - - GROSS WEIGHT EFFECTS - - LIFTOFF SPEED - CLIMB SUBSONIC o 250,400 AND 450 KEAS o MIN/MAX A/B o MILITARY POWER TRANSONIC o 0.9 MACH TO 450 KEAS o 28,000, 30,000 AND 32,000 FT. o DIPSV-DOODLE r- s\ 74 .nA nntA M 11 •• un ~ --- w. eed Aalfdl1Ced Development Company SR-71 CATEGORY II FLIGHT TEST " (CONTINUED) • PERFORMANCE (CONT'D) - SUPERSONIC CLIMB - - 400, 425 AND 450 KEAS - - CONSTANT MACH - - 2.0, 2.8, 3.0, 3 + - - REDUCED POWER. - SUPERSONIC CRUISE - - CONSTANT ALTITUDE/MACH (2.0, 2.4, 2.8, 3.0 & 3 +) - - AFT BY-PASS DOOR SCHEDULING EFFECTS - - RPM TRIM EFFECTS - - C.G. EFFECTS - DESCENTS - - NORMAL - - SINGLE ENGINE 24 DA 0019 OS 17-91 IIG i I ----._, "(f\ ....£:'I r ~Lockheed Aµvanced Deve/ofJIT1t1nlCompany SR-71 CATEGORY II FLIGHT TEST TEST SUMMARY (CONTINUED) • STABILITY AND CONTROL - LONGITUDINAL STABILITY - - STATIC - - DYNAMIC - - SPEED EFFECTS MANEUVERING STABILITY - LATERAL DIRECTIONAL STABILITY - HANDLING QUALITIES - - TAKEOFF - - CLIMB - - SUPERSONIC CRUISE -- DESCENT - - AERIAL REFUELING - - APPROACH AND LANDING --t=:. ~ 24 DA 0020 05 17 91 IIG E) Hiiiiffr:o rt et: ":f ··• •. ·•· ,t --------------·------.... ---·-·•···· ___ ...,_,,....,. ,.,._..,._.....,. __,at,, ~nnn1a::1nl" ·-·· ~ wed Auvanced Development Company Sh-~/1 CATEGORY II FLIGHT TEST TEST SUMMARY (CONTINUED) • SYSTEMS EVALUATIONS - OPERATIONS/MAINTENANCE VIEWPOINT - AIRFRAME - LANDING GEAR/DRAG CHUTE - HYDRAULICS FUEL SYSTEM - - OPERATION - - IN-FLIGHT REFUELING - ELECTRICAL SYSTEM - FLIGHT CONTROLS - ENVIRONMENTAL/CONTROL - COMMUNICATIONS/NAVIGATION - CREW SYSTEMS - SENSOR SYSTEMS 24 DA 0021 05 17 91 IIG --h, ..> 1 I'·" .,.,_.:_.,·.. .· ;r, ·. ,;· · ·"::\h/·-;·,~~•:\-~r:r/ ..~•:1.~.~:~~-:-;'""~~:-· •~;./(f;_, .:.-.·-...:.,:.•.: . ,,:. ..-t,•~.-~.:1i:·:.~~·-1·-:-: ;,:,•. ,:a·/ _.,-.'J~.·/t '.' •'•; · ·•i LOCKHEEDSR-71 BLACKBIRD ~ Crusing speed: Mach 3 Service ceiling: 85,000-plus ft. (25,900 m) Maximum speed: classified Normal range: classified Empty weight: classified Number produced by Lockheed: classified D For 24 years, top decision-makers, including the president of the United States, relied on photographic and other data gathered by SR-71 Blackbirdsduring supersonic