Post on 28-Feb-2023
Course Ae107
Case Studies in Engineering
The SR-71 Blackbird
Presented by Lockheed Advanced Development Company
and The Graduate Aeronautical Laboratories
California Institute of Technology
Program Directors: Mr. David Urie - Lockheed Corporation Prof. Hans Hornung - GALCIT
Teaching Assistant: Patrick Gennain
Spring Term, Academic Year 1990-1991
t
Lecture
1
2
3
4
5
6
7
8
9
10
11
12
Lecture Topics for Ae107b Case Studies in Engineering
Spring 1991 "The Lockheed SR-71 Blackbird"
Date Topic
1 April Introduction
3 April Program Management
8 & 10 April Design
15 & 17 April Structures & Material
22 April Aerodynamics
24 April Flight Controls
29 April & 1 May Thermodynamics & Environmental Systems
6May Hydraulics & Fuel Systems
8May Propulsion Integration (Inlets and Exits)
13 & 15 May Propulsion system (J-58 Engine)
20 &22 May Fright Test
31 May Student Presentations
Speaker
David Urie
Ben Rich
Dick DeGrey
John Altizer
Jerry Meyer
Bob Loschk:e
Pete Law
Dick DeGrey
Tom Anderson
Arnold Gunderson (from Pratt & Whitney)
Dick Abrams
Lecture
1
2
3
4
5
6
7
8
9
10
11
12
Lecture Topics for Ae107b Case Studies in Engineering
Spring 1991 "The Lockheed SR-71 Blackbird"
Date Topic
1 April Introduction
3 April Program Management
8 & 10 April Design
15 & 17 April Structures & Material
22 April Aerodynamics
24 April Flight Controls
29 April & 1 May Thermodynamics & Environmental Systems
6May Hydraulics & Fuel Systems
8May Propulsion Integration (Inlets and Exits)
13 & 15 May Propulsion system (J-58 Engine)
20 &22 May Flight Test
31 May Student Presentations
Speaker
David Urie
Ben Rich
DickDeGrey
John Altizer
Jerry Meyer
Bob Loschke
Pete Law
DickDeGrey
Tom Anderson
Arnold Gunderson (from Pratt & Whitney)
Dick Abrams
. LOCKHEED SR- 71 "BLACKBIRD" CALTECH CASE STUDY IN ENGINEERING
LECTURE 2 - LECTURE 3
• DESIGN
PRESENTED BY: RICHARD DEGREY SR-71 PROGRAM MANAGER (RETIRED)
CONGRATULATIONS!
FOR CHOOSING ENGINEERING AS YOUR PROFESSION
• OUR COUNTRY NEEDS YOU!
• OUR INDUSTRY NEEDS YOUI
• FORTUNATELY THE WIZ OF ID AND THE LITTLE KING DO NOT REFLECT TODAY'S ATTITUDE
ENGINEERING IS AN EVOLUTIONARY PROCESS
THE "BLACKBIRD" DESIGN WAS AN EVOLUTION THAT TOOK
PLACE IN A VERY SHORT PERIOD OF TIME BUT HAD SUCH
ADVANCED TECHNOLOGY THAT IT HAS NOT . BEEN SURPASSED
25 YEARS LATER!
111 PHELIMINAHY
HECIUlflEIV1ENTS I DESUiN DESIGN
I\ND BUll.D MAKE IT
WUIIK
• WHY IS IT NEEDED? IS THEHE A THE DIG PICTURE WHERE HUMILITY SOLUTION-! REDUCED TO BITS ·· 1s DORN AND INOVATION
11 WHAT DOES IT AND RECONSTITUTED RULES ,HAVETO DO?
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FUNCTIONAL SYSTEM TEST ANO MOCKUPS
PHOPULSION SYSTEM DEVELOPMENT
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DESIGN AND BUILD
BEN RICH l•hlAS GIVEN YOU A VERY GOOD ACCOUNT OF Tt-lE "SKUNK WORKS" SYSTEM AND THE HISTORY AND BACKGROUND OF Tt-lE "BLACKBIRD".
DESIGN G~NIUS, KELLY JOHNSON, AND THE ENGINEERS IN ADP PIONEERED IN ALMOST EVERY AREA TO CREATE THESE MACHINES. KELLY ONCE SAID,
"I CAN TRULY SAY EVERYTHING ON Tl-IE AIRCRAFT, FROM RIVETS AND FLUIDS, INCLUDING MATERIALS AND POWER PLANTS 1-IAD TO BE INVENTED FROM SCRATCH".
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EVOLUTION (RC VOLUTION) OF AIRFRAME DESIGN
LOCKHEED FIRSTS:
• VEGA - LATE 20'S - FIRST COMPOSITE STRUCTURE -MANY SPEED RECORDS
• P:-38 - LATE 30'S - FIRST 400 MPH TWO-ENGINE FIGHTER
• P-80 - MID 40'S - FIRST U.S. JET FIGHTER -WORLD'S SPEED RECORD
• XF-90 - LATE 40'S - FIRST JET TO EXCEED MACH 1
• X-7 - MID 50'S - FIRST RAM JET - MACH 4 -BOMARC TEST VEHICLE
• F- 104 - LATE 50'S - FIRST MACH 2 FIGHTER - WORLD SPEED RECORD
• U-2 - LATE 50'S - FIRST HIGH ALTITUDE RECCE
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DESIGN REQUIRE1vlENTS (BRIEF)
II LONG RANGE
• HIGH SPEED
ID LOW CROSS-SECTION
CD HIGH ALTITUDE .
- REQUIRED: LIGHTWEIGHT STRUCTURE - LOW TRIM DRAG
- REQUIRED: GOOD LIFT OVER DRAG RATIO - HI THRUST
- REQUIRED: SHAPING AND EDGE TREATMENT
- REQUIRED: PRESSURE SUIT -FUEL TANK PRESSURE
HIGH TEMPEBATURE - REQUIRED: FUEL HEAT SINK -TITANIUM STRUCTURE
• HIGH RELIABILITY - REQUIRED: REDUNDANT SYSTEMS -NUMEROUS TEST PROGRAMS
---- ----- ---··. ····- ·------·-···-- ··-···- -····--·-··--··· ········--·· --·- --·-· •....... ···- -·-· ·-··--· ·-·· ·-·-•· - - ---- ·---··· ------· - .. ·----- . -- - ...... -·-·· ...... __ .. •·- ... -···- ··-.. --·. ----·- ,. - . ·-· ·- ... ···-
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NFIGURATION SELECTED SIZE COMPARISON
- SIMILAR TO B-58 - SMALLER THAN 8- 70
IN ORDER TO MEET THE REQUIRED PERFORMANCE IN SPEED, ALTITUDE, AND RANGE IT WAS DECIDED:
• A THIN DELTA WING. CONFIGURATION WITH LOW WING LOADING WOULD BE REQUIRED TO REDUCE TRIM DRAG AND INCREASE THE DIRECTIONAL STABILITY.
• CHINES WERE ADDED TO THE LONG FOREBODY OF THE AIRCRAFT.
c. --THE ENGINES WERE LOCATED APPROXIMATELY HALF WAY OUT ON THE WING, AND
°' THE TWIN RUDDERS WERE MOUNTED ON TOP OF THE ENGINE NACELLES.
. ···-· - -----· ------·- -·••····-···--·--·-·· ---------·--· ______ ,, ___________ _
L,QMPARISON TO EXl0 rlNG TECHNOLOGY
• THIS NEW AIRCRAFT HAD TO BE CAPABLE OF:
... A SUSTAINED CRUISING SPEED OF 60% FASTER THAN THE MAXIMUM DASH SPEED OF OUR .FASTEST AIRPLANES,
- A CRUISING ALTITUDE 70% HIGHER THAN OUR HIGHEST SUSTAINED OPERATING ALTITUDE, AND
... APPROXIMATELY 500% GREATER RANGE THAN THE OPERATING RANGE OF OUR BEST INTERCEPTORS AND FIGHTERS. ·
... IN ADDITION, IT HAD TO OPERATE IN THE UNKNOWN AREAS OF HIGH STAGNATION TEMPERATURES AND UNKNOWN AERO- DYNAMIC AND THERMODYNAMIC REGIME.
• IT WOULD BE THE FIRST AIRCRAFT TO UTILIZE A MIXED COMPRESSION AIR INDUCTION SYSTEM.
IJJNCIL,ASSUU:D _s_~NIOR CROWN PROGRAM
GENERAL ARRANGEMENT'
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TSHE "BLACKBIRD" FAMILY
• A-12 ·- LATE 50'S - FIRST TITANIUM
• YF-12A - EARLY 60'S - FIRST MACH 3 INTERCEPTOR MANY SPEED, AL TIT UDE RECORDS
'
• SR-71A - MID 60'8 - FIRST MACH 3+ RECCE -WORLD SPEED, ALTITUDE AND DISTANCE RECORD
• SR- 71B - MID 60'8 - TRAINER
• RECor~10s 1-IELD BY TI-IESE AIRCRAFl-
SR-71
l
ECOR -PEED RUNS NEW YORK-LONPON--• L WPON-LOS ANt;ELES •
NEW YORK 10 LONDON
TIMii ................................ 1:55:32 DISJANCIE ................... 3470 MILES (3014 NM} AVERAGE SPEED ...... 1817 MPH 11578 l<NOlSJ
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GENERAL ARRANGEMENT AND CI-IARACTERISTICS
ALL CHARACTERISTICS SIMILAR TO SR-71 A EXCEPT:
r1 CREW - (2) PILOT AND FIRE CON.TROL OFFICER
r1 PURPOSE - CONUS INTERCEPTOR AND NASA RESEARCH VEHICLE .
PAYLOAD - HUGHES ASG 18 RADAR AND THREE GAR 9 AIR-TO-AIR MISSILES
NOTE: CHINE STOPS AT START OF RADOME. ALSO, 2 SMALL VENTRAL FINS UNDER NACELLE AND ONE LARGE FIN U FUSELAGE REQUIRED TO RESTORE LATERAL STABILITY D ROUND CROSS- SECTION RADOME.
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GENERAL ARR~,1\JGEMENT AND CHARACTERISTICS
• SR-71:
s·PEED CREW PURPOSE ALTITUDE PAYLOAD
COVERAGE
RANGE ENGINES
- MACH 3+, 2100+ MPH; 3299+ F.P.S. - (2) PILOT AND RECCE SYSTEMS OFFICER - STRATEGIC RECONNAISSANCE - ABOVE 80,000 FT. - ADVANCED SENSORS, RADAR, CAMERAS,
ELECTRONIC EQUIPMENT CAN SURVEY OVER 100,000 SQUARE MILES OF EARTH'S SURFACE IN ONE HOUR 3000 MILES - GLOBAL WITH REFUELING
- TWO J-58 TURBO RAM JETS WITH A.8. 32, 000+ LB. THRUST EACH
WING AREA - 1800 SQ. FT. WEIGHT - 135,000 LB. (APPROXIMATELY)
==---======-··-=·-=·-=•·· ==-
FUSELAGE CHINE
THE FORWARD PORTION OF THE FUSELAGE IS A BLENDED BODY. THE WING PORTION IS COMMONLY REFERRED TO AS THE CHINE.
• IT IS SUCH AN EFFECTIVE LIFTING SURFACE THAT AT CRUISE SPEED, THE AERODYNAMIC LIFT CUTS THE FORWARD FUSELAGE BENDING MOMENT IN HALF
' AND REDUCES TRIM DRAG SIGNIFICANTLY.
• ALSO REDUCES RADAR CROSS SECTION
., INCREASE OF LIFT DUE TO CHINE (VF- 12A HAS NO CHINE ON RADOME)
• PLAIN- VIEW OF MODEL IN WATER FLOW TANI< NOTE FORMATION OF VORTEX OVER UPPER SURFACE
STRULTURE
• OVER 93% OF THE AIRCRAFT STUCTURE AND SKIN SURFACE ARE TITANIUM.
• THE EJECTOR FLAPS ARE MADE OF HASTELLOY X.
• THE EJECTOR RING IS MADE OF RENE 41.
• ALL AIR CONDITIONING LINES ARE ALUMINUM
• ALL HYDRAULIC LINES ARE STAINLESS STEEL.
• THE WING HAS PRE-FORMED LONGITUDINAL CORRUGATIONS TO ENSURE THE WING EXPANSION IN THE STREAMWISE DIRECTION. THE OUTBOARD PORTION OF THE WING'S LEADING EDGE HAS CONICAL CAMBER TO MOVE THE LOAD INBOARD AND AFT.
THE AIRCRAFT IS ESSENTIALLY A FLYING FUEL TANI< CARRYING OVER 40 TONS OF FUEL. FUEL IS CARRIED PRINCIPALLY IN FIVE FUSELAGE TANKS AND THE WING TANKS. THE WING TANKS ARE USED IN CLIMB; THAT IS, FIRST, DUE TO THE HIGH RATIO OF SURFACE TO VOLUME FOR THERMODYNAMIC REASONS. FUEL SEQUENCING IS AUTOMATIC AND PROVIDES C.G. CONTROL
- INCIDENTALLY, THE FUSELAGE INCREASES IN LENGTH BY ABOUT 10 INCHES IN CRUISE.
======- ········•·•••·· .. -··-·--·--··-·--·······-··-
STRUCTURE
IN STUDYING THE 8-70 HONEYCOMB APPROACH, IT WAS EVIDENT THAT THE "SKUNK WORKS" WAS NOT SMART ENOUGH TO MAKE USE OF STEEL HONEYCOMB WITH ITS VERY INVOLVED AND PRECISE TOOLING AND DIFFICULTIES IN QUALITY CONTROL. IT WAS DECIDED TO USE THE UNCONVENTIONAL ALLOYS OF TITANIUM IN A CONSTRUCTION WHICH WAS OPEN FOR INSPECTION AND CONSTRUCTION.
- NOTE HOW THIS CONCEPT PROVIDED ACCESS IN THE CONSTRUC.TION PHASE OF THE FINAL ASSEMBLY LINE.
- UPPER PANEL REMOVED FROM WING
- OUTER WING AND NACELLE OPEN FOR ENGINE INSTALLATION (REDUCES DIAMETER)
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TI-IERMAI_ E~ ~ ✓IRONMENT
• THE AIRCRAFT RECEIVES ITS HEAT DUE TO AERODYNAMIC OR CONVECTIVE HEATING.
- THIS RESULTS FROM THE DECELERATION OF AIR IN THE BOUNDARY LAYER; THEREFORE, WHENEVER THE VELOCITY IS ZERO, SUCH AS THE Wl"NG LEADING
. EDGE, THE TEMPERATURE IS AT STAGNATION, THAT IS, APPliOXIMATELY 800 DEGREES FAHRENHEIT. AS THE VELOCITY INCREASES ALONG THE SURFACES, THE TEMPERATURE REDUCES.
• THE AIRCRAFT GETS ADDITIONAL HEAT FROM THE SUN OR SOLAR HEATING, BUT LOSES HEAT BY RADIATION.
- THIS IS WHY AIRCRAFT THAT FLY FAST AND HIGH HAVE THEIR SURFACES PAINTED BLACK.
- THE EMISSIVITY OF TITANIUM IS ABOUT .38 WHEREAS BLACK PAINT REDUCES THE WING TEMPERATURES ABOUT 35 DEGREES FAHRENHEIT.
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