《航空器系统工程学》（英文版）SHUTTLE HISTORY

SHUTTLE HISTORY 1952 FULLY REUSABLE LAUNCH VEHICLE CONCEPT DISCUSSED 1962 FULLY REUSABLE VEHICLE SERIOUSLY CONSIDERED AIR FORCE STUDIED PROJECT DYNASOAR WHICH WAS CANCELLED N1969 1969 NASA ADOPTED THE IDEA OF A FULLY REUSABLE SPACE SHIP

SHUTTLE HISTORY • 1952 FULLY REUSABLE LAUNCH VEHICLE CONCEPT DISCUSSED • 1962 FULLY REUSABLE VEHICLE SERIOUSLY CONSIDERED • AIR FORCE STUDIED PROJECT DYNASOAR, WHICH WAS CANCELLED IN 1969 • 1969 NASA ADOPTED THE IDEA OF A FULLY REUSABLE SPACE SHIP 1

TOP LEVEL REQUIREMENTS FULLY REUSABLE 14 DAY TURN AROUND TO NEXT FLIGHT DEPLOY AND RETRIEVE PAYLOADS DESIGN, deVeloPment. TEST PHASE ESTIMATED TO BE 5.1B N 1971 DOLLARS ORIGINAL COST PER FLIGHT FOR 65.000 POUNDS WAS 10.5M PER FLIGHT IN 1971 FORA FLIGHT RATE OF 60 PER YEAR

TOP LEVEL REQUIREMENTS • FULLY REUSABLE • 14 DAY TURN AROUND TO NEXT FLIGHT • DEPLOY AND RETRIEVE PAYLOADS • DESIGN, DEVELOPMENT, & TEST PHASE ESTIMATED TO BE 5.1B IN 1971 DOLLARS • ORIGINAL COST PER FLIGHT FOR 65,000 POUNDS WAS 10.5M PER FLIGHT IN 1971 $ FOR A FLIGHT RATE OF 60 PER YEAR 2

SHUTTLE STUDIES PHASE“ A STUDIES WERE CONDUCTED TO DETERMINE BASIC REQUIREMENTS AND THEIR EFFECT ON DESIGN N 1969 PRINCIPAL ISSUES SIZE AND WEIGHT OF PAYLOAD CROSS RANGE OF THE ORBITER HEAT-RESISTANT STRUCTURE OR REUSABLE INSULATING MATERIAL

SHUTTLE STUDIES • PHASE “A” STUDIES WERE CONDUCTED TO DETERMINE BASIC REQUIREMENTS AND THEIR EFFECT ON DESIGN IN 1969 • PRINCIPAL ISSUES: – SIZE AND WEIGHT OF PAYLOAD – CROSS RANGE OF THE ORBITER – HEAT-RESISTANT STRUCTURE OR REUSABLE INSULATING MATERIAL 3

SHUTTLE STUDIES PRINCIPAL ISSUES HYPERGOLIC REACTION CONTROL SYSTEM OR LIQUID OXYGEN/HYDROGEN FLY-BY-WIRE FLIGHT CONTROL SYSTEM WIND TUNNEL TESTS TO DETERMINE WING SIZE AND CONFIGURATION AIR BREATHING ENGINES WERE CONSIDERED FOR FLY BACK, LATER WERE DETERMINED TO BE TOO HEAVY

SHUTTLE STUDIES • PRINCIPAL ISSUES: – HYPERGOLIC REACTION CONTROL SYSTEM OR LIQUID OXYGEN/HYDROGEN – FLY￾BY-WIRE FLIGHT CONTROL SYSTEM – WIND TUNNEL TESTS TO DETERMINE WING SIZE AND CONFIGURATION – AIR BREATHING ENGINES WERE CONSIDERED FOR FLY BACK; LATER WERE DETERMINED TO BE TOO HEAVY 4

SHUTTLE STUDIES PRINCIPAL ISSUES ENTRY TECHNIQUES LANDING SPEED APPROACH PATTERN

SHUTTLE STUDIES • PRINCIPAL ISSUES: – ENTRY TECHNIQUES – LANDING SPEED – APPROACH PATTERN 5

SHUTTLE STUDIES PHASE“B” STUDIES WERE PERFORMED|N MID 1970S TO DETERMINE A PRELIMINARY DESIGN RESULTS FULLY RECOVERABLE ORBITER DISPOSABLE FUEL TANK PARACHUTE-RECOVERABLE SOLID ROCKET BOOSTERS HIGH PERFORMANCE HYDROGEN-OXYGEN ENGINES PLACED IN THE ORBITER TO BE RECO∨ERED

SHUTTLE STUDIES • PHASE “B” STUDIES WERE PERFORMED IN MID 1970’S TO DETERMINE A PRELIMINARY DESIGN • R E S U L T S: – FULLY RECOVERABLE ORBITER – DISPOSABLE FUEL TANK – PARACHUTE-RECOVERABLE SOLID ROCKET BOOSTERS – HIGH PERFORMANCE HYDROGEN-OXYGEN ENGINES PLACED IN THE ORBITER TO BE RECOVERED 6

RESULTS OF STUDIES FULLY REUSABLE WITH FLY-BACK BOOSTER WAS GREATER THAN 5.1B MANY CONFIGURATIONS WERE STUDIED (EXAMPLES) TURN AROUND TIME REQUIRED LANDING A WINGED VEHICLE ON A RUNWAY PAYLOAD DEPLOYMENT AND RETRIEVAL REQUIREMENT DETERMINED LOCATION OF ORBITER ON LAUNCH CONFIGURATION

RESULTS OF STUDIES • FULLY REUSABLE WITH FLY-BACK BOOSTER WAS GREATER THAN 5.1B. • MANY CONFIGURATIONS WERE STUDIED (EXAMPLES) • TURN AROUND TIME REQUIRED LANDING A WINGED VEHICLE ON A RUNWAY • PAYLOAD DEPLOYMENT AND RETRIEVAL REQUIREMENT DETERMINED LOCATION OF ORBITER ON LAUNCH CONFIGURATION 7

MAJOR SHUTTLE CONFIGURATION DECISIONS HYDROGEN/OXYGEN MAIN ENGINES THIS SIZED THE LIQUID OXYGEN/HYDROGEN TANK WHICH IS NOT REUSABLE SOLID ROCKET BOOSTERS PROVIDED THE ADDITIONAL PROPULSION REQUIRED TO GET THE ORBITER INTO EARTH ORBIT SOLID ROCKET BOOSTERS DESIGNED TO BE RECOVERED AND RE-USED

MAJOR SHUTTLE CONFIGURATION DECISIONS • HYDROGEN/OXYGEN MAIN ENGINES • THIS SIZED THE LIQUID OXYGEN/HYDROGEN TANK, WHICH IS NOT REUSABLE • SOLID ROCKET BOOSTERS PROVIDED THE ADDITIONAL PROPULSION REQUIRED TO GET THE ORBITER INTO EARTH ORBIT • SOLID ROCKET BOOSTERS DESIGNED TO BE RECOVERED AND RE-USED 8

ORBITER DECISIONS ORBITER ENTRY CROSS RANGE REQUIRED DELTA WINGS DELETION OF AIR BREATHING ENGINES FOR MOVING ORBITER REQUIRED THE BOEING 747 TO CARRY THE ORBITER FO/FS GUIDANCE NAVIGATION. AND CONTROL SYSTEM FLY-BY- WIRE WITH A DIGITAL AUTO PILOT

ORBITER DECISIONS • ORBITER ENTRY CROSS RANGE REQUIRED DELTA WINGS • DELETION OF AIR BREATHING ENGINES FOR MOVING ORBITER REQUIRED THE BOEING 747 TO CARRY THE ORBITER • FO/FS GUIDANCE, NAVIGATION, AND CONTROL SYSTEM • FLY￾BY- WIRE WITH A DIGITAL AUTO PILOT 9

ORBITER DECISIONS SIZE OF PAYLOAD BAY 60 FEET LONG BY 15 FEET DIAMETER SIZE OF CREW CABIN DEFINED TO BE OVER 2600 CUBIC FEET PAYLOAD 65 000 POUNDS AT LIFT OFF AND 35 OO0 POUNDS AT LANDING THE ORBITER IS A LAUNCH VEHICLE A SPACE CRAFT AND AN AIRCRAFT

ORBITER DECISIONS • SIZE OF PAYLOAD BAY 60 FEET LONG BY 15 FEET DIAMETER • SIZE OF CREW CABIN DEFINED TO BE OVER 2600 CUBIC FEET • PAYLOAD 65,000 POUNDS AT LIFT OFF AND 35,OOO POUNDS AT LANDING • THE ORBITER IS A LAUNCH VEHICLE, A SPACE CRAFT, AND AN AIRCRAFT 10