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 1TOP 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 2SHUTTLE 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 3SHUTTLE 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 4SHUTTLE STUDIES • PRINCIPAL ISSUES: – ENTRY TECHNIQUES – LANDING SPEED – APPROACH PATTERN 5SHUTTLE STUDIES • PHASE “B” STUDIES WERE PERFORMED IN MID 1970’S 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 RECOVERED 6RESULTS 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 7MAJOR 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 8ORBITER 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 9ORBITER 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 10HARDWARE SUB-SYSTEMS • THERMAL PROTECTION SYSTEM • STRUCTURES • SPACE SHUTTLE MAIN ENGINES • HYDRAULIC, AUX POWER, FUEL CELLS. OMS, & RCS SYSTEMS • GUIDANCE, NAVIGATION, AND CONTROL • ENVIRONMENTAL CONTROL & LIFE SUPPORT IN CREW CABIN • LANDING & MECHANICAL SYSTEMS • COMMUNICATIONS • ELECTRICAL POWER 11ORBITER SUB-SYSTEMS • MAJOR ISSUES – FUNCTIONS THAT ARE REQUIRED TO BE PERFORMED (FUNCTIONAL REQUIREMENTS) – PERFORMANCE THAT IS REQUIRED (PERFORMANCE REQUIREMENTS) – WEIGHT – INTERFACES – AVAILABLE TECHNOLOGY – SCHEDULE – COST 12ANALYTICAL STUDIES • AERODYNAMICS • AEROTHERMODYNAMICS