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 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 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 4 SHUTTLE STUDIES ? PRINCIPAL ISSUES: – ENTRY TECHNIQUES – LANDING SPEED – APPROACH PATTERN 5 SHUTTLE 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 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 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 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 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,OOO POUNDS AT LANDING ? THE ORBITER IS A LAUNCH VEHICLE, A SPACE CRAFT, AND AN AIRCRAFT 10 ORBITER SUB-SYSTEMS ? THERMAL PROTECTION SYSTEM ? GUIDANCE, NAVIGATION, AND CONTROL ? HYDRAULIC ? AUXILIARY POWER UNIT ? LANDING SYSTEM ? CREW CABIN ?ELECTRICAL POWER ? ORBITAL MANUEVERING SYSTEM ? REACTION CONTROL SYSTEM ? COMMUNICATIONS ? ENVIRONMENTAL CONTROL AND LIFE SUPPORT ? PAYLOAD DEPLOYMENT AND RETRIEVAL ? STRUCTURES 11 ORBITER 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 12