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 – FLYBY-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