The goal of this conceptual design was to devise a reusable, commercially viable, single-stage-to-orbit vehicle. The vehicle has the ability to deliver a 9100 kg (20,000 lb) payload to a low earth orbit of 433 km to 933 km (250 n.mi. - 450 n.mi.). The SSTO vehicle is 51 meters in length and has a gross takeoff mass of 680,400 kg (1,500,000 lb). The vehicle incorporates three RD-701 engines for the main propulsion system and two RL-10 engines for the orbital maneuvering system. The vehicle is designed for a three day stay on orbit with two crew members.
Access to Space
1994
137 pages
Report
Keine Angabe
Englisch
Unmanned Spacecraft , Manned Spacecraft , Aerospace planes , Launch vehicle configurations , Propulsion system configurations , Single stage to orbit vehicles , Space commercialization , Spacecraft design , Transatmospheric vehicles , Life cycle costs , Space transportation , Structural design , Wind tunnel models , Earth orbits , Hypersonic wind tunnels , Mission planning , Orbital maneuvers , Payloads , Rl-10 engines , Safety factors , Spacecrews
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