1996. A Rocket Powered Single-Stage-To-Orbit Launch Vehicle Using U.S. and Soviet Engines

Publication TypeConference Paper
AuthorsMacConochie, I.O.; Stanley, D.
Year of Publication1991
Paper Number1996
Conference50th Annual Conference, San Diego, California, May 20-22
Conference LocationSan Diego, California
Paper Category18. WEIGHT ENGINEERING - SPACECRAFT DESIGN
Pages16
Date Published5/20/91
Price$7.00
Order this PaperClick Here
Key Words18. WEIGHT ENGINEERING - SPACECRAFT DESIGN
AbstractA single-stage-to-orbit launch vehicle is used to assess the applicability of Soviet Energia high pressure hydrocarbon engines to advanced U.S. manned space transportation systems. Two of the Soviet engines are used with three Space Shuttle main engines. When applied to a baseline vehicle that utilized advanced hydrocarbon engines, the higher weight of the Soviet engines resulted in a 20 percent loss of payload capability and necessitated a change in the crew compartment size and location from mid-body to fore-body in order to balance the vehicle. Various combinations of Soviet and Shuttle engines were evaluated for comparison purposes, including an all hydrogen system using all Space Shuttle main engines. Operational aspects of the baseline vehicles are also discussed. A new mass properties program entitled Weights and Moments of Inertia (WAMI) is used in the study.