A single-stage-to-orbit launch vehicle is used to assess the applicability of Soviet Energia high-pressure-hydrocarbon engine 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 forebody 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 vehicle are also discussed. A new mass properties program entitles Weights and Moments of Inertia (WAMI) is used in the study.
A Rocket Powered Single-Stage-to-Orbit Launch Vehicle With U.S. and Soviet Engineers
50th Annual Conference of the Society of Allied Weight Engineers, Inc. ; 1991 ; San Diego, CA, United States
1991-01-01
Aufsatz (Konferenz)
Keine Angabe
Englisch
A Rocket Powered Single-Stage-to-Orbit Launch Vehicle with U.S. and Soviet Engines
British Library Conference Proceedings | 1991
|