A tradeoff study for a single-stage, earth-to-orbit transport spacecraft configured with low structural mass as the prime objective is presented. Among the major design elements affecting vehicle mass are: maneuverability and re-entry heating, the compatibility of an irregular cargo bay geometry to future mission requirements, the fabrication and assembly of large honeycomb structure fuselage sections, and the development of LOX/LH2 engine extendable nozzles and dual-propulsion schemes. It is shown that vehicle geometry and materials and structural technologies will be the critical areas in the development of such a system.
Technologies involved in configuring an advanced earth-to-orbit transport for low structural mass
Annual Conference of the Society of Allied Weight Engineers ; 1980 ; St. Louis, MO
1980-05-01
Conference paper
No indication
English
Advanced Mass Launchers for Low Earth Orbit
NTIS | 1989
|Advanced manned earth-to-orbit vehicle
NTRS | 1986
|Mass transportation to earth orbit
AIAA | 1989