Liquid propulsion systems for orbital transfer of satellites were studied. A self-standing stage with all necessary housekeeping functions; modular assembly; and integrated propulsion were considered. Because the stage and the module lead to the same structural mass, advantages of these two configurations can be combined to give a stage from which elements can be removed (structural elements and propellant tanks to fit the mission need; electrical elements as far as the satellite uses its own functions). This stage with removable elements requires more complicated cabling than in traditional vehicles, but this does not cause feasibility problems, and in the worst case a mass penalty of 10 kg results.
Orbital Propulsion Module System Configuration Study. Volume 1: Executive Summary
1983
70 pages
Report
Keine Angabe
Englisch