Scenarios of payload delivery by STS and by Ariane launch vehicle were examined to determine possible missions using orbital propulsion modules. Propulsion system options and requirements were studied for low Earth, geosynchronous, high eccentric, and escape orbits. Criteria are established for the selection of mission types and the choice of three missions is justified. Results of technical and architectural studies of 9 combinations (3 options, 3 missions) of the orbital propulsion module are presented. It is shown that the module selected should provide better performance than the other possible options and that the stage selected offers easy to design interfaces that are compatible with Ariane 4 and 5 and with the STS. An economic analysis methodology is described which can indicate which option to choose for each mission.
Orbital Propulsion Module System Configuration Study, Volume 2
1983
368 pages
Report
No indication
English
SLUB | 1984
SLUB | 1984