Analytical models were developed to analyze payload transport from space shuttles. The models allow for different transfer stage configurations, the mass of rocket engines, the performance of rocket propellants, and the cost of upper rocket stages. A trajectory calculation model allows space missions to be studied. Only the cost is chosen as a variable for the parametrical presentation of the results. Optimal propulsion platforms for three mission ranges are proposed. For minimum velocity requirements the platform is characterized by isotensoidal tank, hydrazine, and super-blowdown feed system.
Analysis and Optimization of Small Space Shuttle Propulsion Platforms
1984
215 pages
Report
Keine Angabe
Englisch
Space Launch Vehicles & Support Equipment , Rocket Engines & Motors , Propulsion system configurations , Propulsion system performance , Space shuttles , Systems analysis , Design analysis , Feed systems , Fuel tanks , Hydrazine engines , Space shuttle payloads , Upper stage rocket engines , Foreign technology
NTIS | 1994
NTIS | 1970
|NTIS | 1994
NTRS | 1970
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