The characteristics of an optimum thrust program depending on the individual mission of a spacecraft propulsion system and the present state-of-art of realization are discussed. Results of additional theoretical and experimental investigations are presented which confirm that arbitrary at least near-optimum thrust profiles may be realized with solid propellant rockets. In practice, however, overall optimization calls for a compromise between thrust program, structure weight, cost effectiveness, and reliability. (Author)
Methods for Approximate Optimum Thrust Programming of Solid Propellant Rockets for Spacecraft Applications
1975
244 pages
Report
No indication
English
Thrust modulation in solid propellant rockets
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