The objective of the solar rocket concept analysis was to determine the potential value of solar-thermal rockets in large delta velocity space missions. A specific impulse of 872 seconds was achieved by passing hydrogen through a heat exchanger placed at the focal spot of a large parabolic dish solar concentrator mirror. With a windowed chamber type of thruster and a particle-laden hydrogen flow the specific impulse was 1041 seconds. Inflatable construction techniques were determined to be optimum for the large concentrating mirrors based on ease of deployment and low specific mass. It was concluded that the solar rocket offers the mission planner a viable option between the high payload-long trip time of the mercury ion bombardment system and the lower payload-short trip time of a LO2-LH2 stage. (Author)
Solar Rocket System Concept Analysis
1979
242 pages
Report
Keine Angabe
Englisch
Solar rocket system concept analysis
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