The optimization of the payload mass of single stage rocket vehicles is discussed. The free parameters, e.g., Earth radiation effects on solar arrays, prevent a general solution, so a much simplified scheme is proposed. Initial vehicle location and velocity are selected. The relation between these and initial vehicle mass is computed. Carrier rocket selection is based on the result of this computation. The cost of the unfuelled carrier, fuel, launcher-space vehicle integration, transportation to orbital position, and flight operation until end of mission is considered constant. Free parameters e.g., launch time, are chosen so that payload mass, or payload mass/initial vehicle mass, is maximized by trajectory optimization and vehicle mass allocation. Solutions for constant and variable exhaust speeds are shown. Ion engine performance is analyzed.
On Propulsive Optimization of Space Transportation Rocket Vehicles
1981
42 pages
Report
Keine Angabe
Englisch
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