Abstract The results of calculation of the required lateral range are presented for the orbital reentry of a spacecraft having a preset inclination and preset ascending node longitude to land at a preset point on the Earth's surface. The suboptimum laws of roll angle variation in velocity are determined, which allows one to reach the maximum available lateral range for a given value of constant lift-to-drag ratio taking into account constraints imposed on the maximum equilibrium temperature.
Approximate Calculation of Required and Available Lateral Range Achieved in a Spacecraft Descent to a Preset Point on the Earth's Surface
Cosmic Research ; 43 , 6 ; 442-449
2005-11-01
8 pages
Aufsatz (Zeitschrift)
Elektronische Ressource
Englisch
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