Approximate Calculation of Required and Available Lateral Range Achieved in a Spacecraft Descent to a Preset Point on the Earth's Surface

Details Approximate Calculation of Required and Available Lateral Range Achieved in a Spacecraft Descent to a Preset Point on the Earth's Surface Approximate Calculation of Required and Available Lateral Range Achieved in a Spacecraft Descent to a Preset Point on the Earth's Surface

Nov 2005

adsabs.harvard.edu/cgi-bin/nph-data_query?bibcode=2005cosre..43..442y&link_type=abstract

Cosmic Research, Volume 43, Issue 6, pp.442-449

Physics

Scientific paper

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.

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