Analysis of possibilities for combined deceleration of a spacecraft in the atmosphere

Details Analysis of possibilities for combined deceleration of a spacecraft in the atmosphere Analysis of possibilities for combined deceleration of a spacecraft in the atmosphere

Mar 1977

adsabs.harvard.edu/cgi-bin/nph-data_query?bibcode=1977kosis..15..179k&link_type=abstract

Kosmicheskie Issledovaniia, vol. 15, Mar.-Apr. 1977, p. 179-185. In Russian.

Astronomy and Astrophysics

Astronomy

Atmospheric Entry, Deceleration, Hyperbolic Trajectories, Spacecraft Maneuvers, Ablation, Aerodynamic Drag, Astrodynamics, Rocket Thrust

Scientific paper

A combined deceleration maneuver is examined for an axisymmetric spacecraft approaching earth at hyperbolic velocity. The maneuver considered involves active deceleration outside the atmosphere by firing rocket engines and passive deceleration within the atmosphere due to aerodynamic drag. Optimum conditions for spacecraft motion within the atmosphere are determined, and the parameter governing the durations of the active and passive phases of deceleration is obtained. The total mass losses experienced by the spacecraft due to heat-shield ablation while executing the combined maneuver are calculated.

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