Estimated optimum control of a spacecraft by the rocket engine thrust vector at the extraatmospheric section of the reentry of an artificial earth satellite

Details Estimated optimum control of a spacecraft by the rocket engine thrust vector at the extraatmospheric section of the reentry of an artificial earth satellite Estimated optimum control of a spacecraft by the rocket engine thrust vector at the extraatmospheric section of the reentry of an artificial earth satellite

Mar 1992

adsabs.harvard.edu/cgi-bin/nph-data_query?bibcode=1992kosis..30..180s&link_type=abstract

Kosmicheskie Issledovaniia (ISSN 0023-4206), vol. 30, no. 2, Mar.-Apr. 1992, p. 180-193. In Russian.

Physics

Atmospheric Entry, Optimal Control, Reentry Trajectories, Rocket Engine Control, Satellite Orbits, Thrust Vector Control, Gravitational Effects, Orbital Elements, Variational Principles

Scientific paper

The paper investigates optimal, minimum-fuel control of a spacecraft by the rocket engine thrust vector on the extraatmospheric section of the reentry of a satellite. The control design, which provides for firing of the engine twice, is shown to be highly efficient. A high-speed algorithm is developed for calculating the estimated optimum reentry trajectories to the prescribed area of the earth surface.

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