Control of a descent vehicle from earth-satellite orbit

Details Control of a descent vehicle from earth-satellite orbit Control of a descent vehicle from earth-satellite orbit

Jan 1980

adsabs.harvard.edu/cgi-bin/nph-data_query?bibcode=1980kosis..18...57i&link_type=abstract

Kosmicheskie Issledovaniia, vol. 18, Jan.-Feb. 1980, p. 57-62. In Russian.

Physics

Artificial Satellites, Descent Trajectories, Reentry Guidance, Satellite Orbits, Spacecraft Control, Time Optimal Control, Algorithms, Earth (Planet), Maximum Principle, Nonlinear Programming, Nonlinear Systems, Reentry Vehicles, Space Stations

Scientific paper

The maximum principle is used to treat the problem of time-optimal descent to the earth of a semiballistic capsule from an orbital station. The nonlinear two-point problem with nonspecified time is reduced to the problem with a free right end and specified time; this latter problem is solved by nonlinear programming. The proposed algorithm can be used for the optimization of a class of nonlinear systems with constraints on the phase variables and control.

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