Optimal control of the elliptical orbit of an earth satellite with a low-thrust engine

Details Optimal control of the elliptical orbit of an earth satellite with a low-thrust engine Optimal control of the elliptical orbit of an earth satellite with a low-thrust engine

Sep 1980

adsabs.harvard.edu/cgi-bin/nph-data_query?bibcode=1980kosis..18..707v&link_type=abstract

Kosmicheskie Issledovaniia, vol. 18, Sept.-Oct. 1980, p. 707-714. In Russian.

Physics

1

Earth Orbits, Elliptical Orbits, Low Thrust Propulsion, Optimal Control, Satellite Orbits, Trajectory Optimization, Error Correcting Devices, Maximum Principle, Pontryagin Principle, Variational Principles

Scientific paper

The optimal correction of an elliptical orbit is considered for the case of a satellite with an ideal low-thrust engine. The Pontryagin maximum principle is used to solve the formulated variational problem. The optimal correction problem is solved for perigee and apogee distances, and the effect of atmospheric drag on the solution of the variational problem is analyzed.

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