Optimal correction of the orbital parameters of a spacecraft with a low-thrust engine

Details Optimal correction of the orbital parameters of a spacecraft with a low-thrust engine Optimal correction of the orbital parameters of a spacecraft with a low-thrust engine

Sep 1983

adsabs.harvard.edu/cgi-bin/nph-data_query?bibcode=1983kosis..21..666i&link_type=abstract

Kosmicheskie Issledovaniia (ISSN 0023-4206), vol. 21, Sept.-Oct. 1983, p. 666-674. In Russian.

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Computation

1

Low Thrust, Spacecraft Control, Time Optimal Control, Transfer Orbits, Calculus Of Variations, Correction, Orbital Maneuvers

Scientific paper

An analysis is made of the time-optimal modes of control of the plane transfer orbit of a spacecraft with a low-thrust engine. The acceleration due to the thrust is constant in magnitude and transverse in direction. The variational problem is solved for a central gravitational field, and a method for taking into account the second zonal harmonic in the geopotential expansion is indicated. A description is then given of an approximate method for determining the time of correction, the method not requiring computer-aided numerical computations.

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