Time-optimal transfer of an artificial earth satellite on a near-circular orbit with low transverse thrust

Details Time-optimal transfer of an artificial earth satellite on a near-circular orbit with low transverse thrust Time-optimal transfer of an artificial earth satellite on a near-circular orbit with low transverse thrust

Nov 1985

adsabs.harvard.edu/cgi-bin/nph-data_query?bibcode=1985kosis..23..933o&link_type=abstract

Kosmicheskie Issledovaniia (ISSN 0023-4206), vol. 23, Nov.-Dec. 1985, p. 933-937. In Russian.

Physics

Circular Orbits, Orbital Maneuvers, Satellite Orbits, Trajectory Optimization, Transfer Orbits, Method Of Moments, Nonlinear Systems, Time Optimal Control

Scientific paper

The analysis of the time-optimal problem assumes the nearness of the initial and final orbits to a circular orbit, making it possible to linearize the equations of motion with respect to a reference circular orbit, close to the final one. The time-optimal problem can then be solved for the linearized problem by the method of moments. Convex minimization of a function of three variables is carried out, providing for a solution from any initial approximation; this solution is used to obtain a quasi-optimal solution in the initial nonlinear system. Some numerical results are presented.

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