Application of the gradient method to the solution of some problems in space flight dynamics

Details Application of the gradient method to the solution of some problems in space flight dynamics Application of the gradient method to the solution of some problems in space flight dynamics

May 1977

adsabs.harvard.edu/cgi-bin/nph-data_query?bibcode=1977kosis..15..331p&link_type=abstract

Kosmicheskie Issledovaniia, vol. 15, May-June 1977, p. 331-335. In Russian.

Physics

Dynamic Characteristics, Spacecraft Control, Spacecraft Maneuvers, Acceleration (Physics), Angles (Geometry), Equations Of Motion, Optimal Control, Orbit Calculation, Satellite Orbits

Scientific paper

The gradient method outlined by Eneev (1966) is applied to the problem
of optimal parameter control during the execution of a maneuver within
strict time limits. The specific problem of calculating the maximum
angle of rotation of the orbital plane of a satellite with binormal
acceleration is examined. Solutions are obtained for one example.

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