Optimal control during the active segment of spacecraft landing on an atmosphereless planet

Details Optimal control during the active segment of spacecraft landing on an atmosphereless planet Optimal control during the active segment of spacecraft landing on an atmosphereless planet

Jul 1979

adsabs.harvard.edu/cgi-bin/nph-data_query?bibcode=1979kosis..17..506i&link_type=abstract

Kosmicheskie Issledovaniia, vol. 17, July-Aug. 1979, p. 506-519. In Russian.

Physics

Aircraft Maneuvers, Optimal Control, Planetary Landing, Trajectory Optimization, Differential Equations, Equations Of Motion, Trajectory Analysis

Scientific paper

A nonlinear transformation approach in the Euler-Lagrange variational framework is used to determine the fuel-optimal trajectory during the active descent stage of a spacecraft landing on an atmosphereless planet. Conditions of optimal thrust vector control are established; an approximate solution of the nonlinear equations of motion makes it possible to determine conditions under which mass changes are independent of thrust vector angle deviations.

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