Optimal Control of a Spacecraft During Descent in the Martian Atmosphere

Abstract

The way for optimal controlling a spacecraft under its motion in the Martian atmosphere is examined. The minimum final velocity is taken as an optimality criterion. A procedure for calculating the spacecraft trajectories is developed based on the formalism of the Pontryagin maximum principle. The high efficiency of two-parameter control of the spacecraft is shown. The results can be used for exploring Mars and other planets.