Methodology of Spacecraft Optimal Control in the Atmosphere During the Subsequent Orbit Injection of Artificial Satellite of Mars

The subject of optimal control is researched during the insertion of the space vehicle into the orbit of Mars artificial satellite with the preliminary aerodynamic braking in the atmosphere. The space vehicle control methodology of roll angle and angle of attack is elaborated. Variational problems are solved for minimization of necessary power inputs and maximization of space vehicle re-entry corridor. Possibility in principle and high power efficiency of the suggested orbit shaping scheme are shown. Key-Words: Optimal control, space vehicle, aerodynamic characteristic, orbital injection, required energy consumption, re-entry corridor.