Spacecraft optimal control in drag braking flight segment during insertion into orbit of Mars artificial satellite

The article analyzes the spacecraft optimal control problem while using a combined profile of the spacecraft insertion into the orbit of the Mars artificial satellite. The authors use both the maximum atmosphere escape velocity and the maximum width of the re-entry corridor of the spacecraft as the main criteria of optimization. Both an analytical method and algorithm are used for a high-speed calculation of the quasi-optimal trajectories of the spacecraft insertion into the satellite orbits. The obtained results are regarded as an initial approximation for solving the spacecraft optimal control problem in a general statement. The numerical data obtained during the research showed the possibility of implementing the proposed combined profile of the spacecraft insertion into the orbit, if a spacecraft with a lift-to-drag ratio of over 0.3 is used. The results are of practical importance and can be used while analyzing certain deep space missions.

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