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The problem of optimization of the heliocentric segment of the interplanetary trajectory between two planets of a spacecraft with a limited thrust engine is considered. The description of homotopy between the optimal trajectory with limited power or Keplerian trajectory (solution of Lambert's problem) and the optimal trajectory with limited thrust is given. The thrust minimization problem is introduced, by means of which the existence domain of the solution is calculated. The problem of joint optimization of control, main trajectory and design parameters of a spacecraft with a limited thrust engine is considered. Numerical examples of optimal trajectories are given.

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Optimization of Interplanetary Trajectories for a Limited-Thrust Spacecraft

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  • 发表日期：

    2025年

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  • Vyacheslav G. Petukhov

摘要

The problem of optimization of the heliocentric segment of the interplanetary trajectory between two planets of a spacecraft with a limited thrust engine is considered. The description of homotopy between the optimal trajectory with limited power or Keplerian trajectory (solution of Lambert's problem) and the optimal trajectory with limited thrust is given. The thrust minimization problem is introduced, by means of which the existence domain of the solution is calculated. The problem of joint optimization of control, main trajectory and design parameters of a spacecraft with a limited thrust engine is considered. Numerical examples of optimal trajectories are given.