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.
Optimization of Interplanetary Trajectories for a Limited-Thrust Spacecraft
Studies in Systems, Decision and Control
Through Optimization of Aerospace Vehicle Trajectories by the Pontryagin Maximum Principle ; Chapter : 9 ; 367-427
2025-05-29
61 pages
Article/Chapter (Book)
Electronic Resource
English
Lambert problem , Thrust minimization problem , Limited thrust problem , Joint optimization of trajectory and design parameters , Domain of solution existence , Critical value of the hyperbolic excess velocity , Smoothing Optimization , Mechanical Engineering , Aerospace Technology and Astronautics , Computational Intelligence , Control and Systems Theory , Engineering