The problem of optimization of multi-revolution trajectories between elliptical noncoplanar orbits is considered. The necessary conditions of optimality in the thrust minimization problem are given, which is used to diagnose the existence of a solution to the trajectory optimization problem of a spacecraft with limited thrust. A general scheme for solving the trajectory optimization problem with a limited thrust engine and numerical examples are given.
Optimization of Multi-revolution Flights Between Elliptical Non-complanar Orbits
Studies in Systems, Decision and Control
Through Optimization of Aerospace Vehicle Trajectories by the Pontryagin Maximum Principle ; Chapter : 11 ; 451-467
2025-05-29
17 pages
Article/Chapter (Book)
Electronic Resource
English
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