Optimization of the finite-thrust trajectory in the vicinity of a circular orbit

The paper considers the problem of the optimization of the finite-thrust trajectory in the vicinity of the circular orbit. The fixed-time rendezvous missions are considered. The Hill-Clohessy-Wiltshire equations are used to describe spacecraft motion. Maximum principle is used to solve the optimal control problem. The paper presents closed-form optimization of the power-limited trajectory both for two-and three-channel control. These closed-form solutions are used as initial guess values for numerical optimization of trajectory with constant ejection velocity. Numerical examples of optimal trajectories are presented. Impact of thrust magnitude and thrust steering constraints on parameters of the optimal trajectory is discussed. © 2021, Univelt Inc. All rights reserved.