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.

Authors
Petukhov V.G. 1 , Olívio A.P. 2
Conference proceedings
Advances in the Astronautical Sciences
Publisher
Univelt Inc.
Language
English
Pages
5-15
Status
Published
Volume
174
Year
2021
Organizations
  • 1 Research Institute of Applied Mechanics and Electrodynamics, Moscow Aviation Institute, 5 Leningradskoye Shosse, p/o 43, Moscow, 125080, Russian Federation
  • 2 University of Russia, RUDN University, 6 Miklukho-Maklaya Street, Moscow, 117198, Russian Federation
Keywords
Optimal control systems; Optimization; Space applications; Space flight; Space platforms; Closed form solutions; Ejection velocity; Hill-Clohessy-Wiltshire equations; Numerical optimizations; Optimal control problem; Optimal trajectories; Spacecraft motion; Thrust steering; Orbits
Date of creation
16.12.2021
Date of change
16.12.2021
Short link
https://repository.rudn.ru/en/records/article/record/76275/
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