Non-linear solution to the maximum height orbit transfer guidance problem

Author:

Afshari H H1,Taheri E2

Affiliation:

1. Department of Mechanical Engineering, McMaster University, Hamilton, Ontario, Canada

2. Department of Mechanical Engineering - Engineering Mechanics, Michigan Technological University, Houghton, Michigan, USA

Abstract

An optimal control solution to the highly non-linear problem of orbit transfer mission is achieved by using a newly proposed analytical perturbation technique. The problem is classified as a two-point boundary value problem in order to optimize a performance measure in a given time. Assuming a constant thrust operating in a given length of time, it is sought to find the thrust direction history of a transfer from a given initial orbit to the largest possible orbit. The system dynamical model is stated by regarding a variable mass spacecraft moving in the variable gravitational field of the Earth, based on the two-body problem. To assess the perturbation solution fidelity, a numerical solution based on the Gauss pseudospectral method has been employed. The main novelty of this work is in applying a new analytical solution strategy that is a combination of perturbation technique and backward integration to a highly non-linear problem in the calculus of variations approach.

Publisher

SAGE Publications

Subject

Mechanical Engineering,Aerospace Engineering

Cited by 5 articles. 订阅此论文施引文献 订阅此论文施引文献,注册后可以免费订阅5篇论文的施引文献,订阅后可以查看论文全部施引文献

1. Low-Thrust Spacecraft Trajectory Optimization with Gravity-Assist Maneuver using Dymos;AIAA SCITECH 2024 Forum;2024-01-04

2. Global Optimization in Space Engineering;Encyclopedia of Optimization;2022-09-21

3. Shaping low-thrust trajectories with thrust-handling feature;Advances in Space Research;2018-02

4. Initial three-dimensional low-thrust trajectory design;Advances in Space Research;2016-02

5. Fast Initial Trajectory Design for Low-Thrust Restricted-Three-Body Problems;Journal of Guidance, Control, and Dynamics;2015-11

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