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Online trajectory optimization and guidance algorithm for space interceptors with nonlinear terminal constraints via convex programming

Yuan Li (Nanjing University of Science and Technology, Nanjing, China)
Ruisheng Sun (Nanjing University of Science and Technology, Nanjing, China)
Wei Chen (Nanjing University of Science and Technology, Nanjing, China)

Aircraft Engineering and Aerospace Technology

ISSN: 0002-2667

Article publication date: 15 June 2022

Issue publication date: 2 January 2023

65

Abstract

Purpose

In this paper, an online convex optimization method for the exoatmospheric ascent trajectory of space interceptors is proposed. The purpose of this paper is to transform the original trajectory optimization problem into a sequence of convex optimization subproblems.

Design/methodology/approach

For convenience in calculating accuracy and efficiency, the complex nonlinear terminal orbital elements constraints are converted into several quadratic equality constraints, which can be better computed by a two-step correction method during the iteration. First, the nonconvex thrust magnitude constraint is convexified by the lossless convexification technique. Then, discretization and successive linearization are introduced to transform the original problem into a sequence of one convex optimization subproblem, considering different flight phases. Parameters of trust-region and penalty are also applied to improve the computation performance. To correct the deviation in real time, the iterative guidance method is applied before orbit injection.

Findings

Numerical experiments show that the algorithm proposed in this paper has good convergence and accuracy. The successive progress can converge in a few steps and 3–4 s of CPU time. Even under engine failure or mission change, the algorithm can yield satisfactory results.

Practical implications

The convex optimization method presented in this paper is expected to generate a reliable optimal trajectory rapidly in different situations and has great potential for onboard applications of space interceptors.

Originality/value

The originality of this paper lies in the proposed online trajectory optimization method and guidance algorithm of the space inceptors, especially for onboard applications in emergency situations.

Keywords

Acknowledgements

This work was supported by the National Natural Science Foundation of China under Grant 51809138 and China Postdoctoral Science Foundation under Grant 2019M651837.

Citation

Li, Y., Sun, R. and Chen, W. (2023), "Online trajectory optimization and guidance algorithm for space interceptors with nonlinear terminal constraints via convex programming", Aircraft Engineering and Aerospace Technology, Vol. 95 No. 1, pp. 53-61. https://doi.org/10.1108/AEAT-01-2022-0005

Publisher

:

Emerald Publishing Limited

Copyright © 2022, Emerald Publishing Limited

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