Pursuer’s Control Strategy for Orbital Pursuit-Evasion-Defense Game with Continuous Low Thrust Propulsion

Jianhua Cheng,Shuo Wang,Junfeng Zhou,Lin Zhao,Yipeng Wang

doi:10.3390/app9153190

Jianhua Cheng, Shuo Wang + Show 3 more

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https://doi.org/10.3390/app9153190

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Journal: Applied Sciences	Publication Date: Aug 5, 2019
Citations: 4	License type: CC BY 4.0

Affiliation: Harbin Engineering University

Abstract

This paper studies the orbital pursuit-evasion-defense problem with the continuous low thrust propulsion. A control strategy for the pursuer is proposed based on the fuzzy comprehensive evaluation and the differential game. First, the system is described by the Lawden’s equations, and simplified by introducing the relative state variables and the zero effort miss (ZEM) variables. Then, the objective function of the pursuer is designed based on the fuzzy comprehensive evaluation, and the analytical necessary conditions for the optimal control strategy are presented. Finally, a hybrid method combining the multi-objective genetic algorithm and the multiple shooting method is proposed to obtain the solution of the orbital pursuit-evasion-defense problem. The simulation results show that the proposed control strategy can handle the orbital pursuit-evasion-defense problem effectively.

Highlights

The orbital pursuit-evasion problem has attracted increasing attention in space research [1,2,3,4]
The differences between the two examples are that when performing orbital maneuvers, the pursuer in Example 1 adopts the control strategy based on the fuzzy comprehensive evaluation, while the pursuer in Example 2 does not consider the impact of the defender, that is, the parameters k1 = 1, k2 = 0 in the objective function JP
The simulation results show that when the pursuer control is in a dominant position, the control strategy proposed in this paper can make the pursuer bypass the defender and capture the evader, and that when the pursuer control is not in a dominant position, the control strategy proposed in this paper can prolong the time that the defender takes to intercept the pursuer

Summary

Introduction

The orbital pursuit-evasion problem has attracted increasing attention in space research [1,2,3,4]. In reference [7], a method based on periodically updating the solution of the two-point boundary value problem (TPBVP) was proposed to generate near optimal feedback controls for the orbital pursuit-evasion problem. This method is time-consuming and difficult to be applied in real time. References [9,10,11]

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Results

Conclusion