Survey on spacecraft orbital pursuit-evasion differential games

Ya-zhong, Luo; Li, Zhenyu; Zhu, Hai

doi:10.1360/sst-2019-0174

Cited by 23 publications

(7 citation statements)

References 13 publications

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“…Differential games were first proposed by Isaacs [1], and as the study progressed, Berkovitz et al, deduced the necessary conditions for saddle points in this theory [2]. After studying differential games theory [3] in China, it will be applied to tracking game problem [4] [5]. Finally, it will be converted to solving two-point boundary value problem.…”

Section: Introductionmentioning

confidence: 99%

Research on game guidance and control of fixed time spacecraft

Wu,

Chen,

Zhang

2023

International Conference on Automation Control, Algorithm, and Intelligent Bionics (ACAIB 2023)

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The behavior of spacecraft in tracking game is studied by using the theory of differential game. This study is based on the premise that both sides of the game have continuous small thrusts, and the terminal distance is set as the payoff function. Since the altitude of the two sides of the orbit is time-varying, the proposed model has time-varying characteristics. Finally, the problem is transformed into a two-point boundary value problem with high dimensional timevarying nonlinear. In order to solve the two-point boundary value problem, the multi-shooting method is usually adopted, but this method is very sensitive to the initial value problem, and the model has large error. To solve this problem, a hybrid algorithm combining multi-shooting method and particle swarm algorithm is proposed and numerical solutions are given. In the method, the initial value of the co-state variable is estimated by the particle swarm algorithm, and then it is brought into the multiple shooting method to obtain the solution of the problem. The simulation example shows that the hybrid algorithm has high calculation accuracy for the tracking game problem, and the calculation example finally gives the trajectories of both sides of the game.

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Section: Introductionmentioning

confidence: 99%

Research on game guidance and control of fixed time spacecraft

Wu,

Chen,

Zhang

2023

International Conference on Automation Control, Algorithm, and Intelligent Bionics (ACAIB 2023)

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“…As the number of near-Earth space objects increases, there is growing attention to the importance of the orbital evasion problem. The problem of orbital evasion originates from the problem of orbital rendezvous and interception, in which the spacecraft needs to evade other maneuvering or nonmaneuvering space objects that may be about to collide through its own control [1]. 1 0000-0000 © 2023 IEEE Authors' addresses: Kunpeng Zhang, Yao Zhang, Ji Ye, and Hongbo Wang are with School of Aerospace Engineering, Beijing Institute of Technology, 100081 Beijing, People's Republic of China, Email: (zhangkunpeng@bit.edu.cn, zhangyao@bit.edu.cn, 3120210094@bit.edu.cn, wanghongbo2021@bit.edu.cn).…”

Section: Introductionmentioning

confidence: 99%

“…The problem of orbital evasion originates from the problem of orbital rendezvous and interception, in which the spacecraft needs to evade other maneuvering or nonmaneuvering space objects that may be about to collide through its own control [1]. 1 0000-0000 © 2023 IEEE Authors' addresses: Kunpeng Zhang, Yao Zhang, Ji Ye, and Hongbo Wang are with School of Aerospace Engineering, Beijing Institute of Technology, 100081 Beijing, People's Republic of China, Email: (zhangkunpeng@bit.edu.cn, zhangyao@bit.edu.cn, 3120210094@bit.edu.cn, wanghongbo2021@bit.edu.cn). Heng Shi and Huang Huang are with Beijing Institute of Control Engineering, Early studies on orbital evasion were mostly carried out against non-maneuvering space objects.…”

Section: Introductionmentioning

confidence: 99%

Escape-Zone-Based Optimal Evasion Guidance Against Multiple Orbital Pursuers

Zhang

Shi³

et al. 2023

IEEE Trans. Aerosp. Electron. Syst.

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The orbital evasion problem is getting increasing attention because of the increase of space maneuvering objects. In this paper, an escape-zone-based optimal orbital evasion guidance law for an evading spacecraft on near circular reference orbit is proposed against multiple pursuing spacecraft with impulsive thrust. The relative reachable domain is introduced first and approximated as an ellipsoid propagating along the nominal trajectory under the short-term assumption. The escape zone for the impulsive evasion problem is presented herein as a geometric description of the set of terminal positions for all the impulsive evasion trajectories that are not threatened by the maneuvers of pursuers at the maneuver moment. A general method is developed next to calculate the defined escape zone through finding the intersection of two relative reachable domain approximate ellipsoids at arbitrary intersection moment. Then, the two-sided optimal strategies for the orbital evasion problem are analyzed according to whether the escape zone exists, based on which the escape value is defined and used as the basis of the proposed orbital evasion guidance scheme. Finally, numerical examples demonstrate the usefulness of the presented method for calculating escape zone and the effectiveness of the proposed evasion guidance scheme against multiple pursuing spacecraft. 1

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“…Generally, the problem can be considered as a twoplayer zero-sum different game, which is essentially a two-sided trajectory optimization problem with contradic-tory goals [4]. To solve this particular trajectory optimization problem, many methods have been proposed including collocation, parameterization, swarm optimization, and evolutionary algorithm [5], but they are either computation-intensive and time-consuming or sensitive to initial guess.…”

Section: Introductionmentioning

confidence: 99%

An AutoML based trajectory optimization method for long-distance spacecraft pursuit-evasion game

Yang

Lee

Zhu

2023

J. of Syst. Eng. Electron.

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Current successes in artificial intelligence domain have revitalized interest in spacecraft pursuit-evasion game, which is an interception problem with a non-cooperative maneuvering target. The paper presents an automated machine learning (AutoML) based method to generate optimal trajectories in long-distance scenarios. Compared with conventional deep neural network (DNN) methods, the proposed method dramatically reduces the reliance on manual intervention and machine learning expertise. Firstly, based on differential game theory and costate normalization technique, the trajectory optimization problem is formulated under the assumption of continuous thrust. Secondly, the AutoML technique based on sequential model-based optimization (SMBO) framework is introduced to automate DNN design in deep learning process. If recommended DNN architecture exists, the tree-structured Parzen estimator (TPE) is used, otherwise the efficient neural architecture search (NAS) with network morphism is used. Thus, a novel trajectory optimization method with high computational efficiency is achieved. Finally, numerical results demonstrate the feasibility and efficiency of the proposed method.

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Survey on spacecraft orbital pursuit-evasion differential games

Cited by 23 publications

References 13 publications

Research on game guidance and control of fixed time spacecraft

Research on game guidance and control of fixed time spacecraft

Escape-Zone-Based Optimal Evasion Guidance Against Multiple Orbital Pursuers

An AutoML based trajectory optimization method for long-distance spacecraft pursuit-evasion game

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