Optimal Pursuit/Evasion Spacecraft Trajectories in the Hill Reference Frame

Stupik, Joan; Pontani, Mauro; Conway, Bruce A.

doi:10.2514/6.2012-4882

Cited by 32 publications

(30 citation statements)

References 9 publications

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“…Recently, the EH reference frame has been used to describe the linear dynamics of the spacecraft PE game. 17 In Ref. 17, the objective function of both the players is the time to intercept.…”

Section: Introductionmentioning

confidence: 99%

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Optimization Of Spacecraft Pursuit-Evasion Game Trajectories In The Euler-Hill Reference Frame

Jagat

Sinclair

2014

AIAA/AAS Astrodynamics Specialist Conference

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Spacecraft pursuit-evasion game is formulated as a two-player zero-sum differential game. The Euler-Hill reference frame is used to describe the dynamics of the game. The goal is to derive feedback control law which forms a saddle point solution to the game. Both spacecraft use continuous thrust engines. The standard linear-quadratic differential game theory is applied to obtain linear control law. The state-dependent Riccati equation method is applied to extend the standard linear-quadratic differential game theory to obtain nonlinear control law. The efficacy of the nonlinear control law is found to be superior to that of the linear control law.

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Section: Introductionmentioning

confidence: 99%

“…17 In Ref. 17, the objective function of both the players is the time to intercept. The pursuer tries to minimize the time to intercept while the evader tries to maximize it.…”

Section: Introductionmentioning

confidence: 99%

Optimization Of Spacecraft Pursuit-Evasion Game Trajectories In The Euler-Hill Reference Frame

Jagat

Sinclair

2014

AIAA/AAS Astrodynamics Specialist Conference

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“…And using s and c with replacing sin and cos respectively and substituting P f as equations (6), then the co-state equations above can be written as equation (17). 5 4 6 5 4 6 2 1 2 3 4 4 3 3 5 6 2 2 5 1 3 1 1 5 5 4 4 4 5 4 3 3 5 6 3 2 5 3 1 5 1 1 1 3 6 5 4 6 3 6 2 5 1 3 1 5 4 2 2 c c c s 3 s 3c 2 2 2s 2 c s c c 3 2 c 2 s s 3c 2 2 2s 2 c s 6 s 2 c c …”

Section: T T T T T T T T Tmentioning

confidence: 99%

“…And good initial guess is required to guarantee the convergence and correctness of the solving process. In order to avoid these faults, the TPBVP was transformed to an unconstrained optimization problem where the design variables are the 13 knowns and the objective was constructed by minimize the distance between the function values formed from the equalities constraints (15), (17) and (18) and the original. The distance driving to zero in the optimize process equals to the satisfaction of the equalities constraints.…”

Section: Satellites Pursuit and Evasion Solving Based On Mixed Optimimentioning

confidence: 99%

Revisiting the two-side optimization problem in satellite pursuit-evasion

Zhang

et al. 2017

MATEC Web Conf.

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Abstract. In the present paper two-side optimization problem where the intercepting satellite pursuits the target satellite was studied. In the pursuit-evasion game the continuous thruster and the simple central gravity with J2 perturbation were involved for two satellites. With applying the functional extremum condition, the optimal control outputs of both side satellites were obtained by building the systems Hamilton function. Further, the two side optimal problem was transformed to the TPBVP, which contributed the solution with the mixed numerical method. Finally, the proposed method was validated by the numerical simulation, where the optimal interception and escaping trajectories were illustrated.

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“…">Relative Orbital DynamicsThe orbital pursuit-evasion-defense game occurs in the final phase of the confrontation when the spacecraft are close enough so that they can identify each other with onboard electronic devices [4]. In this type of situation, the motion between the spacecraft can be expressed as relative motion [23]. As is known, Lawden's equations [24] and Clohessy-Wiltshire (C-W) equations [25] are two linearized equations used to describe the relative motion between spacecrafts.…”

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confidence: 99%

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

et al. 2019

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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. Appl. Sci. 2019, 9, 3190 2 of 16 information game and presented the adaptive strategies for the pursuer and the evader. Ghosh et al. [17] developed a near-optimal feedback controller for the two-player pursuit-evasion games by using a new extremal-field approach. The above works were studied in the two-player pursuit-evasion game framework. However, in this framework, the evader can only perform maneuvers by itself to avoid threats. It is called self-defense, which disturbs the original mission of the evader and requires a large additional amount of fuel.To overcome this disadvantage, a defender is introduced in [18]. The role of the defender is intercepting the pursuer. In this way, the evader can perform its original mission without being disturbed. A hybrid method combined particle swarm optimization with a Newton-Interpolation algorithm was proposed to solve the orbital defense problem. However, because of the introduction of the defender, the pursuer must avoid the interception by the defender while capturing the evader [19], which makes the design of the pursuer's control strategy more complicated. In order to develop control strategies for pursuers, Liu et al. [19] proposed a distributed online mission plan algorithm for pursuers to access targets. However, these works on the orbital pursuit-evasion-defense game adopted the impulsive thrust, which suffers the drawback that the interception will fail when the target can perform evasive maneuvers [4].Compared with the impulse thrust, the continuous low thrust allows players to perform multiple, continuous maneuvers, which meets the requirements of the frequently orbital transfers in the game. When applying the continuous low thrust, the hypothesis about players' maneuverable is removed. It is closer to the actual situation of the orbital pursuit-evasion-defense game. Therefore, in this paper, the orbital pursuit-evasion-defense game model is constructed based on the continuous low thrust. Different from the model based on impulse thrust, the model based on continuous low thrust cannot adopt the Keplerian dynamics [20]. Its dynamic equations are based on the non-Keplerian motion. T...

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Optimal Pursuit/Evasion Spacecraft Trajectories in the Hill Reference Frame

Cited by 32 publications

References 9 publications

Optimization Of Spacecraft Pursuit-Evasion Game Trajectories In The Euler-Hill Reference Frame

Optimization Of Spacecraft Pursuit-Evasion Game Trajectories In The Euler-Hill Reference Frame

Revisiting the two-side optimization problem in satellite pursuit-evasion

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

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