基于全驱系统理论的航天器姿轨预设性能控制

doi:10.7527/S1000-6893.2023.28313

Abstract

Abstract:

An attitude-orbit integrated controller with prescribed performance based on fully actuated system parameterization approach and adaptive neural network is proposed for close flying-around of the space target in the presence of inertia parameter uncertainty and orbit perturbation. The six degree of freedom motion of rigid spacecraft is derived under the framework of Lie group SE（3）， and an accurate and concise attitude-orbit integrated error dynamic model is established. An exponential-form based performance function is introduced to perform prior and quantitative constraints on the dynamic and stable processes of attitude error and position error. Considering the nonlinear characteristics of the dynamic model， a feedback control term based on the fully actuated system approach is designed to obtain a constant linear closed-loop system with an arbitrarily assignable eigenstructure， thus reducing the difficulty of the subsequent controller design process. An adaptive neural network based integral sliding mode controller is further designed to compensate for the loss of control accuracy caused by inertia parameter uncertainty and orbit perturbation. In addition， to further enhance the engineering utility， an improved particle swarm optimization algorithm is developed to optimize the controller parameters. Numerical simulation results indicate that the high-precision attitude-orbit integrated flying-around is achieved without significant control chatter while satisfying the predesigned performance constraints， thus verifying the effectiveness and feasibility of the proposed controller.

Key words: fully actuated system approach, Lie group SE(3), spacecraft attitude-orbit integrated control, prescribed performance control, improved particle swarm optimization

CLC Number:

V448.2

Ming LIU, Ruichao FAN, Shi QIU, Xibin CAO. Spacecraft attitude-orbit prescribed performance control based on fully actuated system approach[J]. Acta Aeronautica et Astronautica Sinica, 2024, 45(1): 628313-628313.

Figures/Tables 16

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对比项	优化前	优化后
收敛时间/s	334.4	258.8
控制精度	5×10^-6 rad，10×10^-3 m	5×10^-6 rad， 6×10^-5 m
控制器抖振	剧烈抖振	无明显抖振现象
适应度函数g₁	400	400
适应度函数g₂	189.15	424.46

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Spacecraft attitude-orbit prescribed performance control based on fully actuated system approach

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