Attitude Control Considering Variable Input Saturation Limit for a Spacecraft Equipped with Flywheels

查看全文 作　　者：TIAN [1]Lin;XU [1]Shijie

机构地区：[1]School of Astronautics Beihang University,Beijing 100191,China

出　　处：《Chinese Journal of Aeronautics》索引2012年第25卷第3期,共9页

基　　金：National Natural Science Foundation of China(10902003) 摘　　要：A new attitude controller is proposed for spacecraft whose actuator has variable input saturation limit. There are three identical flywheels orthogonally mounted on board. Each rotor is driven by a brushless DC motor (BLDCM). Models of spacecraft attitude dynamics and flywheel rotor driving motor electromechanics are discussed in detail. The controller design is similar to saturation limit linear assignment. An auxiliary parameter and a boundary coefficient are imported into the controller to guarantee system stability and improve control performance. A time-varying and state-dependent flywheel output torque saturation limit model is established. Stability of the closed-loop control system and asymptotic convergence of system states are proved via Lyapunov methods and LaSalle invariance principle. Boundedness of the auxiliary parameter ensures that the control objective can be achieved, while the boundary parameter's value makes a balance between system control performance and flywheel utilization efficiency. Compared with existing controllers, the newly developed controller with variable torque saturation limit can bring smoother control and faster system response. Numerical simulations validate the effectiveness of the controller. 关键词：姿态控制器输入饱和飞轮转子航天器极限 LaSalle不变原理闭环控制系统 LYAPUNOV方法

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Attitude Control Considering Variable Input Saturation Limit for a Spacecraft Equipped with Flywheels

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