大型柔性卫星平台的变结构姿态控制

首先利用拉各朗日方程建立了大型柔性卫星的动力学方程，对该动力学方程进行了线性化，并且为了以后设计变结构控制器的需要，设计了状态观测器，然后设计了变结构控制器．在设计过程中，充分考虑了实际工程要求，采用了边界层方法来削弱变结构控制器的抖振，同时考虑了执行机构控制输出受限的情况，采取了利用4个偏置动量轮系统组成三轴零动量飞轮系统对卫星平台进行姿态控制．最后通过数学仿真证明了所设计的控制器的有效性．

Variable structure attitude control of a large flexible satellite platform

The problem of variable structure attitude stabilization control for a large flexible satellite is investigated. Firstly, the dynamic model of the satellite is established using the Lagrange Equation, the linearization of the dynamic model is done, and the state observer is designed for the design of the variable structure controller. Then the variable structure controller is designed. In the process of designing variable structure controller , the requirements of the engineering are considered, and the boundary layer method is used to weaken the chattering of the variable structure controller. The limitation of the actuator output is considered at the same time. The zeros momentum wheel system constituted by four bias momentum wheels is used as the actuator in the attitude control system. Finally, the mathematical simulation is conducted to demonstrate the validity of the variable structure controller.