轨道快速机动期间的姿态鲁棒稳定控制方法研究

Robust Attitude Control of Flexible Liquid Spacecraft under Fast Orbit Transfer

根据挠性充液航天器刚液柔强耦合、变参数及模型不确定的特点,研究了一种神经网络输出变结构控制算法。根据该算法提出了轨道快速机动下的姿态控制方案,设计了控制系统并对干扰力矩、模型不确定性等工况进行了仿真。仿真结果表明在发动机干扰力矩和模型不确定情况下,系统能够快速稳定到要求的精度。所设计的系统具有较强的鲁棒性,能够抑制挠性附件振动和液体晃动的影响。

Flexible liquid spacecraft is a rigid-liquid-flexible couple vehicle with variable parameters and model uncertainty. Investigated a neural network output variable structure control algorithm and applied it to the attitude control of spacecraft under orbit fast transfer. And then the control system was simulated for the perturbation torque and model uncertainty. Simulation results indicate that the spacecraft can arrive at the required attitude state quickly with good stability and high accuracy. The controller is robust and can stabilize the vibration of flexible appendix and fuel.