基于ESO的可重复使用飞行器积分滑模控制器设计

考虑参数不确定和外界干扰对姿态控制的影响，开展基于扩张状态观测器(ESO,extended states observer)的可重复使用飞行器姿态控制研究.首先，对飞行器运动模型进行描述，在合理假设条件下，得到面向控制器设计的纵向和横侧向姿态模型；其次，分别针对纵向和横侧向姿态模型设计积分滑模控制器(ISMC,integral sliding mode control)；然后，引入ESO对耦合作用、参数不确定及外界干扰进行估计，并在控制器中进行补偿；最后，六自由度仿真结果表明，本研究给出的控制策略能够实现对给定制导指令的稳定跟踪，确保安全再入飞行.

SO Based Integral Sliding Mode Control Design for Reusable Launch Vehicle

Considering the effects of parametric uncertainties and external disturbances on reentry phase, an attitude controller for reusable launch vehicle (RLV) is developed. Firstly, the dynamic model is described. Longitudinal and lateral attitude dynamic models are obtained for controller design under some proper assumptions. Secondly, integral sliding mode controllers (ISMCs) are designed for both of longitudinal and lateral model. Thirdly, coupling effects, parametric uncertainties and external disturbances are estimated by introducing the extended states observer (ESO), which can be compensated in the controller. At last, numerical simulation for the six degree of freedom reusable launch vehicle is conducted. Results demonstrate that the proposed controller can track the guidance command steadily and accurately, which guarantee a safe reentry flight.