基于拟连续高阶滑模的高超声速飞行器再入姿态控制

Reentry attitude control for hypersonic vehicle based on quasi-continuous high order sliding mode

中文关键词  高超声速飞行器  再入姿态控制  拟连续高阶滑模  虚拟控制  制导控制一体化

英文关键词  hypersonic vehicle  reentry attitude control  quasi-continuous high order sliding mode  virtual control  integrated guidance and control

中文摘要

      考虑模型参数不确定和外界干扰对再入制导控制性能的影响, 基于拟连续高阶滑模控制策略对高超声速 飞行器的再入制导控制问题进行了研究. 首先, 给出再入制导指令的设计过程. 其次, 基于再入飞行特性对模型进 行简化, 获得面向控制的姿态模型, 在此基础上, 通过引入新的控制变量, 设计解耦滑模面, 实现姿态间的解耦. 再 次, 为了削弱控制抖振, 通过引入虚拟控制, 对系统进行增广, 基于齐次性理论设计拟连续三阶滑模再入姿态控制 器, 确保系统在有限时间实现对制导指令的稳定跟踪. 最后, 六自由度再入飞行器的制导控制一体化仿真结果表明, 本研究给出的控制策略在不影响系统鲁棒性的同时, 能够实现对标称轨迹和再入姿态的综合控制.

英文摘要

      Considering the influence of model parameter uncertainties and external disturbance on the reentry guidance and control, we investigate the guidance and control problem for reentry hypersonic vehicles based on the quasi-continuous high-order sliding mode control strategy. Firstly, the design process of reentry guidance command is introduced. Secondly, the control-oriented attitude model is developed via model reduction based on reentry flight characteristics. On this basis, sliding mode surfaces are designed by introducing new control variables, and then the decoupling for each attitude channel is achieved. Thirdly, in order to reduce the control chattering, the virtual-control is introduced to augment the system, and then a third-order quasi-continuous sliding mode reentry attitude controller is designed based on homogeneity theory which ensures that the system to be able to track the guidance command in finite time. Finally, the integrated guidance and control with six-degrees-of-freedom simulation results demonstrate that the developed control of the nominal trajectory and reentry attitude can be achieved based on the proposed control strategy without the loss of robustness.