考虑攻击角约束和输入饱和的制导控制一体化设计

针对攻击角度约束和执行机构因物理约束导致控制输入饱和的问题,提出了一种带攻击角度约束和输入饱和的制导控制一体化设计方法。建立了带攻击角度约束的制导控制一体化三通道独立设计模型,采用扩张状态观测器估计和补偿模型误差和通道间的耦合关系。在此基础上,采用终端滑模控制和反演控制,对制导控制系统进行一体化设计,并引入Nussbaum函数和一个辅助系统处理输入饱和问题。通过导弹六自由度仿真验证了所提制导控制一体化算法的有效性,制导精度和角度约束精度比现有制导控制一体化算法更高,且制导控制效果更好。

Design on Integrated Guidance and Control Considering the Constraint of Impact Angle and Input Saturation

Aiming at the problem of impact angle constraint and the control input saturation caused by the physical constraint of the actuator,an integrated guidance and control design method with impact angle constraint and input saturation was proposed. An integrated three-channel independent design model of the guidance and control system with impact angle constraint was established,and an extended state observer was used to estimate and compensate the model error and the coupling relationship between channels. On this basis,the terminal sliding mode control and backstepping control were used to design the integrated guidance and control system,and the Nussbaum function and an auxiliary system were introduced to deal with the input saturation problem. The six-degree-of-freedom simulation of the missile was carried out to verify the effectiveness of the proposed integrated guidance and control algorithm. Compared with the existing integrated guidance and control algorithms,the guidance accuracy and angle constraint accuracy are higher,and the guidance and control effect is better.