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针对吸气式导弹级间分离控制存在模型参数突变和强分离干扰等不确定性问题,提出了一种快速非奇异终端滑模变结构控制方案。采用动态逆方法将分离控制数学模型输入/输出线性化,然后对线性化模型设计了快速非奇异终端滑模控制器,并采用蚁群优化算法对控制器参数进行优化。对正常分离条件和异常分离条件下控制器的性能进行了仿真验证,结果表明二级导弹姿态角和角速度分别在0.5s,1s内收敛至期望状态,同时舵面无抖振现象。
In order to solve the uncertainties such as sudden change of model parameters and strong separation disturbance, a kind of fast non-singular terminal sliding mode variable structure control scheme is proposed. The dynamic inverse method is used to linearize the input / output of the separation control mathematical model. Then a fast non-singular terminal sliding mode controller is designed for the linearized model. The ant colony optimization algorithm is used to optimize the controller parameters. The performance of the controller under normal and abnormal separation conditions is verified by simulation. The results show that the attitude and angular velocity of the second-stage missile converge to the desired state in 0.5s and 1s respectively, and there is no chattering on the control surface.