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针对超声速飞行器末飞行段攻击地面移动目标问题,提出一种带落角约束的制导控制一体化设计方法。联立目标-飞行器三维相对运动方程和飞行器控制系统非线性模型,基于不确定项有界假设建立具有严格反馈形式的制导控制一体化设计模型,将制导控制一体化设计问题转化为高阶非线性时变系统输出调节问题。构建视线角速率动态面向量并利用高频率反馈鲁棒控制方法得到控制系统的虚拟控制量,进而利用块动态面控制方法得到带落角约束的一体化制导控制律。以动态面和滤波误差为基础构建李雅普诺夫函数并证明各动态面和滤波误差的一致有界性。仿真结果表明,该一体化方法能保证飞行器以期望落角精确命中地面移动目标,且飞行器全部状态变量均有界稳定。
In order to solve the problem of ground moving target in the final flight stage of supersonic vehicle, an integrated design method of guidance control with cornering restraint is proposed. The joint goal - the three-dimensional relative motion equation of the aircraft and the nonlinear model of the aircraft control system, an integrated design guidance control system with strict feedback is established based on the bounded assumption of uncertainties, and the integrated guidance design problem is transformed into higher order nonlinearity Time-varying system output adjustment problem. The visual vector of line-of-sight angular rate is constructed and the high-frequency feedback robust control method is used to obtain the virtual control volume of the control system. Then, the integrated guidance control law with the corner-angle constraint is obtained by using block dynamic surface control. The Lyapunov function is constructed on the basis of dynamic surface and filtering error and the uniform boundedness of dynamic surface and filtering error is proved. The simulation results show that the integrated method can ensure that the aircraft accurately hits the ground moving target with the expected arrival angle, and that all the state variables of the aircraft have a bounded stable boundary condition.