带落角约束的超声速飞行器制导控制一体化设计

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。

Integrated guidance and control design for supersonic vehicles with impact angle constraint

According to the requirements of the supersonic vehicle which attacks the maneuver target with specified impact angle, an integrated guidance and control(IGC)scheme considering impact angle constraint is proposed.An intact IGC design model with the strict feedback form was formulated by combining the three dimensional(3D)relative dynamics and nonlinear rotational dynamics of the supersonic vehicle under the assumption that the uncertainties in the IGC design model are bounded, and the IGC design problem was converted into an output tuning problem.The pseudo-inputs with respect to rotational loop of the vehicle were obtained based on the block dynamic surface vector composed of elevation and azimuth angle rates of the line-of-sight(LOS),and the commanded control surface fin deflections were derived with the help of block dynamic surface control approach.Finally, the states of the closed-loop system and the filter errors were proved to be with uniform ultimate boundedness based on the Lyapunov stability theory.Numerical simulation results show that the proposed IGC scheme can ensure an accuracy interception with desirable impact angle and the state varidbles of the supersonic vehicle are all bounded and stable.