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针对传统制导与控制系统分开设计在拦截高速机动目标时的缺陷,提出一种高阶滑模制导控制一体化方法。综合考虑弹目拦截几何与导弹动态,根据零化视线(LOS)角速率的准则,将导弹制导控制问题转化为一个三阶积分链系统的镇定问题。基于几何齐次理论设计了标称系统的全局有限时间镇定控制律,同时针对目标机动和导弹气动参数摄动等带来的不确定性,利用超扭曲算法(STA)设计了补偿控制律。仿真结果表明,与传统制导与控制系统分开设计相比,本文所提出的鲁棒高阶滑模制导控制一体化方法具有更小的脱靶量,且导弹姿态和控制舵偏角的变化更加平缓。
Aiming at the defect that the traditional guidance and control system is separately designed to intercept high-speed maneuvering targets, a high-order sliding mode guidance integrated control method is proposed. Considering the projectile interception geometry and the missile dynamics, the missile guidance control problem is transformed into the stabilization problem of a third-order integrator chain system according to the zero-line-of-sight (LOS) angular rate criterion. Based on the theory of geometric homogeneity, the global finite-time stabilization law of the nominal system is designed. At the same time, aiming at the uncertainties of target maneuvering and missile aerodynamic parameters perturbation, the compensation control law is designed by the super-warping algorithm (STA). The simulation results show that compared with the traditional guidance and control system, the integrated sliding mode guidance control method proposed in this paper has a smaller miss distance, and the missile attitude and control steering angle changes more smoothly.