变质心控制高速滑翔弹动力学与控制律研究

Study on Dynamics and Control Law for High-speed Glide Missile Controlled by Variable-centroid

为研究变质心控制高速滑翔弹在下滑弹道上的动力学建模与弹道跟踪控制问题,基于Lagrange分析力学建立了滑翔弹在下滑纵向平面上的动力学方程,并将其转化为标准状态方程.在标准下滑弹道的某配平点上作小扰动线性化,然后根据LQR理论设计了飞行控制律.控制律通过沿弹头纵轴移动的滑块实现,可避免空气舵在高速飞行条件下的气动热烧蚀等问题.数值仿真表明,滑块具有强大的控制能力,只需在较小范围内移动即可有效控制弹头精准跟踪标准下滑弹道,验证了本文方法的有效性和可行性.

To study the dynamic modeling and trajectory tracking controller of high-speed glide missile（HSGM） controlled by variable-centroid at glide stage,Lagrange analytical mechanics was used to establish the dynamic model of glide missile on longitudinal glide plane, and the model was converted to standard state equations. The small disturbance linearization was carried out aiming at a trim point on the glide trajectory, and the flight controller was designed based on linear quadratic regulator theory. The designed control law was implemented by a slider moving along the longitudinal axis of the warhead,and the problems such as aerothermal ablation caused by the aerodynamic rudder under high speed flight were avoided. Numerical simulation result shows the powerful control capability of slider. Glide missile can accurately track the standard trajectory by the control of slider, which moves within a small range. The variable-centroid control method is efficient and feasible.