论文部分内容阅读
针对高超声速导弹无热流约束弹道的热流率过大问题,用动态逆和奇异摄动方法推导了一种最大末端能量近最优中制导律。根据变量的时间尺度,将导弹质点动力学模型分成三层,对降阶系统用最小值原理计算出降阶最优高度。在第一边界层和第二边界层分别使用动态逆方法设计出闭环控制器,使导弹沿降阶最优高度飞行。数值仿真结果表明,该制导律可将导弹导引至目标附近,并为末段拦截保存能量。该制导律使导弹沿降阶最优高度飞行,形成了平滑弹道,使最大热流率显著降低,符合工程应用要求。
Aiming at the problem of hyperthermal missile missiles with large heat flow rate, a method of dynamic inversion and singular perturbation is used to derive a maximum end-energy near-optimal guidance law. According to the time scale of the variables, the missile particle dynamics model is divided into three layers, and the reduced order optimal height is calculated by using the minimum principle for the reduced order system. In the first boundary layer and the second boundary layer, a dynamic inverse method is used to design the closed-loop controller so that the missile can fly along the optimal height of the reduced order. The numerical simulation results show that the guidance law can guide the missile near the target and save the energy for the final interception. The guidance law makes the missile fly along the optimal height of the reduced order, forming a smooth trajectory, the maximum heat flow rate significantly reduced, in line with engineering requirements.