高超声速导弹近最优中制导律  

Near-optimal midcourse guidance law for hypersonic missile

作　　者：乔清青[1] 陈万春[1] 

机构地区：[1]北京航空航天大学宇航学院,北京100191

出　　处：《飞行力学》2014年第1期48-52,共5页Flight Dynamics

摘　　要：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。In view of the problem that unrestraint maximum range glide for hypersonic missile have too large heating rate, a near-optimal mideourse guidance law is developed with dynamic inversion and singu- lar perturbation method. Missile＇ s mass point dynamic model is separated into 3 layers according to vari- ables＇ time scale. In reduced order system, the minimum principal is used to obtain the reduced order optimal height. Dynamic inversion technique is employed in the first boundary layer and the second boundary layer. A close-loop controller is designed to follow the reduced order optimal height. The results obtained from numerical simulation show that, the guidance law can guide the missile to fly to the place near the target and conserve energy for terminal interception. This guidance law also guides the missile to fly along the degraded optimal altitude. The trajectory is smooth, thus the maximum heating rate is de- creased significantly.

关 键 词：中制导 摄动理论 反馈线性化 热流率 

分 类 号：V448.13[航空宇航科学与技术—飞行器设计]