基于正交实验与牛顿方法的滑翔导弹助推弹道设计  

Boost Trajectory Design of Boost-Glide Missile Based on Orthogonal Experimental Design and Newton's Iterative Method

作　　者：刘开封 陈颖[2] 何念念[2] 蒋斌[2] 梁立威[2] 

机构地区：[1]第二炮兵工程大学906教研室,西安710025 [2]第二炮兵装备研究院,北京100085

出　　处：《导弹与航天运载技术》2014年第4期50-53,75,共5页Missiles and Space Vehicles

摘　　要：分析了助推-滑翔导弹助推段关机参数要求,并基于牛顿迭代法和正交实验设计求解了助推弹道。牛顿迭代法局部搜索效率高,但易陷入局部最优,为避免初值设置不当导致无法求取可行解,分析了各控制变量的取值范围,并对其划分水平设计正交实验,从每一个正交实验点开始搜索,避免陷入局部最优。仿真结果表明,该方法能够快速求解出满足约束要求的助推弹道。In this paper, the requirements of boost-glide missile during boost phase were analyzed and the boost trajectory was gained based on Newton＇s iterative method and orthogonal experimental design. Newton＇s iterative method has a high efficiency in local search, but it is sensitive to initial value and easy to fall into local minimum. In this paper, the scope of the control variables was analyzed and the orthogonal experiment was designed by dividing control variables into several levels. The optimal value was searched from each experimental point to guarantee a feasible solution. The simulation result shows that the boost trajectory with constraints could be gained quickly by this method.

关 键 词：助推-滑翔导弹 助推弹道设计 牛顿迭代法 正交实验设计 

分 类 号：V448.1[航空宇航科学与技术—飞行器设计]