导弹俯冲段弹道分析与最优设计  

Analysis and Optimum Design of the Dive Trajectory for a Cruise Missile

作　　者：李响[1] 柳长安[2] 

机构地区：[1]北京理工大学机电工程学院,北京100081 [2]陕西动力机械设计研究所,陕西西安710100

出　　处：《北京理工大学学报》2006年第9期773-776,共4页Transactions of Beijing Institute of Technology

基　　金：国家自然科学基金资助项目(0105377)

摘　　要：分析了导弹俯冲段的飞行任务,并建立了相应的弹道优化设计数学模型.该模型要求俯冲段末的实际飞行参数与突防段的参数差距最小,同时满足过载与发动机性能约束.采用遗传算法进行弹道优化计算,同时为了简化遗传算法中的编码方法,提高编码效率,引入非均匀有理B样条(NURBS)曲线进行控制律的描述.优化后弹道使导弹以一种最优方式实现从中、高空的水平飞行状态转换到低空的突防飞行状态.利用该方法对某仿真算例进行了优化计算,并对计算结果进行了物理分析,表明了本方法的有效性.An optimum design of the dive trajectory for a cruise missile is presented. The dive process is analyzed, based on which the optimization problem is modeled as the minimization of discrepancy between the required parameters of penetration and the parameters at the end of the dive maneuver subjected to the overload and engine performance constraints. Genetic algorithm is applied to solve this optimization problem. To reduce the amount of computation, non-uniform rational B-spline （NRUBS） curve is utilized to represent the complex laws of flight control. A simulation example is provided in the last section and its results are analyzed in detail.

关 键 词：俯冲段 优化 遗传算法 

分 类 号：V211.21[航空宇航科学与技术—航空宇航推进理论与工程]