高超声速飞行器俯冲机动最优制导方法  

Optimal guidance with maneuver for hypersonic vehicle in dive phase

作　　者：朱建文[1] 刘鲁华[1] 汤国建[1] 包为民[2] 

机构地区：[1]国防科技大学航天科学与工程学院,湖南长沙410073 [2]中国航天科技集团公司,北京100048

出　　处：《国防科技大学学报》2013年第6期25-30,共6页Journal of National University of Defense Technology

基　　金：国家自然科学基金资助项目(61104200)

摘　　要：为解决高超声速飞行器俯冲段精确制导与机动突防问题,研究了机动突防最优制导方法。针对零化视线角速率降低突防性能的问题,在俯冲平面及转弯平面内分别设计了正弦形式的视线角参考运动,同时为进一步实现俯冲精确制导,以落速最大为性能指标,利用最优控制对其进行跟踪,引入了伪控制量,以简化最优制导问题的求解,最后分析了该方法的稳定性及制导性能。以CAV-H为例进行仿真分析,仿真结果表明,该方法能够实现机动飞行,且能够高精度地满足终端落角及落点约束,可为高超声速飞行器俯冲段精确制导及机动突防提供参考。To solve precise guidance and maneuver penetration problems for hypersonic vehicle in dive phase, the optimal guidance method with maneuver was proposed. Considering that the traditional guidance law based on zero-LOS angle rate can debase penetrative ability, it designed reference motion for the rate in diving-plane and turning-plane. Besides, in order to enhance penetrative ability farther and realize precise guidance, it took advantage of optimal control with the optimal index of maximum terminal velocity to track the LOS angle rate, and pseudo control variable was introduced to simplify the resolution of optimal control problem. Finally, it analyzed the guidance capability and stability of this method. The results of CAV-H vehicle test show that the algorithm can realize maneuvering flight, and can satisfy terminal impact point and falling angle constraints. Therefore, the method can offer reference for high precision guidance and maneuver penetration for hypersonic vehicle in dive phase.

关 键 词：高超声速飞行器 俯冲段 最优制导 机动突防 

分 类 号：V448.235[航空宇航科学与技术—飞行器设计]