基于非连续点火的变射面空间“M”形弹道设计及优化  

Design and optimization of changeable launching plane‘M'maneuvering trajectory based on discontinuous ignition

作　　者：刘炳琪[1] 鲜勇[1] 李振华[1] 王继平 苏国华 

机构地区：[1]第二炮兵工程大学,西安710025 [2]二炮装备研究院,北京100096

出　　处：《固体火箭技术》2015年第5期608-613,共6页Journal of Solid Rocket Technology

基　　金：国家自然科学基金(61304231)

摘　　要：为有效提高导弹的突防能力和禁避飞区规避能力,提出在一级段偏离传统射面,后面级再修正射面以命中目标的变射面空间"M"形弹道。设计了基于级间非连续点火的导弹纵横向适应性飞行程序模型,并采用免疫粒子群与内点牛顿相结合的串联混合优化算法对弹道进行了优化。仿真结果表明,提出的变射面弹道能有效增大主动段飞行时间,压缩被动段射程,提高导弹的中段机动能力。优化算法收敛速度快,精度高。In order to improve the capability of avoiding no-fly zone and penetration,a changeable launching plane‘M＇maneuvering trajectory is proposed. The first-stage of missile is deviated from traditional launching plane and then the launching plane is changed in the following stage to hit the target. The longitudinal and transversal adaptability flight program model is designed and optimized through the proposed series hybrid optimizing algorithm which combines immune particle swarm optimization with interiorpoint Newton method. The simulation results show that the proposed changeable launching plane can improve the missile midcourse maneuverability availably by increasing boost phase flying time and cutting down the unpowered phase range. The optimizing algorithm has fast convergence speed and high convergence precision.

关 键 词：变射面 弹道设计 免疫粒子群算法 内点牛顿法 

分 类 号：V448[航空宇航科学与技术—飞行器设计]