固体火箭技术2015，Vol.38Issue(5)：608-613,6.DOI:10.7673/j.issn.1006-2793.2015.05.002
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
摘要
Abstract
In order to improve the capability of avoiding no-fly zone and penetration,a changeable launching plane'M' maneu-vering 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 op-timized through the proposed series hybrid optimizing algorithm which combines immune particle swarm optimization with interior-point 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 algo-rithm 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Key words
changeable launching plane/trajectory design/immune particle swarm optimization/interior-point newton method分类
航空航天引用本文复制引用
刘炳琪,鲜勇,李振华,王继平,苏国华..基于非连续点火的变射面空间"M"形弹道设计及优化[J].固体火箭技术,2015,38(5):608-613,6.基金项目
国家自然科学基金( 61304231). （ 61304231）
