助推-滑翔导弹弹道优化研究  

A Study of Optimal Trajectory for Boost-glide Missile

作　　者：李瑜[1] 杨志红[2] 崔乃刚[1] 

机构地区：[1]哈尔滨工业大学航天学院,哈尔滨150001 [2]北京机电工程研究所,北京100074

出　　处：《宇航学报》2008年第1期66-71,共6页Journal of Astronautics

基　　金：2003年航天创新基金(0316)

摘　　要：针对助推-滑翔导弹的弹道优化问题,给出了一种求解其最大射程弹道的分段优化方法,建立了其纵平面运动模型和弹道优化模型。在考虑攻角绝对值、攻角变化率、法向过载、分离点攻角衔接及落地条件等约束下,应用序列二次规划法求解了其最大射程弹道。分析表明,助推-滑翔导弹比传统弹道导弹射程显著提高,其最优弹道的起伏有助于增大射程和提高突防能力。Boost-glide missile is associated with a kind of unique trajectory.A method that boost phase and glide phase were optimized separately,was proposed which optimized the range of boost-glide missile.The equations of motion and optimization model for the boost-glide trajectory were presented.The sequential quadratic programming algorithm was used to solved the optimization problem.The maximum range of the boost-glide missile with the constraints of change rate and absolute value for angle-of-attack,the constra...

关 键 词：助推-滑翔 导弹 弹道优化 最优控制 序列二次规划 

分 类 号：TJ013[兵器科学与技术—兵器发射理论与技术]