洲际助推-滑翔导弹全程突防弹道优化  

Optimization of overall penetration trajectory for intercontinental 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：《固体火箭技术》2010年第2期125-130,共6页Journal of Solid Rocket Technology

摘　　要：分析了考虑路径点、勿入区域、天基激光武器与拦截导弹杀伤区等实际问题的洲际助推-滑翔导弹全程突防弹道,给出了弹道分段准则。建立了三自由度运动模型、推力模型、气动模型与气动热模型。针对其弹道优化问题,在同时考虑级间分离、跨声速区、控制、动压、法向过载、热率、壁温、路径点、勿入区域、天基激光武器与拦截导弹杀伤区内机动等约束条件下,建立了全程突防弹道的多约束多阶段弹道优化模型。利用直接打靶法,将此最优控制模型转化为非线性规划问题,并采用序列二次规划算法进行解算。结果表明,文中研究方法适合于解决洲际助推-滑翔导弹全程突防弹道优化问题,所得最优弹道更有利于满足实际作战需求。In considering waypoints,no-fly zones,kill zones of space-based laser weapon and intercept missile,and so on,the overall penetration trajectory for intercontinental boost-glide missile was analyzed.To benefit optimization,the trajectory is divided into four phases by fight states.The dynamics,propulsion,aerodynamics,and aerothermodynamics models are described.With the constraints of stage separation,transonic phase,control,dy-namic pressure,normal overload,heating rate and wall temperature at stagnation point,waypoints,no-fly zones,ma-neuver in kill zones of space-based laser weapon and intercept missile,the optimization model of overall penetration trajectory was established,i.e.multi-constraints multi-phase trajectory optimization model.By using direct shooting method,the associated optimization was converted into a nonlinear programming problem,which was solved through a sequential quadratic programming solver.The numerical results show that the proposed method can effi-ciently solve the optimization problem of overall penetration trajectory with the given constraints,and the trajectory accords with the actual warfare.

关 键 词：洲际助推-滑翔导弹 突防弹道 弹道优化 多约束多阶段优化 非线性规划 

分 类 号：V412[航空宇航科学与技术—航空宇航推进理论与工程]