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

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.