助推-滑翔导弹弹道优化与总体参数分析  

Trajectory Optimization and Parameter Analysis for Boost-Glide Missile

作　　者：刘欣[1] 杨涛[1] 张青斌[1] 

机构地区：[1]国防科学技术大学航天与材料工程学院,长沙410073

出　　处：《弹道学报》2012年第3期43-48,共6页Journal of Ballistics

摘　　要：为解决助推-滑翔导弹的弹道设计与性能分析问题,提出了一种分段优化的全弹道设计方法.利用工程估算方法估算导弹的助推器参数,建立了弹道优化模型,将全弹道分为主动段和滑翔弹头飞行段,分段进行弹道优化.采用Gauss伪谱法将弹道优化问题转化为非线性规划问题,采用序列二次规划(SQP)等数值方法进行求解.仿真结果表明,Gauss伪谱法处理此类多阶段多约束的弹道优化问题效果较好,最优弹道起伏较小,控制量变化平滑,各项约束都得到满足.利用弹道优化分析了起飞质量、主动段终端倾角对导弹射程的影响,并与弹道导弹进行了比较,结果表明,助推-滑翔导弹在增程方面具有较大优势.To analyze the performance of boost-glide missile,a trajectory design method that boost phase and glide phase were optimized separately was proposed. A method for quickly evaluating booster parameter was given. The optimization model for boost-glide trajectory was presented, and the whole trajectory was devided into boost phase and glide phase. By Gauss pseudospectral method（GPM）, the trajectory design problem was transformed to the nonlinear programming （NLP）problem,and the sequential quadratic programming（SQP）method was used to solve the NLP problem. Simulation results show that the method is effective,the fluctuation of the optimal trajectory is small, the controlled parameter changes smoothly, and all the constraints can be satisfied. Based on trajectory optimization, the influence of takeoff mass and burnout velocity angle on range were analyzed and compared with ballistic missile. The results show that the boost-glide trajectory has an advantage over the ballistic trajectory in range.

关 键 词：助推-滑翔导弹 弹道优化 GAUSS伪谱法 

分 类 号：V412.4[航空宇航科学与技术—航空宇航推进理论与工程]