高超声速飞行器非连续点火助推增程弹道设计  

Trajectory design of improving range for hypersonic vehicle based on discontinuous booster

作　　者：鲜勇 郭玮林 张大巧 雷刚 李少朋 

机构地区：[1]火箭军工程大学,西安710025

出　　处：《固体火箭技术》2017年第3期397-402,共6页Journal of Solid Rocket Technology

摘　　要：针对高超声速飞行器因防热烧蚀而制约整体射程的问题,创新提出了一种非连续点火助推方案,通过增大助推段射程的弹道设计方法提高飞行器整体射程能力,减轻后续段的射程压力。综合考虑动压、过载、控制和终端高度、速度、弹道倾角等约束条件,以助推段射程最大为目标函数,设计了非连续点火助推段飞行程序和纵向平面弹道优化模型,采用改进的梯度粒子群算法进行优化求解。仿真结果表明,改进的梯度粒子群算法能有效解决非连续点火助推弹道设计问题,设计的非连续点火助推弹道方案在满足各项约束的同时,助推段射程比连续点火方案提高了8.7倍,射程达到了4 800 km,增程的效果十分明显。A novel discontinuous ignition booster method has been proposed in the present work to solve the restriction issues of the whole range,which are caused by the thermal ablation of the hypersonic vehicles.The controlling stress of the gliding range has been alleviated via an increase of the boost phase range.Setting the multi-parameters ,such as dynamic pressure ,overloads, control- ling and terminal height, speed, and trajectory angles as the constraint conditions, and regarding the maximum distance of boost phase as the objective function, the flight program designs of the vehicles, as well as the optimization model of vertical plane trajec- tory have been established. Comparisons of the simulated results with the experimental ones demonstrated that the improved grads particle swarm optimization algorithm（IGPSO） can be efficiently applied to solve the discontinuous booster trajectory project with all the constraint conditions fulfilled,and the boost phase range of the discontinuous booster case has been improved by 8.7 times com- pared to that of the continuous with a range of 4 800 km.The results demonstrated a conspicuous improving effect.

关 键 词：非连续点火 助推段射程 改进的梯度粒子群算法 弹道优化 

分 类 号：V412.1[航空宇航科学与技术—航空宇航推进理论与工程]