冲压发动机导弹爬升轨迹与推力调节规律优化  

Integrated optimum design for ramjet missile climb trajectory and thrust regulation

作　　者：尚腾[1] 谷良贤[1] 赵吉松[1] 龚春林[1] 

机构地区：[1]西北工业大学航天学院,陕西西安710072

出　　处：《飞行力学》2012年第3期280-283,288,共5页Flight Dynamics

基　　金：武器装备预研基金资助(9140A20100111HK03)

摘　　要：针对以冲压发动机为动力的导弹爬升问题,建立了飞行轨迹和推力规律一体化优化设计模型。采用基于三次样条的直接离散方法,将弹道优化问题转化为参数优化问题,选取兼顾全局搜索能力和局部搜索精度的粒子群-变尺度法(PSO-BFGS)串联混合算法求解最省燃料爬升弹道,得到了"先减速再加速"爬升方案。相比传统的采用最大推力规律、仅优化爬升轨迹的爬升方案,一体化设计能充分发挥冲压发动机的推力调节能力,使导弹以较小的平均飞行速度完成爬升过程,可以显著节省燃耗,提高导弹的性能。For the climb trajectory of a ramjet-powered missile,a trajectory/propulsion integrated design model was established,and was converted into a parameter optimization problem by using a cubic spline-based parameterization method.A series hybrid algorithm PSO-BFGS algorithm with both the global search ability and local search precision was put forward,to solve the optimal climb trajectory of least fuel consumption,and a first slow down and then speed up climbing scheme was achieved.Compared to traditional maximum thrust climbing scheme,in which only the flight path was optimized,the climbing scheme achieved from integrated optimum design in this paper,was able to give full play to the thrust regulation ability of ramjets,and can make missiles finish the climbing with a smaller average flight speed.Significant saving of fuel consumption can be got and missile performance can be improved.

关 键 词：冲压发动机导弹 爬升弹道 三次样条 粒子群-变尺度法 

分 类 号：TJ761.6[兵器科学与技术—武器系统与运用工程]