冲压发动机为动力导弹爬升弹道优化  

Optimization Research on Climb Trajectory for a Ramjet Powered Missile

作　　者：王华[1] 杨存富[1] 刘恒军[1] 

机构地区：[1]航天科工集团二院,北京100854

出　　处：《弹箭与制导学报》2008年第3期185-188,共4页Journal of Projectiles,Rockets,Missiles and Guidance

摘　　要：针对以冲压发动机为动力的战术导弹的爬升弹道优化,建立了优化问题的数学模型,提出了基于射程直接离散的参数化方法,分别就耗油最少和飞行时间最短的爬升弹道利用遗传算法进行了优化。通过仿真获得了这两种优化弹道,并证明了这种参数化方法对于处理这种弹道优化问题是有效的。弹道的优化研究为以冲压发动机为动力的战术导弹的弹道设计提供了理论参考。For the climb trajectory optimization of a ramjet powered tactical missile, a mathematical model was established and a parameterization method of directly discreting the parameter along range was presented. Two optimal trajectories, time optimal and fuel consumption optimal were obtained from simulation. The simulation also proved the validity of the parameterization method. The simulation results also provide a reference to trajectory design for a ramjet powered tactical missile.

关 键 词：冲压发动机 导弹弹道 弹道优化 遗传算法 

分 类 号：V43[航空宇航科学与技术—航空宇航推进理论与工程] TJ013[兵器科学与技术—兵器发射理论与技术]