摘要
为了解决巡航导弹加速爬升段的弹道设计,使导弹能以一种最优方式到达巡航高度并开始巡航,提出了一种弹道优化方法。该方法采用NURBS曲线拟合控制律,并通过遗传算法优化弹道。仿真计算表明,该方法可以解决基准弹道的设定问题,为发动机及导弹的研制提供数据参考,同时也可以初步确定发动机和导弹的控制律,为进一步的设计提供依据和基础。
A cruise missile should climb with a large climbing angle to arrive at the cruise height in an optimum way and begin the cruising flight at the cruising speed. To deal with this problem, this paper presents a fast method, which using NURBS curve to represent the flight control rule, using the genetic algorithm to get the optimum result. Simulation results show that this method can get the optimum trajectory with ease, provide the calculation data for the conceptive design and even for the detail design of the engine and the missile.
出处
《飞行力学》
CSCD
北大核心
2006年第1期45-47,51,共4页
Flight Dynamics
关键词
巡航导弹
弹道
遗传算法
cruise missile
trajectory
genetic algorithm
