运载火箭迭代制导方法的改进研究  

AN IMPROVED ITERATIVE GUIDANCE METHOD FOR LAUNCH VEHICLE

作　　者：吴楠[1] 程文科[1] 王华[1] 

机构地区：[1]国防科技大学航天与材料工程学院,长沙410073

出　　处：《动力学与控制学报》2009年第3期279-282,共4页Journal of Dynamics and Control

摘　　要：提出了一种能够同时控制终端六个状态分量的迭代制导改进方法.针对只能控制发动机推力方向的运载火箭,将俯仰角控制过程分为两段,分别对两个位置分量进行修正,实现对火箭六个状态分量的控制.在火箭到达终点时同时满足了三个速度分量和三个位置分量的终端约束,增强了迭代制导方法的自适应性.算例结果表明,改进方法将制导终端位置偏差减小了一个量级,且未增加迭代制导的计算量,便于箭载计算机软件实现.Based on the traditional method of iterative guidance, which only controls the engine＇ s thrust direction, the pitch angle control process was divided into two sections, which carry on the revision separately to twoposition components and realize the control for six state components of the rocket. When the rocket arrives at the end point, it simultaneously has satisfied the terminal constraint of three velocity components and three position components and strengthened the adaptability of iterative guidance method. The example results indicate that the improved method further increase the guidance accuracy and the position deviation reduces a magnitude. At the same time, this method has not increased the computation amount of iterative guidance, which is advantageous for the rocket- borne computer＇s realization, so it has certain project significance.

关 键 词：运载火箭 迭代制导 最优控制 位置修正 

分 类 号：V448.1[航空宇航科学与技术—飞行器设计]