摘要
迭代制导是直接终端制导,是运载火箭路线自适应制导方法的一种。从20世纪60年代末开始,在运载火箭上得到了广泛的应用。它的主要特点是制导精度高、任务适应性强、箭上飞行软件简单、对地面诸元准备要求相对较低。迭代制导基于火箭自适应制导的基本原理:即对于确定的目标轨道,最优飞行程序是瞬时飞行状态和瞬时视加速度的复杂函数,利用简化形式下最优控制求解的必要条件,对火箭末级的关机时间进行迭代,可以得到一套解析制导方程。基于运载火箭的实际飞行情况,建立了迭代制导的工程计算模型,并结合某型号进行大量的实例计算分析,对迭代制导的制导精度、自适应能力等方面进行研究。
Iterative Guidance namely closedloop directly terminal guidance mode,is one of the pathadaptive guidance modes.Since 20th century 60 years,Iterative Guidance has been abroad applied to launch vehicle.This method owns such good performance as high precision,more flexible mission adaptability,simply guidance data preparation and so on.Iterative Guidance base on a principle,the optimal flight program is a complicated function of instantaneous flight state parameters and acceleration for a desired object orbit.According to the simplified optimal control solution,we can obtain a set of simple analytical guidance equation by iterating the cutoff time of the last vehicle stage.This paper sets up the Iterative Guidance equation,and demonstrates an example of some twostagesvehicle's second flight phase to study the Iterative Guidance precision and mission flexibility.
出处
《宇航学报》
EI
CAS
CSCD
北大核心
2003年第5期484-489,501,共7页
Journal of Astronautics
关键词
迭代制导
自适应制导
运载火箭
Iterative guidance
Adaptive guidance
Launch vehicle
