固体探空火箭迭代制导方法研究  

Research on iterative guidance method of solid sounding rocket

作　　者：唐冰涛 陈华兵 杨宇星 江小娟 TANG Bingtao;CHEN Huabing;YANG Yuxing;JIANG Xiaojuan(Xi'an Institute of Aerospace Solid Propulsion Technology,Xi'an 710025,China;North west Industry Froup Co.Ltd.,Xi'an 710043,China)

机构地区：[1]西安航天动力技术研究所,西安710025 [2]西北工业集团有限公司,西安710043

出　　处：《固体火箭技术》2024年第1期135-142,共8页Journal of Solid Rocket Technology

基　　金：快速扶持基金项目(80903020104)。

摘　　要：固体探空火箭在实施某类载荷远程投递任务时,要求接近落点的精度在千米级,由于火箭一般在大气层内的主动段实施有效的制导控制,其制导时间短,气动影响无法忽视,实现落点精度控制难度很大。针对该问题提出了一种适用于固体探空火箭在大气层内的迭代制导方法,通过在线计算剩余视速度和视位置增量,对固体探空火箭落点进行迭代计算,形成制导控制指令。仅在主动段进行制导控制,对再入段进行气动补偿,使得固体火箭落点控制达到了较高的精度。数值仿真分析表明:该方法落点精度较传统的摄动制导方法提高了1个数量级,体现出该迭代制导方法的优越性。The solid sounding rocket is required to achieve the accuracy of the landing point in the kilometer level when carrying out the long-range delivery of certain kinds of loads.Because the rocket generally implements effective guidance and control in the active section of the atmosphere,its guidance time is short,and the aerodynamic influence cannot be ignored,so it is very difficult to achieve the accuracy control of the landing point.To solve this problem,an iterative guidance method for solid sounding rocket in atmosphere was proposed.Through online calculation of the residual apparent velocity and apparent position increment,the iterative calculation of the solid sounding rocket landing point was carried out to form guidance and control commands.The guidance control is only carried out in the activestage,and the pneumatic compensation is carried out in the reentry stage,which makes the solid rocket landing point control reach a higher precision.Mathematical simulation shows that the accuracy of this method is one order of magnitude higher than that of the traditional perturbation guidance method,which shows the superiority of the proposed iterative guidance method.

关 键 词：气动阻力 视速度 视位置 气动补偿 迭代制导 摄动制导 

分 类 号：V435[航空宇航科学与技术—航空宇航推进理论与工程]