基于解析预报模型的火箭远场安全性快速分析方法  

Study on Fast Analysis Method of Relative Motion Safety ofLaunch Vehicle Based on Analytical Prediction Model

作　　者：周敬 张晚晴 张博戎 魏威 牟宇 ZHOU Jing;ZHANG Wanqing;ZHANG Borong;WEI Wei;MOU Yu(Beijing Institute of Astronautical Systems Engineering,Beijing 100076,China)

机构地区：[1]北京宇航系统工程研究所,北京100076

出　　处：《宇航总体技术》2025年第1期32-40,共9页Astronautical Systems Engineering Technology

基　　金：国家部委基础加强计划技术领域基金(JSLY-49-A49017)。

摘　　要：随着低轨巨型互联网星座的快速工程应用,运载火箭“一箭多星”已经成为主要发射方式。为了解决由此带来的复杂远场安全性分析问题,提出一种基于解析预报模型的远场安全性快速分析方法。以地心惯性系下星箭分离点参数为初始状态,结合无奇异轨道根数外推模型,获得绝对运动解析预报模型。通过引入CW方程和TH方程,获得各飞行体之间相对运动演化的解析模型。仿真结果表明,相较于运载火箭小步长积分远场安全性分析方法,本方法计算效率提升超过90%,绝对运动预报误差小于1%,相对运动预报误差小于0.2%,可以满足工程应用需要。The rapid engineering application of low-Earth-orbit large constellations has made the multi-satellite launch mission the primary mode.To address the more complex issues of relative motion safety analysis arising from this,a fast analysis method based on an analytical prediction model is proposed.Firstly,begin with the parameters of the satellite separation point in the geocentric inertial system,and combined with a non-singular orbital element prediction model,an analytical prediction model for the absolute motion of the satellite is obtained.By introducing the CW equation and the TH equation,an analytical model for the evolution process of relative motion between satellites and launch vehicle is obtained.Simulation results show that,compared with the traditional relative motion safety analysis,the efficiency of this method is significantly improved by 90%.The absolute motion prediction error is less than 1%,and the relative motion prediction error is less than 0.2%,which can meet the needs of engineering applications.

关 键 词：运载火箭 一箭多星 远场安全性 解析预报模型 

分 类 号：V412.2[航空宇航科学与技术—航空宇航推进理论与工程]