大推力发动机在轨羽流热效应监测与反演方法  

Method of On-orbit Plume Heat Effect Monitoring and Inversion for Large Thrust Engines

作　　者：马巨印[1] 张有为[1] 陈建新[1] 宋馨[1] 李庆辉[2] MA Juyin;ZHANG Youwei;CHEN Jianxin;SONG Xin;LI Qinghui(Beijing Institute of Spacecraft System Engineering,Beijing 100094,China;Beijing Institute of Spacecraft Environment Engineering,Beijing 100094,China)

机构地区：[1]北京空间飞行器总体设计部,北京100094 [2]北京卫星环境工程研究所,北京100094

出　　处：《航天器工程》2019年第4期60-64,共5页Spacecraft Engineering

基　　金：国家重大科技专项工程

摘　　要：为了获得相对准确的大推力发动机在轨真实羽流热效应数据,提出了一种在轨羽流热效应监测与反演方法,并将其应用于嫦娥四号着陆器.该方法突破400℃宽温区对400 kW/m2短时超高羽流热效应进行精确监测的技术,获得发动机周边温度数据,建立发动机羽流到达目标表面的反演模型.反演结果与嫦娥四号着陆器在轨实测结果一致,验证了该方法的正确性.该方法反演所得羽流热效应数据,可为后续月球着陆器热防护设计提供参考.In order to obtain relatively accurate on—orbit real plume heat effect data of large thrust engines,a method for on—orbit plume heat effect monitoring and inversion of large thrust engines is proposed and it is also used on the Chang’e—4 lander.This method breaks through the technolo—gy of detecting 400kW/m2 ultrahigh plume heat effect in a short time,which can be adapted to a wide temperature range of 400℃.It also obtains the temperature data around the engine and es—tablishes an inversion model for the engine plume to the target surface.The inversion results are in agreement with the Chang’e—4 lander on—orbit measurement results,which verifies the correct—ness of the method.The plume heat effect data inversed by this method can provide a reference for subsequent lunar landers thermal protective design.

关 键 词：嫦娥四号着陆器 大推力发动机 在轨羽流热效应 监测与反演 

分 类 号：V476[航空宇航科学与技术—飞行器设计]