大型航天器与外热流模拟装置的数字化结构匹配方法  

A digital method for structure matching between large spacecraft and external heat flux simulation device

作　　者：谢吉慧[1] 苏新明[1] 秦家勇[1] 袁伟峰[1] 吴星亮 XIE Jihui;SU Xinming;QIN Jiayong;YUAN Weifeng;WU Xingliang(Beijing Institute of Spacecraft Environment Engineering,Beijing 100094,China;Nothton Metrology Technology（Beijing）Co.,Ltd,Beijing 100024,China)

机构地区：[1]北京卫星环境工程研究所,北京100094 [2]北京诺斯顿测量技术(北京)有限公司,北京100024

出　　处：《航天器环境工程》2018年第3期288-292,共5页Spacecraft Environment Engineering

基　　金：战略支援部预研课题"大型卫星智能化高效试验技术"

摘　　要：在航天器真空热试验中,常选用红外加热笼作为外热流模拟装置。为提高外热流模拟的准确性,红外加热笼需要对航天器进行全表面覆形。文章针对如何确认外热流模拟装置与航天器的结构匹配性这个难题,依托三维扫描技术,建立了一套数字化结构匹配方法,解决了多站测量拼接误差累积、三维扫描仪参数优化选择2个技术难点,使三维扫描和逆向建模过程引入的几何误差不超过10 mm。该数字化结构匹配方法的实际应用结果表明,外热流模拟装置与航天器的配装成功率达到100%,实际安装状态与仿真结果吻合度较好。The infrared heating cage is often used as the external heat flux simulation device in the thermal vacuum test（TBT＆TVT） for spacecraft. To conduct an accurate simulation of the heat flux, the infrared heating tape array is supposed to cover the whole surface of the spacecraft. To solve the difficulties in confirming the structural matching degree between the spacecraft and the infrared heating cage in the test, a set of digital structure matching methods is adopted based on the 3 D scanning technology. The set of methods is successful in reducing the accumulated error during the data splicing and in optimizing the parameters of the 3 D scanner. The total geometric error of the 3 D scanning and the reverse modeling is not more than 10 mm. By using this set of methods, the structural matching is completely achieved between the heat flux simulation device and the spacecraft. In the meantime, the actual installation state is in good agreement with the simulation results.

关 键 词：大型航天器 外热流模拟装置 结构匹配 

分 类 号：V416.4[航空宇航科学与技术—航空宇航推进理论与工程]