航天器工程2026，Vol.35Issue(1)：84-91,8.DOI:10.3969/j.issn.1673-8748.2026.01.011
航天器空腔结构隔热屏设计及安装方法
Design and Installation Method of Heat Shield for Cavity Structure in Spacecraft
郝佳 1梁小峰 1范庆梅 1丁勤 1孟晓亮 1沈群 1李志壮1
作者信息
- 1. 航天东方红卫星有限公司,北京 100094
- 折叠
摘要
Abstract
To solve problems such as structural complexity,high material density,insufficient support force during installation,and the risk of foreign object debris in the design of heat shield for cavity structure in spacecraft,a suspended heat shield design and installation method is pro-posed.The design utilizes a composite heat shield structure consisting of two layers of aramid fi-ber frames and one multilayer insulation blankets.A quantitative formula for detecting the tight-ening force of the aramid fibers is derived.Concurrently,the installation process method for this type of heat shield is described.The proposed heat shield is implemented and experimentally vali-dated on a three ultra-stable platform spacecraft featuring a central load-bearing cylinder cavity structure.Results demonstrate that temperature fluctuations of equipment on the spacecraft are effectively reduced,with the orbital temperature variation of the camera constrained within[-2℃,+2℃],thereby significantly improving its in-orbit imaging quality.The design and method resolve the thermal insulation challenges associated with cavity structures in spacecraft,expands the diversity of thermal control implementation strategies,and can be applied to other cavity structures and equipment on spacecraft.关键词
航天器/空腔结构/隔热屏/芳纶线框架/多层隔热组件Key words
spacecraft/cavity structure/heat shield/aramid fiber frame/multilayer insulation blankets分类
航空航天引用本文复制引用
郝佳,梁小峰,范庆梅,丁勤,孟晓亮,沈群,李志壮..航天器空腔结构隔热屏设计及安装方法[J].航天器工程,2026,35(1):84-91,8.
