航天器工程2025，Vol.34Issue(4)：43-50,8.DOI:10.3969/j.issn.1673-8748.2025.04.006
航天器发动机耐高温复合材料支架设计与验证
Design and Verification of High-temperature Resistant Composite Material Bracket for Spacecraft Engine
韩明芬 1张少辉 1李竞蔚1
作者信息
- 1. 北京空间飞行器总体设计部,北京 100094
- 折叠
摘要
Abstract
In response to the challenge that the first-generation 490N engine composite bracket and the second-generation 490N engine titanium alloy bracket cannot simultaneously meet the high-temperature resistance and light weight requirements,a second-generation 490N engine bracket is designed by using high-temperature resistant bismaleimide resin composite materials,and analy-sis verification and test verification are conducted.The verification results demonstrate that this bracket can withstand both mechanical and thermal workloads under complex operating condi-tions.Compared to the first-generation 490N engine composite material bracket,the heat resis-tance has been increased from 100℃to 200℃,and compared to the second-generation 490N en-gine titanium alloy bracket,the structure has achieved a weight reduction of 57.7%.This high-temperature resistant composite material bracket has been successfully applied to multiple space-craft,providing reliable technical support for their high-quality launches and precise orbit adjustments.关键词
航天器发动机支架/耐高温复合材料/机热一体化设计Key words
spacecraft engine bracket/high-temperature resistant composite material/mechanical-thermal integrated design分类
航空航天引用本文复制引用
韩明芬,张少辉,李竞蔚..航天器发动机耐高温复合材料支架设计与验证[J].航天器工程,2025,34(4):43-50,8.
