中国空间站燃烧科学实验系统燃烧室设计与分析

中国空间站燃烧科学实验系统能够在轨进行多种燃料的微重力燃烧实验，其关键组件燃烧室是可实现密封的压力容器，为实验插件提供机械、氧化剂、废气排放、供电、控制、冷却等接口，支持实验插件完成相关功能.本文依据承压范围、漏率、透射光波段等设计技术指标进行燃烧室结构设计与力学分析.燃烧室采用分段式结构，由合叶门、锁紧圈、连接环、筒体等组件依次连接组成，连接结构处使用密封圈.通过燃烧室的承压分析、模态分析以及随机响应分析，校核了燃烧室结构的强度、刚度及随机振动响应特性，验证了燃烧室设计的安全性与可靠性，能够满足发射及在轨工作要求. 

Combustion Chamber Design and Analysis of the Space Station Combustion Science Experimental System

The Chinese Space Station Combustion Science Experiment System is capable of conducting microgravity combustion experiments of multiple fuel types in orbit. The combustion chamber, one of the key components, is a pressure vessel that can be sealed. It is equipped with interfaces for the experiment inserts such as mechanical, oxidizer, exhaust gas emission, power supply, control and cooling. In this paper, the detailed design and analysis of the combustion chamber is based on the technical indicators such as pressure-bearing range, leakage rate, and transmitted light band. The combustion chamber adopts a sectional structure, which consists of a hinged door assembly, a locking ring assembly, a connecting ring assembly, a cylinder assembly, etc. Seals are used at the connection positions. The strength, stiffness and random vibration response of the combustion chamber structure were checked through pressure analysis, modal analysis and random response analysis. The results verified the safety and reliability of the combustion chamber design, which can meet launch and in-orbit operational requirements.