摘要
基于国外羽流试验经验和国内实际,设计了一套主要由空间环境模拟设备、电加热气体模拟发动机、稳压气源、轴向与径向移动装置、测量系统和温控系统等组成的空间羽流试验系统,并测试了试验系统的温度、压力稳定度等参数。测量结果表明:系统满足发动机模拟空间高度大于100 km长程试车的要求,测试过程中真空舱内压力维持在1×10-3Pa量级,冷阱温度为(93±5)K。系统测量准确可靠,达到设计要求。
A plume experimental system was designed and tested based on the experience of some plume experiments and the conditions in domestic in this paper,which was composed of a simulated electric heat-gas thruster,a steady pressure gas supply system,radial and axis movement device,measurement system and temperature control system mainly.The parameters related with temperature and pressure were tested.The results showed that the experimental system designed would be conducted stably at the simulated altitude which...
出处
《上海航天》
北大核心
2008年第4期56-60,共5页
Aerospace Shanghai
关键词
空间羽流试验台
低温冷肼系统
稳压气源漏率
压力波动幅度
Space plume experimental system
Liquid nitrogen trap system
Leakage of steady pressure gas supply system
Amplitude of pressure variation
