空间羽流试验台设计与系统测试  

Design and Testing of Space Plume Experimental System

作　　者：肖泽娟[1] 程惠尔[1] 周红玲[2] 周伟敏[3] 

机构地区：[1]上海交通大学机械与动力工程学院,上海200240 [2]上海空间推进研究所,上海200233 [3]上海航天技术研究院,上海201109

出　　处：《上海航天》2008年第4期56-60,共5页Aerospace Shanghai

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...

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 

分 类 号：V416.8[航空宇航科学与技术—航空宇航推进理论与工程]