摘要
为研究空间发动机羽流对卫星的影响,建立针对太阳反光镜、光学仪表和低温红外传感器等重要载荷的羽流污染预报数据库,开发了一套羽流试验系统并进行了试验研究.试验台主要包括:空间环境模拟系统;电热气体模拟发动机;稳压气源;测量系统及其温控.采用计算流体动力学(CFD)和直接模拟Monte Carlo(DSMC)相结合的方法完成了羽流场的数值模拟,计算结果为试验参数的选择提供了重要依据.试验系统满足在mPa量级的真空压力和(93±5)K的背景温度下的稳定运行和精确测量.完成了国内首次在模拟100 km高空条件下,羽流场关键参数——压力场的测量.
In order to study the space thruster plume flow effect on satellite and build the database that can be used to predict the function degradation of optical solar reflector （OSR）, optical elements, and cryogenic infrared sensor caused by the thruster plume contamination, a set of plume test system was developed and experimental investigations were performed. The experimental system includes a simulated space environment vacuum facility, a simulated electric-heat-gas thruster, a steady pressure gas supply system, test system and temperature control system. Numerical calculation was finished with the combined method CFD and direct simulation Monte Carlo（DSMC）, and the results were served as the important reference data in the selection of the test parameters. The experimental system works well and the measurements perform accurately under the vacuum pressure of the mPa order and the background temperature of （93±5） K. The most important parameter of the plume flow, pressure, was tested at the simulated space environment with 100 kilometers altitude.
出处
《上海交通大学学报》
EI
CAS
CSCD
北大核心
2007年第9期1542-1545,1564,共5页
Journal of Shanghai Jiaotong University
关键词
羽流试验
羽流污染
真空
低温
压力场
plume test
plume contamination
vacuum
cryogenic
pressure field
