摘要
载人航天器密封舱温、湿度控制系统是生命保障系统的重要组成部分。本文介绍了一种实验系统的研究情况。该系统主要由航天服循环回路、座舱循环回路及冷却剂循环回路组成。在模拟舱容积为4.7m^3、压力为101.55、30.7kPa。热负荷为1610—1804kj/h 和产湿量为150—363g/h的条件下实验表明:该实验系统能将舱温控制在16.3—24.5℃的范围内,相对湿度控制在51～89%的范围内。
Temperature and humidity control system is an important partof the life support system in space capsule.This paper describesthe study of a test system which consists primarily of spacesuitcircuit,cabin circuit and liquid coolant loop.It was tested in asimulated capsule in which the operational conditions were 4.7m^3 volume,101.55.30.7kpa pressure,1610-1804 kj/h heat loadand 150-363 g/h moisture production rate.The system was foundto be capable of controlling the temperature and relative humiditywithin the rage of 16.3-24.5℃ and 51-89%,respectively.
出处
《航天医学与医学工程》
CAS
CSCD
1990年第1期11-16,共6页
Space Medicine & Medical Engineering
关键词
航天器
密封舱
温度
湿度
控制系统
Spacecraft cabins
Temperature control
Humidity control
Thermal control
Environmental control
Life support systems
