摘要
文章基于空间推进系统热控的特点,针对长期在轨航天器推进系统热控面临的贮箱膜片热胀冷缩疲劳和机组阀门超温问题进行机理分析,归纳贮箱热控和发动机、推力器高温工况相应的解决措施及难点,结合某型号实际提出解决方案,并对改进后的效果进行分析预示,给出长期在轨航天器热控方案设计建议。
Based on the structural characteristics of spacecraft propulsion sub-subsystem,the considerations in the thermal control of the subsystem are introduced.The problems focus on the thermal cycling fatigue of the diaphragm of the propellant tank,and the overheating of the valves with respect to the spacecraft of long service life.The general temperature control measures for both the active expulsion tank and the engine and thruster in the HT condition are expounded with discussion of the engineering difficulties.Then,an actual example is given with analytical predictions.Suggestions are made of the design of thermal control subsystem for long-life spacecrafts.
作者
贾世锦
明章鹏
刘建盈
付扬
王国军
JIA Shijin;MING Zhangpeng;LIU Jianying;FU Yang;WANG Guojun(Beijing Institute of Manned Space System Engineering;Beijing Institute of Spacecraft System Engineering: Beijing 100094,China;Shanghai Institute of Space Propulsion,Shanghai 201112,China)
出处
《航天器环境工程》
2019年第2期165-170,共6页
Spacecraft Environment Engineering
基金
国家重大科技专项工程
关键词
空间推进系统
长期在轨航天器
金属膜片贮箱
机组阀门
热控方案
space booster sub-system
long-term orbiting spacecraft
metal diaphragm tank
valves of engine unit
thermal control scheme
