火箭推进2026，Vol.52Issue(3)：105-112,8.DOI:10.3969/j.issn.1672-9374.2026.03.010
单组元姿控推力室真空深冷环境温度控制
Monopropellant attitude control thruster in the vacuum cryogenic environment
摘要
Abstract
The monopropellant hydrazine catalytic decomposition attitude control thruster's decomposition reaction is stable at normal temperature.However,the thruster is easy to bring large cold starting pressure peak in the space vacuum cryogenic environment when it is used as the attitude control power of the space vehicle,which reduces the reliability of the thruster structure.In order to improve the adaptability of monopropellant thruster to the cryogenic environment,the temperature reduce characteristics and performance characteristics were carried out.The temperature reduction characteristics of thruster at-170 ℃ were studied by simulation and vacuum cryogenic tests.The temperature rise characteristics of thruster using the different working procedures at-170 ℃ were studied by high-altitude simulation tests.The results show that temperature reduce rate of thruster is deceased by the methods of passive thermal control measures such as heat insulation wrap.The timing multiple pulse procedures effectively improve the warm-up efficiency of thruster and the impression is better than long-range procedures in the same working time.关键词
单组元推力室/真空深冷传热试验/高空模拟试验/保温程序Key words
monopropellant thruster/vacuum cryogenic thermal test/high-altitude simulation test/warm-up procedure分类
航空航天引用本文复制引用
党涵宇,朱伟,董佳磊,陈铮夏,汤成龙..单组元姿控推力室真空深冷环境温度控制[J].火箭推进,2026,52(3):105-112,8.基金项目
国家自然科学基金(52236001) （52236001）
