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中文摘要：
液化气推进技术是微小伴随卫星在轨飞行采用的一种新型推进技术。微小伴星空间调姿、变轨过程需精确的推力控制,因此必须了解卫星推进系统中推进剂的形位分布。本文理论分析了空间微重力环境下液化气推进剂气/液界面的形位分布及变化,并通过落塔实验验证了微重力环境下有效控制液体推进剂的管理方法。
英文摘要：
Liquefied gas propulsion is an advanced propulsion technology which has been used in the flight of concomitant microsatellite.The distribution of liquid propellant in the tank must be known to precisely control the thrust for the attitude adjustment and orbit change of the microsatellite. The computational simulations have been performed to investigate the motion of the gas-liquid interface of propellant in the tank of on-orbit spacecraft under micro-gravity environment.And drop tower experiments have been conducted to verify the effective method of propellant management in microsatellite.
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Influence of working liquid on the onset characteristics of a thermoacoustic engine with gas and liq
Influence of Rayleigh-Taylor Instability on Liquid Propellant Reorientation in a Low-Gravity Environ
The Coupling of Evaporation and Thermocapillary Convection in a Liquid Layer with Mass and Heat Exch
Coupling of thermocapillary convection and evaporation effect in a liquid layer when the evaporating
Experimental Study on the Combined Evaporation Effect and Thermocapillary Convection in a Thin Liqui
The influence of Rayleigh-Taylor instability on liquid propellant reorientation in low-gravity envir
Influence of Rayleigh-effect combined with Marangoni effect on the onset of convection in a liquid l
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