液体推进剂在轨加注技术与加注方案

梳理了推进剂空间加注的关键技术，介绍了不同流体空间加注的系统组成与加注程序，提出了我国开展相关研究的思路.研究表明:①气液相分离是实现推进剂空间加注的基础，常温推进剂可采用挠性隔膜或叶片式贮箱实现气液分离，而金属网状膜通道式液体获取装置（LAD）在低温流体空间分离领域效果最佳；②低温推进剂空间加注需要结合空间热防护技术、蒸发量控制技术等；③常温推进剂采用排气型空间加注，低温推进剂采用无排气加注，且可借助热力学排气系统实现大充灌率加注；④我国可按照先常温后低温的思路开展研究，并充分借鉴现有实验平台与研究成果的支持. 

On-orbit refilling technologies and schemes of liquid propellant

The key technologies associated with propellant on-orbit refilling was summarized whilst the system construction and the refilling procedures were introduced. Moreover, a suggesting research project was proposed for guiding the domestic researches. Several valuable conclusions were drawn as follows: (1) On-orbit gas-liquid separation technology is the basis of the propellant refilling. Membrane and vane tank can be used to separate the gas-liquid phases in a normal-temperature propellant tank, while screen channel liquid acquisition devices (LAD) may be the best choice for the cryogenic propellant tank. (2) Space thermal-insulation and boil-off control technologies must be applied in the on-orbit refilling operation of cryogenic propellant. (3) Venting approach can be used for normal-temperature propellant, and no-vent filling is suggested for the cryogenic propellant. Also, use of thermodynamic venting system (TVS) is beneficial to a larger refilling rate of cryogenic propellant. (4) A research scheme concerning the normal-temperature propellant first and then the cryogenic propellant is suggested in the domestic researches. Simultaneously, the present research platform and the latest research achievements should be referenced.