作　　者： ; ; ; ;

机构地区： 西安交通大学能源与动力工程学院

出　　处： 《航空动力学报》 2016年第8期2002-2009,共8页

摘　　要： 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. The key technologies associated with propellant on-orbit refilling was summa- rized 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.

关 键 词： 低温推进剂 在轨加注 运载火箭 蒸发量控制 深空探测

领　　域： [航空宇航科学与技术]