摘要
微型电推进技术具备体积小、质量轻、功耗低、比冲高等特点,是微纳卫星最合适的动力技术。结合微纳卫星对微型电推进系统的技术需求,综述了微型离子推力器、低功率霍尔推力器、场致发射电推力器、离子液体电喷雾推力器、真空电弧推力器、脉冲等离子体推力器等六种典型微型电推力器的工作机理、性能参数范围及研究和应用现状,分析了气体工质电离、液体工质电喷雾、固体工质烧蚀等三种电离机制的微型电推力器的技术特点。结果表明:气体电离模式技术较成熟、寿命长,缺点是系统相对复杂、低功率工作时效率大幅下降,故建议应用于微卫星动力系统;液体电喷雾模式结构简单,效率高,微纳卫星均可应用,但性能一致性和长寿命工作特性需要进一步考核验证;固体烧蚀模式结构最简单,微纳卫星均可应用,缺点是效率低。研究结果可为微纳卫星推进系统方案的优选提供参考。
Micro electric propulsion technology is the most suitable propulsion technology for micro/nano satellites,with the characteristics of small size,light weight,low power consumption and high specific impulse.Based on the technical requirements of micro/nano satellite for micro electric propulsion system,the working mechanism,performance parameters range,research and appli⁃cation status of six typical micro thrusters,such as micro ion thruster,low power hall thruster,field emission electric thruster,ionic liquid electrospray thruster,vacuum arc thruster and pulsed plasma thruster,were reviewed in this paper.The technical characteris⁃tics of micro electric thruster with three ionization mechanisms,such as gas working medium ionization,liquid working medium elec⁃trospray and solid propellant ablation,were analyzed.The results show that the gas ionization mode has the most abundant technology accumulation,and long life characteristics,while with the disadvantage of relatively complex system and low efficiency at low power operation.Therefore,it is suggested to be applied to microsatellites power system.The liquid electrospray mode is simple and effi⁃cient,which is suitable for both microsatellites and nanosatellites.However,the performance consistency and long life working char⁃acteristics need further examination and verification.The solid ablation mode has the simplest structure,which is suitable for both microsatellites and nanosatellites,and has the disadvantage of low efficiency.The research results can provide reference for the opti⁃mization of micro/nano satellite propulsion system.
作者
陈茂林
刘旭辉
周浩浩
陈冲
贾翰武
CHEN Maolin;LIU Xuhui;ZHOU Haohao;CHEN Chong;JIA Hanwu(Combustion,Internal Flow and Thermal-Structure Laboratory,Northwestern Polytechnical University,Xi'an 710072,China;Beijing Institue of Control Engineering,Beijing 100094,China)
出处
《固体火箭技术》
EI
CAS
CSCD
北大核心
2021年第2期188-206,共19页
Journal of Solid Rocket Technology
关键词
电推进
微纳卫星
电喷雾推力器
真空电弧推力器
场致发射电推力器
electric propulsion
micro/nano satellites
electrospray thruster
vacuum arc thruster
field emission electric thruster
