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离子液体微推进技术研究进展
引用本文:范益朋,夏广庆,韩亚杰.离子液体微推进技术研究进展[J].航空动力学报,2020,35(6):1275-1285.
作者姓名:范益朋  夏广庆  韩亚杰
作者单位:大连理工大学工业装备结构分析国家重点实验室,辽宁大连116024,大连理工大学工业装备结构分析国家重点实验室,辽宁大连116024;大连理工大学辽宁省空天飞行器前沿技术重点实验室,辽宁大连116024,大连理工大学工业装备结构分析国家重点实验室,辽宁大连116024,大连理工大学工业装备结构分析国家重点实验室,辽宁大连116024;大连理工大学辽宁省空天飞行器前沿技术重点实验室,辽宁大连116024,大连理工大学工业装备结构分析国家重点实验室,辽宁大连116024;大连理工大学辽宁省空天飞行器前沿技术重点实验室,辽宁大连116024,中国航天科技集团有限公司中国空间技术研究院北京卫星环境工程研究所,北京100094
基金项目:国家自然科学基金(11675040); 中央高校基本科研业务费专项资金(DUT18GF109,DUT19LAB46);北京卫星环境工程研究所CAST-BISEE创新基金(CAST-BISEE2019-034)
摘    要:介绍了离子液体推进器的基本结构和工作原理,阐述了粒子发射的限制条件及通常采用的工作模式,总结了该推进器的常见分类形式。介绍了当前广泛应用的一些实验方法和仿真手段,以及针对发射阈值场强、束流散射、多粒子分散效率、推进器长时间工作稳定性等问题开展相关研究取得的进展,对比分析了适合粒子发射的工作环境及相对精确的仿真方法,为推进器的后续设计、工作模式设定及性能评估等工作提供了参考。结果表明:增大推进剂流阻、提高发射极阵列密度是提高离子液体推进器效率和推力的合适手段;利用闭环控制的方法改变发射电压极性、逐渐提高发射电压大小是维持推进器推力大小、提高工作稳定性的有效方法。

关 键 词:电推进  微推进  离子液体  发射条件  推进器效率
收稿时间:2019/12/4 0:00:00

Research progress of ionic liquid micropropulsion technology
FAN Yipeng,XIA Guangqing,HAN Yajie.Research progress of ionic liquid micropropulsion technology[J].Journal of Aerospace Power,2020,35(6):1275-1285.
Authors:FAN Yipeng  XIA Guangqing  HAN Yajie
Institution:State Key Laboratory of Structural Analysis for Industrial Equipment,,Dalian University of Technology,Dalian Liaoning 116024,China;;State Key Laboratory of Structural Analysis for Industrial Equipment,,Dalian University of Technology,Dalian Liaoning 116024,China;Key Laboratory of Advanced Technology for Aerospace Vehicles,,Liaoning Province,Dalian University of Technology,Dalian Liaoning 116024,China;
Abstract:The basic structure and working principle of ionic liquid thrusters, including the restrictions on particle emission and the commonly used operating regimes, were introduced. The common classification methods of ionic liquid thruster were summarized. The presently wide-used experimental or simulation methods, and the related progress on emission threshold field strength, beam divergence, polydispersive efficiency, long-term working stability and other issues were reviewed to compare and analyze the working conditions suitable for particle emission and more accurate simulation methods. The future research ideas and reference for the improved design, operating regime setting, and performance evaluation of ionic liquid thruster were also presented. Results show that increasing the flow resistance of propellant and array density of emitter is the appropriate means to improve the efficiency and thrust of the ionic liquid thruster, and changing the emitter voltage polarity and increasing the emitter voltage gradually by using the closed-loop control method is the effective way to maintain the thrust and improve the working stability of the thruster.
Keywords:electric propulsion  micropropulsion  ionic liquid  emission condition    thruster efficiency
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