微空心阴极放电推力器性能研究  

Performance of microhollow cathode discharge thruster

作　　者：夏广庆[1] 毛根旺[2] 陈茂林[2] 孙安邦[2] 

机构地区：[1]大连理工大学工业装备结构分析国家重点实验室运载工程与力学学部航空航天学院,大连116024 [2]西北工业大学航天学院,西安710072

出　　处：《强激光与粒子束》2010年第5期1145-1148,共4页High Power Laser and Particle Beams

基　　金：大连理工大学引进人才启动基金项目(3014-893309);国家留学基金委资助项目([2006]3074)

摘　　要：微空心阴极放电推力器是一种新颖的电热式微推力器,利用纳卫星提供的1-10 W的功率可提高微推进装置的性能。为了预示该推力器的性能,结合实验中测量的气体温度值和火箭发动机原理,初步计算得出微放电推力器的推力范围为几十至上千μN,以氩气为工质比冲量级为600-1 000 N·s/kg,以氦气为工质比冲量级为3 000 N·s/kg。研究结果表明,微空心阴极放电较小的尺寸结构与强烈并可控的气体加热相结合,可以开发应用在电热式微放电推进中,作为微小卫星,尤其是纳卫星和皮卫星的动力系统。The gas heating of microhollow cathode discharge（MHCD） is found to have a strong relation with overall discharge behavior in the experimental investigation.It provides crucial understanding to support the application and preliminary design of MHCD thruster.The thruster produced by this kind of propulsion system is predicted in the range of several tens to several thousands μN and the specific impulse is evaluated on the order of 600～1 000 N·s/kg using argon or on the order of 3000 N·s/kg using helium as the propellant gas respectively.The main performance of the MHCD thruster proves that MHCD can be applied as a new microplasma propulsion system for attitude control and station keeping of nano-satellites.

关 键 词：电推进 纳卫星推进 微推力器 微空心阴极放电 

分 类 号：V439.4[航空宇航科学与技术—航空宇航推进理论与工程]