烧蚀Z箍缩脉冲等离子体推进系统实验研究  

Experimental Study of Ablative Z-Pinch Pulsed Plasma Thruster System

作　　者：王骥勤 刘裴栩 刘伟[1,2] 高俊[3] 王伟宗[1,2] WANG Jiqin;LIU Peixu;LIU Wei;GAO Jun;WANG Weizong(Beihang University,Beijing 100191,China;Key Laboratory of Spacecraft Design Optimization and Dynamic Simulation Technologies,Ministry of Education,Beijing 100191,China;Beijing Institute of Control Engineering,Beijing 100094,China)

机构地区：[1]北京航空航天大学,北京100191 [2]航天器设计优化与动态模拟技术教育部重点实验室,北京100191 [3]北京控制工程研究所,北京100094

出　　处：《空间控制技术与应用》2024年第5期92-100,共9页Aerospace Control and Application

基　　金：国家自然科学基金资助项目(52277133)。

摘　　要：脉冲等离子体推力器(PPT)是最早用于空间任务的电推力器.烧蚀Z箍缩脉冲等离子体推力器(AZPPT)因其同轴前后式和阳极尖锥的特殊构型可以在较小体积和功率下实现较高的推功比和比冲.研究阳极尖锥长度、充电电压、放电次数对AZPPT性能的影响,试验表明随着充电电压的升高,推力器放电电流峰值、羽流等离子体电子温度、元冲量等参数升高,证明可通过改变电压实现推力的宽范围调节.阳极尖锥高度增加时,推力器的元冲量有少量下降,比冲有明显上升,相比没有尖锥时,比冲最高提升23.7%,总体效率最高提升7.3%,证明该结构在小功率AZPPT中的性能优化作用.基于以上结果,设计开发了一款1 U小型化、模块化推进系统.推进系统点火成功,5 J放电能量下元冲量达193.72μN·s,具有小功率、综合性能好、结构紧凑等特点.Pulsed Plasma Thruster(PPT)is the earliest electric thruster used for space missions.Among them,the Ablative Z-pinch Pulsed Plasma Thruster(AZPPT)can achieve high thrust to power ratio and specific impulse at a low volume and power due to its special front-back coaxial configuration and anode spike.The effects of anode spike length,charging voltage,and discharge frequency on the performance of AZPPT was studied in this paper.The experiment showed that with the increase of charging voltage,the peak discharge current of the thruster,the electron temperature of the plume plasma,and the impulse bit increased,proving that the wide range adjustment of thrust can be achieved by changing the voltage.When the height of the anode spike increases,the impulse bit of the thruster decreases slightly,while the specific impulse increases significantly.Compared to the performance of thruster without the spike,the specific impulse increases by 23.7%,and the overall efficiency increases by 7.31%,indicating that anode spike can optimize the thrust performance of low-power AZPPT significantly.Based on the above results,a 1 U miniaturized and modular propulsion system has been developed.The ignition of the propulsion system was successful,and the impulse bit reached 193.72μN·s under a discharge energy of 5 J.It has the characteristics of low power,good overall performance,and compact structure.

关 键 词：脉冲等离子体推力器 Z箍缩 电源处理单元 微推力测量 

分 类 号：V439[航空宇航科学与技术—航空宇航推进理论与工程]