离子推力器工作性能参数控制模型  

Work performance parameter control model of ion thruster

作　　者：孙明明[1] 张天平[1] 郭伟龙[1] 龙建飞[1] 

机构地区：[1]兰州空间技术物理研究所真空低温技术与物理国家级重点实验室,兰州730000

出　　处：《强激光与粒子束》2017年第4期59-65,共7页High Power Laser and Particle Beams

基　　金：真空低温技术与物理重点实验室基金项目(9140c550206130c5503)

摘　　要：为了研究离子推力器工作参数对输出特性的影响,通过离子推力器工作性能参数的理论计算公式,建立起离子推力器输入参数与输出参数的Simulink控制模型,根据模型分别对我国研制的30cm口径以及20cm口径离子推力器的工作输出参数进行了理论计算,并通过推力测量试验对理论值进行了比对和分析。比对结果表明:在推力理论计算过程中引入二价Xe离子比率和束流密度分布推力修正,以及推力均方误差修正后,推力理论值与实测值符合性较好,计算误差小于1mN,证明了推力修正方法的合理性。In order to research the effect of ion thruster＇s work performance parameters on output characteristics, an ion thruster＇s input/output work performance parameter control model was built by theoretical equation, which was also used to cal- culate work performance parameters of the 30 cm diameter ion thruster and the 20 cm diameter ion thruster. Thrust measure ex- periment was carried out to verify the calculation results. The verification results indicate that, after doubly charged xenon ion ra- tio, beam current density and thrust minimum mean squared error were introduced in thrust correction, thrust theoretical calcula- tion values are in rough agreement with the experimental results. The calculation error is less than 1 mN compared with the ex- perimental results, which proves that the thrust correction method used in this paper is reasonable. Ion thruster input/output per- formance parameter control model provides reference to semi-physical simulation modeling process, and it can be used in thruster work performance parameters optimization and in electrical supply parameters and propellant supply parameters confirm during e- lectrical system united experiment as well.

关 键 词：离子推力器 工作性能 参数控制模型 

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]