铟场致发射电推力器的研制  

Development of indium field emission electric propulsion thruster

作　　者：段君毅[1] 康小明[1] 赵万生[1] 

机构地区：[1]上海交通大学机械与动力工程学院,机械系统与振动国家重点实验室,上海200240

出　　处：《固体火箭技术》2011年第6期734-738,共5页Journal of Solid Rocket Technology

基　　金：国家自然科学基金重点课题资助(50635040)

摘　　要：基于场致发射电推力器工作机理,分析并设计了针型铟场致发射电推力器的结构,利用微细电化学加工方法制作了发射针,并对该样机的伏安特性及稳定性等进行了相关测试。结果表明,该样机可正常发射,稳定性良好。对场致发射电推力器发射特性影响因素的分析发现,发射针针尖顶点半径对发射伏安特性有显著影响,而吸极内孔径及吸极到发射极距离对伏安特性影响并不大。Based on the study of the field emission electric propulsion （FEEP） operating mechanism, the thruster prototype structure was designed, the emitting tip was fabricated with micro electrochemical etching method, and the current-voltage character- istics of the prototype were measured and its stability was investigated. The results show that the thruster prototype can operate norreally with good stability. Factors influencing the current-voltage characteristics of the thruster were analyzed for optimization of its design. It is found that the radius of the emitting tip apex has great impact on the current-voltage characteristics, while the inner ra- dius of the extractor and the distance between the extractor and emitter have minor effects.

关 键 词：铟场致发射电推力器 发射针 伏安特性 

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]