• 文献检索
  • 文档翻译
  • 深度研究
  • 学术资讯
  • Suppr Zotero 插件Zotero 插件
  • 邀请有礼
  • 套餐&价格
  • 历史记录
应用&插件
Suppr Zotero 插件Zotero 插件浏览器插件Mac 客户端Windows 客户端微信小程序
定价
高级版会员购买积分包购买API积分包
服务
文献检索文档翻译深度研究API 文档MCP 服务
关于我们
关于 Suppr公司介绍联系我们用户协议隐私条款
关注我们

Suppr 超能文献

核心技术专利:CN118964589B侵权必究
粤ICP备2023148730 号-1Suppr @ 2026

文献检索

告别复杂PubMed语法,用中文像聊天一样搜索,搜遍4000万医学文献。AI智能推荐,让科研检索更轻松。

立即免费搜索

文件翻译

保留排版,准确专业,支持PDF/Word/PPT等文件格式,支持 12+语言互译。

免费翻译文档

深度研究

AI帮你快速写综述,25分钟生成高质量综述,智能提取关键信息,辅助科研写作。

立即免费体验

内联螺旋馈送真空电弧推力器。

Inline screw feeding vacuum arc thruster.

作者信息

Kronhaus Igal, Laterza Matteo, Maor Yonatan

机构信息

Aerospace Plasma Laboratory, Faculty of Aerospace Engineering, Technion - I.I.T., Technion City, 3200003 Haifa, Israel.

出版信息

Rev Sci Instrum. 2017 Apr;88(4):043505. doi: 10.1063/1.4979706.

DOI:10.1063/1.4979706
PMID:28456244
Abstract

A new type of micropropulsion device for nanosatellite applications is presented-the inline-screw-feeding vacuum-arc thruster (ISF-VAT). This thruster couples a conventional "triggerless" ignition geometry with a feeding mechanism that maintains a steady state discharge performance. The feeding mechanism implements a screw action on a central cathode rod. At a predetermined rate, a complete and uniform erosion of the cathodes tip is obtained as well as "healing" of the insulator coating. The inline feeding of the cathode forces the arc to emerge on the tip of the cathode, flush with the exit plane of the anode. This enables the plasma plume to efficiently accelerate away from the thruster, eliminating the need for an additional ion acceleration stage. The ISF-VAT feeding mechanism is computer controlled and offers reliable operation of the thruster over a large number of pulses. Characterization of the ISF-VAT performance is presented, conducted on an experimental prototype in the Aerospace Plasma Laboratory, Technion. Measurement results of the mass flow rate, electrical parameters of the discharge, and thrust are presented. Using a Ti cathode at a discharge power of 3 W, a mass flow rate of ≈1.8×10 kg/s and a thrust level ≈ 7 μN were measured. More than 10 pulses were demonstrated in a single run, accumulating a total impulse of 0.2 Ns. The thruster prototype dimensions are 15 × 15 × 65 mm and are ≈ 60 g in mass.

摘要

本文介绍了一种用于纳米卫星应用的新型微推进装置——内联螺旋进料真空电弧推进器(ISF-VAT)。该推进器将传统的“无触发”点火几何结构与一种能维持稳态放电性能的进料机构相结合。进料机构对中心阴极棒实施螺旋作用。以预定速率,可实现阴极尖端的完全且均匀侵蚀以及绝缘涂层的“修复”。阴极的内联进料迫使电弧在阴极尖端出现,与阳极出口平面齐平。这使得等离子体羽流能够有效地从推进器加速离开,无需额外的离子加速阶段。ISF-VAT进料机构由计算机控制,并能在大量脉冲下使推进器可靠运行。文中展示了在以色列理工学院航空航天等离子体实验室的实验原型上对ISF-VAT性能的表征。给出了质量流率、放电电参数和推力的测量结果。在3W的放电功率下使用钛阴极时,测得质量流率约为(1.8×10)kg/s,推力水平约为7μN。单次运行展示了超过10个脉冲,累积总冲量为0.2Ns。推进器原型尺寸为15×15×65mm,质量约为60g。

相似文献

1
Inline screw feeding vacuum arc thruster.内联螺旋馈送真空电弧推力器。
Rev Sci Instrum. 2017 Apr;88(4):043505. doi: 10.1063/1.4979706.
2
An ion thruster internal discharge chamber electrostatic probe diagnostic technique using a high-speed probe positioning system.一种使用高速探针定位系统的离子推力器内部放电室静电探针诊断技术。
Rev Sci Instrum. 2008 Jan;79(1):013302. doi: 10.1063/1.2800772.
3
A 100 KW Class Applied-field Magnetoplasmadynamic Thruster.一台100千瓦级应用场磁等离子体动力推进器。
J Vis Exp. 2018 Dec 22(142). doi: 10.3791/58510.
4
Demonstration of electric micropropulsion multimodality.电微推进多模态演示。
Sci Adv. 2022 Sep 9;8(36):eadc9850. doi: 10.1126/sciadv.adc9850. Epub 2022 Sep 7.
5
Design and experimental results of a laser-ignited solid-propellant-fed magnetoplasmadynamic thruster.激光点火固体推进剂供能磁等离子体动力推进器的设计与实验结果
Rev Sci Instrum. 2020 Jul 1;91(7):074501. doi: 10.1063/5.0006603.
6
Development and research of a coaxial microwave plasma thruster.同轴微波等离子体推进器的研制与研究。
Rev Sci Instrum. 2008 Aug;79(8):083503. doi: 10.1063/1.2967340.
7
Onset of the magnetized arc and its effect on the momentum of a low-power two-stage pulsed magneto-plasma-dynamic thruster.磁化电弧的起始及其对低功率两级脉冲磁等离子体动力推进器动量的影响。
Phys Rev E. 2020 Aug;102(2-1):021203. doi: 10.1103/PhysRevE.102.021203.
8
Invited article: physical and chemical analyses of impregnated cathodes operated in a plasma environment.特邀文章:在等离子体环境中运行的浸渍阴极的物理和化学分析
Rev Sci Instrum. 2008 Nov;79(11):111301. doi: 10.1063/1.3005784.
9
Thirty percent conversion efficiency from radiofrequency power to thrust energy in a magnetic nozzle plasma thruster.磁喷管等离子体推进器中射频功率到推力能量的转换效率达30%。
Sci Rep. 2022 Nov 10;12(1):18618. doi: 10.1038/s41598-022-22789-7.
10
Velocimetry of cathode particles in a magnetoplasmadynamic thruster discharge plasma.磁等离子体动力推进器放电等离子体中阴极粒子的速度测量
Rev Sci Instrum. 2015 Jul;86(7):073513. doi: 10.1063/1.4927477.

引用本文的文献

1
Demonstration of electric micropropulsion multimodality.电微推进多模态演示。
Sci Adv. 2022 Sep 9;8(36):eadc9850. doi: 10.1126/sciadv.adc9850. Epub 2022 Sep 7.