{"title":"Retarding Potential Analyzer Design and Result Analysis for Ion Energy Distribution Measurement of the Thruster Plume in the Laboratory","authors":"Ma Ya-li, Tang Fu-jun, Xue Yu-xiong, Chen Yi-feng, Gao Xin, Wang Yi, Tian Kai, Yan Ze-dong","volume":71,"journal":"International Journal of Aerospace and Mechanical Engineering","pagesStart":2539,"pagesEnd":2543,"ISSN":"1307-6892","URL":"https:\/\/publications.waset.org\/pdf\/12556","abstract":"
Plasma plume will be produced and arrive at spacecraft when the electric thruster operates on orbit. It-s important to characterize the thruster plasma parameters because the plume has significant effects or hazards on spacecraft sub-systems and parts. Through the ground test data of the desired parameters, the major characteristics of the thruster plume will be achieved. Also it is very important for optimizing design of Ion thruster. Retarding Potential Analyzer (RPA) is an effective instrument for plasma ion energy per unit charge distribution measurement. Special RPA should be designed according to certain plume plasma parameters range and feature. In this paper, major principles usable for good RPA design are discussed carefully. Conform to these principles, a four-grid planar electrostatic energy analyzer RPA was designed to avoid false data, and details were discussed including construction, materials, aperture diameter and so on. At the same time, it was designed more suitable for credible and long-duration measurements in the laboratory. In the end, RPA measurement results in the laboratory were given and discussed.<\/p>\r\n","references":"[1] M. Perdu, D. Borie, F. Sainct, Th. Grassin, In Orbit Experimental Package\r\nFor Electric Propulsion Interaction, 46th International Astronautical Congress, October 2-6, 1995\/ Oslo, Norway.\r\n[2] Lyon Bradley King, Ph.D. Thesis, Transport-property and Mass Spectral\r\nMeasurements in the Plasma exhaust Plume of a Hall-Effect Space Propulsion system [D].University of Michigan, Department of Aerospace\r\nEngineering, 1998.\r\n[3] M. Capacci, G. Matticari, G. Noci and A. Severi, An Electric Propulsion\r\nDiagnostic Package for the Characterization of the Plasma Thruster\/Spacecraft Interactions on STENTOR Satellite, AIAA 99-2277,\r\n35th AIAAIASMEISAEIASEE Joint Propulsion Conference and Exhibit 20-24 June 1999.\r\n[4] Timothy Glover, Ph.D. Thesis, Measurement of Plasma Parameters in the\r\nExhaust of a Magnetoplasma Rocket by Gridded Energy Analyzer and\r\nEmissive Langmuir Probe(D). RICE UNJVERSITY, 2002.4.\r\n[5] Green, T. S., Plasma Physics, Vol. 12, 1970, p. 877.\r\n[6] Christian B\u00f6hm and J\u00e9r\u251c\u2524me Perrin, Retarding-field analyzer for\r\nmeasurements of ion energy distributions and secondary electron emission coefficients in low-pressure radio frequency discharges,\r\nRev.Sci.Instrum., Vol.64, No.1, January 1993, P31-p44.\r\n[7] Colleen M. Marrese, Neha Majumdar, James M. Haas, George Williams, Lyon B. Ring, Alec D. Gallimore, Development of a\r\nSingle-orifice Retarding Potential Analyzer for Hall Thruster Plume\r\nCharacterization, IEPC-97-066.","publisher":"World Academy of Science, Engineering and Technology","index":"Open Science Index 71, 2012"}