微衛星離子探測系統; Micro Satellite Ion Probe System

NCUIR > College of Earth Sciences > Graduate Institute of Space Science > Department of Earth Sciences > Item 987654321/47880

Please use this identifier to cite or link to this item: http://ir.lib.ncu.edu.tw/handle/987654321/47880

Title:	微衛星離子探測系統;Micro Satellite Ion Probe System
Authors:	朱宴達;Yen-Da Chu
Contributors:	太空科學研究所
Keywords:	離子探測儀;微衛星;Ion Probe
Date:	2011-07-13
Issue Date:	2012-01-05 14:11:01 (UTC+8)
Abstract:	本篇論文主要討論如何設計微衛星所使用的離子探測儀，並將實際做出的成品經過太空電漿模擬艙之測試。本酬載為第一顆由國人完全設計並自製之完整離子探測儀酬載。設計過程包括外型設計與製作、電路設計、程式撰寫、量測校正以及實驗驗證均是在國內進行。本篇論文中此系統於太空電漿模擬艙配合旋轉平台進行之量測離子溫度約為1675.9 ± 66.3 K；離子密度約為3.0256 ⨉ 105 ± 2.066 ⨉ 104 #cm-3，並透過校正曲線證實此系統為一優良之微電流量測系統。內容也同樣探討設計上需要改進之處，並驗證國人完整自製高性能離子探測儀之可行性。並希望未來本國之太空計畫中能夠將此架構之系統裝置於微衛星上，提供一個高性能之電漿量測系統。 This article is meanly talks about how to design a micro satellite ion probe payload, and tested in space plasma simulation chamber. This is the first complete payload designed by ourselves. The design including payload case, circuit design, programing, measuring calibration, and testing all were being done in this nation. The ion temperature and plasma density in the space plasma simulation chamber were measured by the ion probe, the temperature was about 1675.9 ± 66.3 K, and the density was about 3.0256 ⨉ 105 ± 2.066 ⨉ 104 #cm-3, and through the calibration result, it can be prove that this system is a well tiny current measuring device. And this article also talks about how to improve the design, and hope in the future, there is a chance for us to put a high performance plasma measuring payload which is based on this design.
Appears in Collections:	[Graduate Institute of Space Science] Department of Earth Sciences

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