| 姓名 |
吳書沅(WU, SHU-YUAN)
查詢紙本館藏 |
畢業系所 |
光機電工程研究所 |
| 論文名稱 |
探空八號酬載冷流噴射減滾系統開發
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| 相關論文 | |
| 檔案 |
 [Endnote RIS 格式]
[Bibtex 格式]
 [相關文章]  [文章引用]  [完整記錄]  [館藏目錄]  至系統瀏覽論文 ( 永不開放)
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| 摘要(中) |
本論文研究利用商業現成件研製冷流噴射推進系統，並量測將其搭載在太空火箭八號的回收艙上進行飛行試驗時，可以達到姿態控制的減滾效能。
本系統由微控制器(MicroController Unit)控制，執行高壓氣源氣瓶穿刺、氣壓與溫度量測，以電磁閥開關控制噴氣與回收艙減滾控制。即時控制軟體建構在實驗室自主開發的LUTOS(Lookup Table Operating System)作業系統上。系統的氣路是由高壓氣瓶、調壓閥、絕對氣壓計、電磁閥、噴嘴和管件所組成。
系統的推力效能是利用天秤特性和負重元來量測推力、開閥時間與推力的相對關係。調壓閥的輸出壓力預設在135psia，而實際量測二次側壓力直為145psia。在一大氣壓下，單邊噴嘴推力可達0.4N，因此可對回收艙提供0.11(N*m)的減滾力矩。利用工式推導可知在高空真空環境下，單邊推力可達2.66N，減滾力矩可達0.72(N*m)。已回收艙的吊掛旋轉測試，搭配無線電模組之數據遙傳與G&G(G-Accelerometer & Gyroscope)模組的旋轉角速度量測，確認冷流噴射系統在一大氣壓環境下對探八回收艙酬載可提供70 deg/sec^2的減滾效果，並已備便可行飛行任務。 |
| 摘要(英) |
A Cold Gas Thruster System is developed for the de-spin attitute control of the re-entry capsule in Sounding Rocket 8 Project with commercial off the shelf (COTS) components. Its thrust performance is confirmed by bench and suspended spinning tests.
The system is controlled by a Micro Controller Unit (MCU) to punch open the high pressure cold gas canister, to measure the gas line pressure and system temperature, to control the thrust on and off by the solenoid valve to de-spin the re-entry capsule. The real-time control software is developed on our proprietary Lookup Table Operating System (LUTOS). And the pneumatic system consists of the high-pressure gas canister, regulator valve, absolute gas line pressure gauge, solenoid valve, gas lines, nozzles, and fittings.
The magnitude and timing performance of the thrust is measured by libra balance scale and load cell. With the regulator valve set at 135psia by the manufacturer, the actual secondary side gas line pressure measured is 145psia, 0.4N thrust force can be achieved at 1 atmosphere environment (equivalently, 2.66N in high altitude vacuum), and, therefore, 0.72(N*m) de-spin torque. Hanging the re-entry capsule on a spinning bearing, the angular deceleration of 70deg/sec^2 can be achieved. In the suspended spinning test, the data telemetry is carried out by the wireless module, while the angular velocity of the spinning is measured by the G & G (G-Accelerometer & Gyroscope) module. The tests verify the effectiveness of the system for the de-spin flight test. |
| 關鍵字(中) |
★ 冷流噴射推進器
★ 探八回收艙酬載
★ 減滾
★ 姿態控制 |
關鍵字(英) |
|
| 論文目次 |
論文摘要 I
致謝 III
目錄 IV
圖目 VI
表目 IX
縮寫及符號 X
第一章 緒論 1
1.1 研究動機與目的 1
1.2文獻回顧 2
1.3 研究構想 5
1.4論文章節 6
第二章 研究背景 7
2.1 計畫沿革 7
2.2 理論及技術基礎 9
第三章 冷流噴射系統設計 14
3.1系統需求及週邊環境: 14
3.2功能方塊: 16
3.3具體實現： 17
(1)氣路設計: 17
(2)機構設計: 24
(3)電路設計: 27
(4)軟體設計: 30
第四章 實驗設計 37
4.1實驗名稱：冷流噴射減滾性能量測實驗 37
實驗目的： 37
實驗環境條件： 37
實驗觀察重點: 37
實驗器材及設置： 37
實驗步驟： 39
實驗結論： 40
4.2實驗名稱：冷流噴射推力測試實驗 42
實驗目的： 42
實驗環境條件： 42
實驗平台介紹： 42
實驗器材及設置： 45
實驗步驟： 51
實驗數據： 53
第五章 結論 55
第六章 參考文獻 56 |
| 參考文獻 |
[1]Mueller, J. (1997). Thruster options for microspacecraft: a review and evaluation of existing hardware and emerging technologies. AIAA paper, 97, 3058.
[2]Bzibziak, R. (2000, December). Update of cold gas propulsion at Moog. InSpacecraft Propulsion (Vol. 465, p. 553).
[3]De Groot, W. (1999, December). Propulsion options for primary thrust and attitude control of microspacecraft. In COSPAR Colloquia Series (Vol. 10, pp. 200-209). Pergamon.
[4]Nguyen, H., Köhler, J., & Stenmark, L. (2002). The merits of cold gas micropropulsion in state-of-the-art space missions.
[5]Kuan, C. K., Chen, G. B., & Chao, Y. C. (2007). Development and ground tests of a 100-millinewton hydrogen peroxide monopropellant microthruster. Journal of Propulsion and Power, 23(6), 1313-1320.
[6]Kuan, C. K., Chen, G. B., & Chao, Y. C. Development of a High Test Hydrogen Peroxide (HTP) Micro-Thruster. In 20th International Colloquium on the Dynamics of Explosions and Reactive Systems.
[7] MUYBIEN ENTERPRISE CO. http://www.muybien.com.tw/index.htm
[8]陳彥廷.2013.探空火箭八號回收艙(主控電腦系統)開發.中央大學
[9]江士標. 2012.「Cold Gas 系統規格書」.未公開文件.中央大學.光機電工程研究所
[10] 黃志文：中華民國電子零件認證委員會：小型衛星的發展與運用
[11]李宗翰. 2012.Development Of Cold Gas Thruster Propulsion Test For The De-Spin Of A Sounding Rocket Recovery System.NCU
[12]李後毅.2010.Indigenous Technology Development of a Prototype Arcjet System.NCKU |
| 指導教授 |
葉則亮
|
審核日期 |
2013-8-1 |
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