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| DC 欄位 | 值 | 語言 |
|---|---|---|
| dc.contributor.advisor | 江茂雄(Mao-Hsiung Chiang) | |
| dc.contributor.author | Chi-Feng Sung | en |
| dc.contributor.author | 宋奇峰 | zh_TW |
| dc.date.accessioned | 2021-07-10T22:08:34Z | - |
| dc.date.available | 2021-07-10T22:08:34Z | - |
| dc.date.copyright | 2018-08-10 | |
| dc.date.issued | 2018 | |
| dc.date.submitted | 2018-08-08 | |
| dc.identifier.citation | [1] 國家太空中心. [Online]. Available: http://www.nspo.narl.org.tw/
[2] E. Erdem, 'Thrust Vector Control by Secondary Injection ' The Graduate School of Natural and Applied Sciences, September 2006. [3] 楊月誠, '火箭發動機理論基礎,' 西北工業大學出版社, 2010. [4] C. D. Brown, 'Spacecraft Propulsion,' AIAA, Inc., 1995. [5] D. Mccloy and H. R. Martin, 'Control of Fluid Power: Analysis and Design,' John Wiley & Sons, 1980. [6] 張利平, '液壓閥原理、使用與維護,' 化學工業出版社, 2005. [7] J. E. Broadwell, 'Analysis of Fluid Mechanics of Secondary Injection for Thrust Vector Control,' AIAA Journal, vol. 1, pp. 1067-1075, 1963. [8] H. Ko and W. Yoon, 'Performance Analysis of Secondary Gas Injection into aConical Rocket Nozzle,' Propulsion and Power, vol. 18, pp. 585-591, 2002. [9] G. Masuya, N. Chinzei, and S. Ishii, 'Secondary Gas Injection into a Supersonic Conical Nozzle,' AIAA Journal, vol. 15, pp. 301-302, 1977. [10] C. L. Martin and L. B. Powers, 'Feasibility Study of LITVC for Shuttle SRB,' NASA Technical Paper 1912, 1981. [11] I. Zeierman and Y. Manheimer-Timnat, 'Full Control of Solid Propellant Rockets by Secondary Injection,' Spacecraft and Rockets, vol. 10, 1973. [12] J. Tsohas, L. J. Droppers, E. Glenn Case IV, E. M. Dambach, S. D. Heister, 'Progress in Technology Demonstration for a Small Hybrid Launch Vehicle,' AIAA 5th Responsive Space Conference, 2007. [13] J. F. Newton and F. W. Spaid, 'Interaction of Secondary Injectants and Rocket Exhausts for Thrust Vector Control,' American Rocket Society, pp. 1203-1211, August 1962. [14] M. R. Heidari and A. R. Pouramir, 'Investigation and Comparison Effects of Fluid Injection Type in Thrust Vector Control,' Applied Fluid Mechanics, vol. 9, pp. 19-26, 2016. [15] Spacerockets of Japan [Online]. Available: http://www.b14643.de/Spacerockets_1/Japan/Mu/Description/Frame.htm [16] Japan's Institute of Space and Astronautical Sciences (ISAS) [Online]. Available: www.isas.jaxa.jp/e/enterp/rockets/vehicles/mv/index.shtml [17] Titan Missile Family [Online]. Available: https://commons.wikimedia.org/wiki/File:Titan_Missile_Family.png [18] 川口淳一郎、森田泰弘、澤井秀次郎, 'Investigation on the Second Stage LITVC Attitude Control Problem of M-3SII-8 Launch,' Japan Aerospace Exploration Agency, 1995. [19] R. Akiba and M. Kohno, 'experiments with solid rocket technology in the development of M-3SII,' Acta Astronautical, vol. 13, pp. 349-361, 1986. [20] 屠善澄, '衛星姿態動力學與控制,' 宇航出版社, 2006. [21] Expansion - HVAC Tanks [Online]. Available: https://westank.com/expansion-tanks/ [22] 壓力系統中的重要角色 [Online]. Available: http://www.jetec.com.tw/E-DM/20141209_Accumulator.html [23] TESCOM Company [Online]. Available: http://www.emerson.com/catalog/en-us/tescom-20-1200 [24] V. L. Pisacane and R. C. Moore, 'Fundamentals of Space Systems,' Aerospace Engineering Department,United States Naval Academy, March,2005. [25] New Horizons Propulsion System [Online]. Available: https://mattcbergman.com/2015/07/21/new-horizons-propulsion-system/ [26] G. W. Sutton, 'Rocket Propulsion Elements,' 7th ed., John Wiley & Sons, 2001. [27] H. Greer and D. J. Griep, 'Dynamic performance of low-thrust cold gas reaction jets in a vacuum,' J. Spacecraft and Rocket, 1967. [28] H. Greer and J. D. Griep, 'Low Thrust Reaction Jet Performance,' ASME 65-WA/AUT-11, 1966. [29] L. Hui, P. Jinyun, and J. Tao, 'Research on submarine maneuverability of flooded compartment,' International Conference on Computer Technology and Development, pp. 149-152, 2009. [30] 邱逢琛、劉韋群, 'Development for a Simulation System of Submarine Maneuvering Motions by Applying Modular Mathematical Model,' NTU-ESOE Tech, 2015. [31] 劉祖源、戴余良, '潛艇應急上浮操縱運動分析與控制技術研究,' 武漢理工大學, 2007. [32] 劉輝、浦金云、李其修、吳向君, '潛艦高壓氣吹除主壓載水艙系統實驗研究,' Harbin Engineering University. | |
| dc.identifier.uri | http://tdr.lib.ntu.edu.tw/jspui/handle/123456789/77556 | - |
| dc.description.abstract | 本研究旨在發展以高壓氣體驅動液體排放系統之研究，包含衛星發射載具使用之二次噴射推力向量控制系統以及高壓氣體應用於水下載具壓載水櫃排洩系統，分別進行動態建模及模擬分析。
本文發展之二次噴射推力向量控制系統應用，基於高壓氣瓶的排放，經調壓閥控制氣體壓力輸出，並且設計氣體排放達到滿足壅塞流(Choked flow)之條件進行高壓氣瓶的設計，以達到目標所需的橫推力，本文進行其組件動態建模及模擬計算分析。 高壓氣體應用於水下載具壓載水櫃排洩系統，亦基於高壓氣瓶排放致使壓載水櫃中的海水排出水櫃，假定氣瓶內的氣體為滯止狀態並且進行管路的連接，計算其氣體排放之狀態計算，並連接到壓載水櫃計算其排水特性，由其排水特性計算各水櫃之重心改變，並且可計算其姿態的運動狀態。 本文研究高壓氣體驅動液體排放之特性，均使用Matlab/Simulink分別完成二次噴射推力向量控制系統以及高壓氣體應用於壓載水櫃排洩之系統，依照目標所需設計之組件參數進行系統動態建模以及模擬分析。 | zh_TW |
| dc.description.abstract | This study aims to develop high-pressure air driving liquid emissions systems, including the secondary injection thrust vector control system of satellite launch vehicles and the blowing system of the underwater vehicle ballast tanks.
The application of the secondary injection thrust vector control system developed in this paper is based on the discharge of the high pressure gas vessel, the gas pressure output is controlled by the pressure reducing valve, and the design of the gas discharge reaches the condition of the choked flow to design the high pressure gas vessel for achieving the required target lateral thrust. In the blowing system of the underwater vehicle ballast tanks, the pressure reducing valve in this paper is a normally open spring regulating valve, and calculates the physical model of the components; the system application of the ballast tanks also drains out of the seawater by high pressure vessel. Assume that the gas in the vessel is in a stagnation state and the pipeline is connected to the vessel for discussing the dynamic equation of gas emissions. The center of gravity change of each tank can be calculated from its drainage characteristics, and the motion state of its posture can be calculated. In this paper, the dynamic modeling and the dynamic simulation by Matlab/Simulink for the secondary injection thrust vector control system of satellite launch vehicles and the blowing system of the underwater vehicle ballast tanks were developed and verified respectively. | en |
| dc.description.provenance | Made available in DSpace on 2021-07-10T22:08:34Z (GMT). No. of bitstreams: 1 ntu-107-R05525044-1.pdf: 2916221 bytes, checksum: 2fcb1dc5243783a27828eb9a68db438b (MD5) Previous issue date: 2018 | en |
| dc.description.tableofcontents | 口試委員會審定書…………………………………………………………………….
致謝 I 摘要 II Abstract III 目錄 IV 圖目錄 VI 表目錄 IX 第一章 緒論 1 1-1 前言 1 1-2 文獻回顧 2 1-2-1 二次噴射推力向量控制系統回顧 2 1-2-2 高壓氣體應用於壓載水櫃排洩系統回顧 4 1-3 研究動機 5 1-4 本文架構 6 第二章 二次噴射推力向量控制系統 7 2-1 氣體基礎理論 9 2-2 系統架構及運作 13 2-2-1 高壓氣瓶 19 2-2-2 調壓閥 20 2-2-3 噴射劑與儲箱 23 2-2-4 推力閥 25 第三章 高壓氣體應用於壓載水櫃排洩系統 31 3-1 水櫃質量變化之影響 31 3-2 高壓氣體應用於壓載水櫃排洩系統之數學模型 34 3-3 系統動態建模 41 第四章 模擬結果與討論 42 4-1 二次噴射推力向量控制系統 42 4-1-1 系統組件動態模擬 43 4-1-2 系統動態模擬 51 4-2 高壓氣體應用於壓載水櫃排洩系統 58 4-2-1 壓載水櫃排水設計 58 4-2-2 潛艦運動模擬 69 第五章 結論 77 參考文獻 79 | |
| dc.language.iso | zh-TW | |
| dc.title | 以高壓氣體驅動液體排放特性之研究 | zh_TW |
| dc.title | Study on the Liquid Emission Characteristics Driven by High Pressure Air | en |
| dc.type | Thesis | |
| dc.date.schoolyear | 106-2 | |
| dc.description.degree | 碩士 | |
| dc.contributor.coadvisor | 陳義男(Yih-Nan Chen) | |
| dc.contributor.oralexamcommittee | 鐘清枝,陳明飛 | |
| dc.subject.keyword | 衛星發射載具,二次噴射推力向量控制系統,氣體驅動液體,高壓氣體,水下載具,壓載水櫃, | zh_TW |
| dc.subject.keyword | Satellite launch vehicle,Secondary injection thrust vector control system,Liquid emission,High pressure gas,Submarine,Ballast tank, | en |
| dc.relation.page | 80 | |
| dc.identifier.doi | 10.6342/NTU201802538 | |
| dc.rights.note | 未授權 | |
| dc.date.accepted | 2018-08-08 | |
| dc.contributor.author-college | 工學院 | zh_TW |
| dc.contributor.author-dept | 工程科學及海洋工程學研究所 | zh_TW |
| 顯示於系所單位： | 工程科學及海洋工程學系 | |
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| ntu-107-R05525044-1.pdf 目前未授權公開取用 | 2.85 MB | Adobe PDF |
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