Please use this identifier to cite or link to this item: http://hdl.handle.net/11455/1638
DC FieldValueLanguage
dc.contributor羅鴻生zh_TW
dc.contributor江俊顯zh_TW
dc.contributor.advisor李興軍zh_TW
dc.contributor.author林栩zh_TW
dc.contributor.authorLin, Hsien_US
dc.contributor.other中興大學zh_TW
dc.date2007zh_TW
dc.date.accessioned2014-06-05T11:41:18Z-
dc.date.available2014-06-05T11:41:18Z-
dc.identifierU0005-1907200610311100zh_TW
dc.identifier.citation[1] http://www.capcomespace.net/dossiers/espace_US/apollo/lanceurs/saturn5.htm [2] Lee, H. J. and Chang, C. L., “Deriving the Generalized Power and Efficiency Equations for Jet Propulsion System”, JSME International Journal, Vol.44, No.4, Nov, 2001, pp.658-667. [3] Lee, H. J. and Huang, S. C., “On the derivation Process of Reynolds Transport Equation”, the International Journal of Mechanical Engineering Education, Vol.21, No.1, 1993, pp.49-53. [4] Lee, H. J. and Chein, R. R., “Lagrangian Reynolds Transport Equation for Jet Propulsion Dynamics”, Journal of Chinese Society of Mechanical Engineers, Vol.12, No.6, 1991, pp.611-617. [5] Lee, H. J. and Lee, H. W., “Deriving the Generalized Rocket Kinetic Power Equations and Associated Propulsion Indexes”, JSME International Journal, Vol.42, No.1, 1999, pp.127-136. [6] 張智星, “MATLAB 程式設計與應用”, 清蔚科技, 新竹, 2000. [7] 洪維恩, “MATLAB 7程式設計”, 旗標出版社, 台北市, 2005. [8] 夏道師, “火箭推動淺說”, 臺灣中華書局, 1968. [9] 謝世輝, “太空旅行”, 旗標出版社, 1991年7月. [10] 李逆熵, “飛向太空”, 臺灣商務印書館, 1991. [11] Lee, H. J., Chiu, C. H. and Hsia, W. K., “Integrated Energy Method for Propulsion Dynamics Analysis of Air-Pressurized Waterjet Rocket”, Transactions of the Japan Society for Aeronautical and Space Sciences, Vol.44, No.143, May, 2001, pp.1-7.zh_TW
dc.identifier.urihttp://hdl.handle.net/11455/1638-
dc.description.abstract本文以追蹤雷諾輸送公式、火箭動量方程式以及火箭通化總動力功率等先進觀念為基礎,並配合木頭火箭模型來解析火箭系統中的能量分配大小,進而說明火箭推進效率之關係,以證明顛覆傳統的U迴發射模式將火箭總動力功率及重力位能轉變為火箭動力之可行性。最後再以農神五號的第一級火箭引擎為例,輔以Matlab程式做火箭推進效能之數值模擬與分析,並從模擬結果證明以U迴模式發射太空火箭將比傳統垂直發射方式更具優勢。此一革命性的發射方式,將能大幅提升日後無人衛星運載火箭以及其他太空火箭之推進效率。而從本文中的木頭火箭相關推導可知,火箭本體不但充分利用了其自發的總動力功率,並且將m2的重力位能也充分利用,化為m1之動能,因此對火箭本體m1而言,真可謂『呷郎夠夠』!zh_TW
dc.description.abstractThis thesis is based on the concepts of Lagrangian Reynolds transport equations (LRTE), momentum, and the generalized total kinetic power for rocket. Herein, the wood rocket is used as a vivid model to explain the propulsive efficiency of rocket. And then, we will prove that the novel U-turn launch mode is workable to convert the total kinetic power and gravitational potential energy into the rocket propulsive power. Furthermore, we take the 1st stage rocket engine of Saturn V as an example to simulate and analyze its propulsive efficiency computationally with the aid of Matlab software. This simulation also proves that U-turn mode will be better than its traditional counterpart in launching the space rocket. In conclusion, this revolutionary launch mode has the potential to dramatically improve the propulsive efficiency of launch vehicles.en_US
dc.description.tableofcontents目 錄 誌謝 I 中文摘要 II 英文摘要 III 目錄 IV 圖目錄 VI 表目錄 VIII 第一章 緒論 1 1.1 研究動機 1 1.2 火箭之發展史 2 1.3 U迴發射模式之原理 3 第二章 火箭動力公式之回顧 5 2.1 追蹤雷諾輸送公式之簡介 5 2.2 火箭動量方程式之推導 6 2.3 火箭通化總動力功率之推導 8 2.4 木頭火箭之通化總動力功率印證 13 第三章 U迴模式發射火箭之推進優勢分析 20 3.1 彈簧-質量系統之能量分析 20 3.2 各質量塊所獲得彈簧能量之分析 23 3.3 彈簧k值與質量塊所獲得能量之關係 26 3.3.1 v2rel<VCV的情況 27 3.3.2 v2rel=VCV的情況 28 3.3.3 v2rel>VCV的情況 29 3.4 U迴模式發射火箭之推進效率分析 33 第四章 U迴模式發射火箭推進優勢之數值模擬 44 4.1 相關公式之列舉 44 4.2 農神五號火箭之相關數據 46 4.3 Matlab程式之模擬結果 47 第五章 結論 55 參考文獻 56 附錄 U迴軌道發射系統之Matlab程式 57zh_TW
dc.language.isoen_USzh_TW
dc.publisher機械工程學系所zh_TW
dc.relation.urihttp://www.airitilibrary.com/Publication/alDetailedMesh1?DocID=U0005-1907200610311100en_US
dc.subjectU-turn launch modeen_US
dc.subjectU迴發射模式zh_TW
dc.titleU迴模式發射衛星運載火箭之推進優勢分析zh_TW
dc.titlePropulsion Superiority Analysis of U-turn Launch Mode for Satellite Rocketen_US
dc.typeThesis and Dissertationzh_TW
item.openairecristypehttp://purl.org/coar/resource_type/c_18cf-
item.openairetypeThesis and Dissertation-
item.cerifentitytypePublications-
item.fulltextno fulltext-
item.languageiso639-1en_US-
item.grantfulltextnone-
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