Please use this identifier to cite or link to this item: http://hdl.handle.net/11455/2002
標題: 衛星運載火箭之通化推進性能分析
Generalized Propulsion Performance Analysis of Satellite Rocket
作者: 袁廣麟
Yuan, Kuang-Lin
關鍵字: 噴射推進系統
Jet Propulsion Systems
通化總動力功率
通化推進功率
通化可供應推進功率
火箭
U型發射模式
推進效率
Generalized Total Kinetic Power
Generalized Thrust Power
Generalized Available Propulsion Power
Rocket
U-turn Launch Mode
Propulsive Efficiency
出版社: 機械工程學系所
引用: [1] 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. [2] 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. [3] Caceres, M., Commercial Satellites Surge Ahead, Aeroapace America, (Nov.,1998), p.24-26. [4] Komar, D. R., Air Breathing Propulsion - Research and Technology,Aeroapace America, (Dec., 1998), p.57. [5] Caceres, M., Too Many Launch Vehicles for the Market? Aeroapace America, (Feb., 1998), p.24-26. [6] Wilcanan, J. W., Fighters Vie for Future Markets, Aeroapace America, (Jan., 1998), p.24-26. [7] Wilson, J. R., Launching with Laser Light, Aeroapace America, (Mar., 1999), p.24-26. [8] Morgan, J. A. Robinson, E. Y., A Long Shot for Satellite Launch, Aerospace America, (Apr.,1998), p.32-39. [9] Bokulich, F., Space Technology - Boeing Moves Forward with Its EELV, SAE Aerospace Engineering, (Apr., 1999), p.23. [10] David, L., Incredible Shrinking Spacecraft, Aeroapace America, (Jan., 1996), p.20-24. [11] Ashley. S., Bringing Launch Costs Down to Earth, Mechanical Engineering Vol.120, No.10, (1998), p.62-68. [12] Mankins, J. C., Lower Costs for Highly Reusable Space Vehicles, Aeroapace America, (March, 1998), p.36-42. [13] Tsien H. S. and Evens, R. C., Optimal Thrust Programming for a Sounding Rocket, Journal of the American Rocket Society, Vol.21, No.5, (1951), p.635-643. [14] King, M. K., Rocket Propulsion Strategy Based on Kinetic Energy Management, Journal of Propulsion and Power, Vol.14, No.2, (1998), p.270-272. [15] Sparenberg, J. A., Hydrodynamic Propulsion and Its Optimization, (1995), Kluwer Academic Publishers, Boston. [16] Powel, S. F., IV, On the Leading Edge: Combining Maturity and Advanced Technology on the F404 Turbofan Engine, ASME Journal of Engineering for Gas Turbines and Power, Vol.113, No.1, (1991), p.1-10. [17] Lane, R. J. and Behenna, J., EJ2000- The Engine for the New European Fighter, ASME Journal of Engineering for Gas Turbines and Power, Vol.113, No.1, (1991), p.25-32. [18] 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. [19] Jhang, J. S., "MATLAB program design and application", CWEB Technology, Inc., Hsinchu, 2000. [20] Hong, W. Y., "MATLAB 7 program design", Flag Publishing, Taipei, 2005. [21] Yuan, K. L., Lee, H. J. and Lin, H, "Propulsion Superiority Analysis of U-turn Launch Mode for Satellite Rocket", Transactions of the Japan Society for Aeronautical and Space Sciences, Vol.51, No.171, May, 2008, pp.52-60. [22] Sie, S. H., "Space tourism", Flag Publishing, Taipei, 1991.
摘要: 傳統上噴射推進系統之動力功率和效率公式均以粗略、不完整、且不一致的方式呈現,使研究設計人員無法清楚瞭解各推進參數及其影響之相關性。有時在某種情況下還可能導致如本文所述推進性能降低與推進效率不彰的問題。因此我們將試圖澄清一些相關的重要概念,並嚴謹地推導出含完整物理參數之通化方程式,以追求系統更佳的推進性能表現。藉由高效率交織運輸法(interweaved transport scheme)與追蹤雷諾輸送公式(LRTE),我們成功地推導出噴射推進系統之相關方程式:如動力方程式、通化總動力功率(TKP)、通化推進功率(TP)、通化可供應推進功率(APP)及相關通化推進效率等公式,此外並考慮這些公式於不同特殊條件下之運用。為充分利用上述的推進理論,我們列舉了一些創新的推進策略如火箭U迴發射模式等。在本文中,將以木頭火箭說明該發射模式之優越性,並證明此法可將總動力功率及重力位能轉換為火箭推進動能,因此深具未來大幅提昇衛星發射火箭推進效率之潛力。
The kinetic power and efficiency equations for general jet propulsion systems are classically given in a much cursory, incomplete, and ununified format. This situation prohibits the propulsion designer from seeing the panorama of interrelated propulsion parameters and effects. And in some cases, it may lead to an energy-inefficient propulsion system design, or induce significant offset in propulsion performance as demonstrated in this study. Thus, herein we attempt to clarify some related concepts and to rigorously derive the associated generalized equations with a complete spectrum of physical parameters to be manipulated in quest of better performance. By a highly efficient interweaved transport scheme, we have derived the following equations for general jet propulsion systems: i.e., generalized total kinetic power (TKP) 1,2), generalized thrust power (TP), generalized available propulsion power (APP), and relevant generalized propulsive efficiency equation. Further, the variants of these equations under special conditions are also considered. For taking advantage of above propulsion theories, we also illustrate some novel propulsion strategies such as U-turn launch mode1). In this study, the wood rocket model is used to explain how to improve the propulsive efficiency of a rocket. We prove that the novel U-turn launch mode can convert total kinetic power and gravitational potential energy into rocket propulsive power and thus has the potential to dramatically improve the propulsive efficiency of satellite launch rocket.
URI: http://hdl.handle.net/11455/2002
其他識別: U0005-0808200814404400
文章連結: http://www.airitilibrary.com/Publication/alDetailedMesh1?DocID=U0005-0808200814404400
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