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研究生:唐偉珉
研究生(外文):Tang, Wei-Min
論文名稱:過氧化氫預分解混合火箭推力調控模型建立與性能驗證
論文名稱(外文):Model Development and Performance Validation of Throttleable Pre-decomposition Hydrogen Peroxide Hybrid Rocket
指導教授:趙怡欽
指導教授(外文):Chao, Yei-Chin
口試委員:許紘瑋鄭藏勝楊憲東湯敬民趙怡欽
口試日期:2024-01-12
學位類別:碩士
校院名稱:國立成功大學
系所名稱:航空太空工程學系
學門:工程學門
學類:機械工程學類
論文種類:學術論文
論文出版年:2024
畢業學年度:112
語文別:中文
論文頁數:105
中文關鍵詞:混合火箭過氧化氫預分解混合火箭控制閥推力調控混合火箭推力模型
外文關鍵詞:hybrid rocketpre-decomposition hydrogen peroxide hybrid rocketfluid control valvehybrid rocket throttling model
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混合火箭為安全、成本低的火箭形式,適合想發展火箭產業的政府部門與民間公司入門。在本研究室月球登陸器的計畫中,規劃使用推力可調整之過氧化氫預分解混合火箭,來抵銷登月器的重量。相較於固態火箭,混合火箭可以利用調整氧化劑流量的方式控制推力,但是因為混合火箭的燃燒機制,無法直接調整燃料質流率,使得混合火箭相較於液態火箭更難以精準的調控推力。
研究中利用本實驗室發展之混合火箭系統與流體控制閥進行推力調控測試,並利用測試得到的數據,建立火箭的推力調控模型,以利未來進行推力控制器的開發,同時此研究將針對推力調控範圍作探討。推力調控限制定義為在可接受的性能損失下可調整的推力範圍,造成性能下降的因素有:進入燃燒室的氧化劑燃料比例偏離理想值、操作條件改變導致燃燒效率降低等等。
混合火箭的推力調控模型可分為氧化劑供給系統模型、退縮率模型與燃燒室內彈道模型。氧化劑模型中利用管流摩擦因數、流量係數、觸媒床壓損等概念,分別對桶槽管路、控制閥與觸媒床進行建模。退縮率模型使用點火測試的實驗資料來建立,測試時改變藥柱的通道大小與氧化劑質流量,量測不同氧化劑通量下的質流率,同時觀察火箭藥柱通道直徑對火箭性能的影響。燃燒室內彈道模型中,假設燃燒室為一控制體積,燃料、氧化劑與排氣在燃燒中進出,使燃燒室的壓力與其他熱力學性質產生變化,這些性質變化利用質量守恆與能量守恆的觀點可以計算出來。最後計算各時間段的燃燒室壓力與推力,並將燃燒室狀態的變化帶入下一個時間段做計算,得到推力對時間變化的曲線。
實驗證實本研究建立之混合火箭推力調控模型在穩態時與實驗值相符,但在響應時間方面由於模型的簡化,與實際值有一些出入。最後利用實驗驗證本混合火箭系統可達到1:3.34的推力調控比例。
For its safety and cost-effectiveness, the hybrid rocket technology emerges as an alternative for government agencies and private companies seeking entry into the realm of rocket launching. In SRPL's Lunar Lander program, there is a plan to install a throttleable pre-decomposition hydrogen peroxide hybrid rocket to offset the weight of the Lunar lander. However, because of the combustion mechanism of hybrid rockets, the mass flow rate of fuel cannot be independently adjusted. This poses a challenge for achieving precise throttling in hybrid rocket systems.
This thesis involves conducting throttling tests using the hybrid rocket system and fluid control valves developed in our laboratory. Meanwhile, a throttling model of the hybrid rocket was constructed by employing models of the oxidizer feed system and the internal ballistic of the hybrid rocket combustor. Parameters for building models were obtained from several tests.
Finally, the throttling model was validated with a comparison of the throttling test. The thrust and the chamber pressure predicted by the model match the experimental results in steady regions. However, the rise times of the model and the experiment are different from one order of magnitude. After the investigation, we discovered that the transient response of this hybrid rocket system is predominantly influenced by thermal lags in solid fuel and turbulent boundary layer diffusion lags. These factors were not accounted for in the throttling model. The throttling ratio of the hybrid rocket in this study is 1:3.34.
摘要I
Extended AbstractIII
致謝XVII
目錄XIX
表目錄XXII
圖目錄XXIII
符號XXV
第一章 緒論1
1.1 研究動機1
1.2 文獻回顧2
1.2.1 混合火箭簡介2
1.2.2 過氧化氫預分解混合火箭4
1.2.3 混合火箭推力調控6
1.2.4 推力調控範圍7
1.3 研究目的8
第二章 理論分析與實驗方法9
2.1 預分解過氧化氫混合火箭設計9
2.1.1 混合火箭設計參數訂定9
2.1.2 觸媒室設計參數11
2.1.3 燃燒室設計參數11
2.2 混合火箭推力調控模型11
2.2.1 桶槽管路模型12
2.2.2 控制閥模型14
2.2.3 觸媒床模型16
2.2.4 燃燒室模型18
2.3 實驗方法與設備20
2.3.1 冷流測試23
2.3.2 觸媒床測試23
2.3.3 穩態點火與推力調控測試24
第三章 實驗結果與討論27
3.1 冷流測試結果27
3.2 觸媒床測試結果30
3.3 穩態點火測試結果32
3.3.1 桶槽管路模型建立33
3.3.2 控制閥模型建立33
3.3.3 觸媒床模型建立34
3.3.4 退縮率模型建立35
3.4 推力調控測試結果與火箭推力調控模型驗證36
3.4.1 過氧化氫預分解混合火箭之推力調控模型建立36
3.4.2 推力調控實驗結果與動態模型驗證38
3.5 混合火箭推力調控性能分析41
第四章 結論42
第五章 未來工作43
參考文獻44
附表47
附圖57
[1]趙怡欽, 許紘瑋, 陳介力, "應用過氧化氫推進與控制系統於自主微型月球登陸器之開發研究," 國科會計畫(MOST108-2221-E006-072-MY3), 2020.
[2]S. A. Whitmore, Z. W. Peterson, and S. D. Eilers, "Closed-Loop Precision Throttling of a Hybrid Rocket Motor," Journal of Propulsion and Power, vol. 30, no. 2, pp. 325-336, 2014, doi: 10.2514/1.B34924.
[3]G. Marxman and M. Gilbert, "Turbulent boundary layer combustion in the hybrid rocket," Symposium (International) on Combustion, vol. 9, no. 1, pp. 371-383, 1963/01/01/ 1963.
[4]G. Marxman, R. Muzzy, and C. Wooldridge, "Fundamentals of hybrid boundary layer combustion," in Heterogeneous Combustion Conference, 1963.
[5]K. K. Kuo and M. J. Chiaverini, Fundamentals of hybrid rocket combustion and propulsion. American Institute of Aeronautics and Astronautics, 2007, pp. 7-9, 43-45.
[6]J. S. Mok, W. J. Helms, J. C. Sisco, and W. E. Anderson, "Thermal Decomposition of Hydrogen Peroxide, Part I: Experimental Results," Journal of Propulsion and Power, vol. 21, no. 5, pp. 942-953, 2005, doi: 10.2514/1.13284.
[7]G. Moore and K. Berman, "A Solid-Liquid Rocket Propellant System," Journal of Jet Propulsion, vol. 26, no. 11, pp. 965-968, 1956, doi: 10.2514/8.7170.
[8]莫嘉傑, "預分解過氧化氫與HTPB/石蠟混合火箭之研發及測試," 碩士, 航空太空工程學系, 國立成功大學, 台南市, 2016.
[9]張家瑋, "200公斤級推力過氧化氫預分解混合火箭之研發," 碩士, 航空太空工程學系, 國立成功大學, 台南市, 2020.
[10]陳奕良, "300kgf旁通預分解過氧化氫混合火箭之研究," 碩士, 航空太空工程學系, 國立成功大學, 台南市, 2018.
[11]劉俊宏, "過氧化氫預分解混合火箭於多次點火應用之點火延遲特性探討," 碩士, 航空太空工程學系, 國立成功大學, 台南市, 2020.
[12]F. B. Mead and B. R. Bornhorst, "Certification tests of a hybrid propulsion system for the Sandpiper Target Missile," Air Force Rocket Propulsion Laboratory report AFRPL-TR-69-73, 1969.
[13]C. D. Penn and J. E. Branigan, "Preliminary flight rating tests of the HAST propulsion system," Air Force Rocket Propulsion Library TR-15-5, Edwards AFB, CA, 1975.
[14]G. Story and J. Arves, "Chapter 14: Flight Testing of Hybrid Powered Vehicles," NASA Marshall Space Flight Center, Feb, 2006.
[15]A. Ruffin, "Study and development of throttleable hybrid rocket motors," Ph.D. dissertation, University of Padova, 2018.
[16]Z. Peterson, S. Eilers, and S. Whitmore, "Closed-loop thrust and pressure profile throttling of a nitrous-oxide HTPB hybrid rocket motor," in 48th AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit, 2012, p. 4200.
[17]S. A. Whitmore, Z. S. Spurrier, S. D. Walker, and S. L. Merkley, "Throttled launch-assist hybrid rocket motor for an Airborne NanoSat Launch Platform," in 52nd AIAA/SAE/ASEE Joint Propulsion Conference, 2016, p. 4658.
[18]G. Bernard, "Development of a hybrid sounding rocket motor," M.S. thesis, Mechanical Engineering, University of KwaZulu-Natal, 2013.
[19]T. J. Velthuysen, "Closed-loop throttle control of a hybrid rocket motor," M.S. thesis, Mechanical Engineering, University of KwaZulu-Natal, 2018.
[20]W. Waidmann, "Thrust modulation in hybrid rocket engines," Journal of Propulsion and Power, vol. 4, no. 5, pp. 421-427, 1988.
[21]C. Carmicino and A. R. Sorge, "Influence of a conical axial injector on hybrid rocket performance," Journal of Propulsion and Power, vol. 22, no. 5, pp. 984-995, 2006.
[22]G. P. Sutton and O. Biblarz, Rocket propulsion elements. John Wiley & Sons, 2016.
[23]D. K. Huzel, Modern engineering for design of liquid-propellant rocket engines. AIAA, 1992, p. 113.
[24]小栗富士雄, 小栗達男, 黃癸森, 標準機械設計圖表便覽 增訂三版. 臺北市: 眾文, 2005.
[25]R. W. Fox, A. T. McDonald, P. J. Pritchard, and J. W. Mitchell, Fluid Mechanics. Wiley, 2016.
[26]L. F. Moody, "Friction factors for pipe flow," Transactions of the American Society of Mechanical Engineers, vol. 66, no. 8, pp. 671-678, 1944.
[27]"Difference between Quick Opening, Linear & Equal Percentage Control Valve characteristics." https://instrumentationtools.com/difference-between-quick-opening-linear-equal-percentage-control-valve-characteristics/
[28]M. Popp, J. Hulka, V. Yang, and M. Habiballah, "Liquid Rocket Thrust Chambers: Aspects of Modeling, Analysis, and Design," ed: American Institute of Aeronautics and Astronautics, 2004.
[29]A. F. Grant Jr, "Basic Factors Involved in the Design and Operation of Catalytic Monopropellant-Hydrazine Reaction Chambers," California Inst of Technology Pasadena Jet Propulsion Lab, 1954.
[30]O. A. Hougen and K. M. Watson, Chemical Process Principles. Part III: Kinetics and catalysis. J. Wiley & Sons, Incorporated, 1943.
[31]M. Constantine and E. Cain, Hydrogen peroxide handbook. Air Force Rocket Propulsion Laboratory, US Air Force Systems Command, 1967.
[32]C. Carmicino and A. R. Sorge, "Role of injection in hybrid rockets regression rate behaviour," Journal of propulsion and power, vol. 21, no. 4, pp. 606-612, 2005.
[33]M. A. Karabeyoglu, & Cantwell, Brian J., "Transient combustion in hybrid rockets," Ph.D. dissertation, Department of Aeronautics and Astronautics, Stanford University, 1998.
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