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研究生:陳宏宜
研究生(外文):Hong-Yi Chen
論文名稱:混合式火箭燃燒系統之性能與設計分析
論文名稱(外文):Performance and Design Analysis of Hybrid Rocket Combustor
指導教授:邱輝煌邱輝煌引用關係
指導教授(外文):Huei-Huang Chiu
學位類別:碩士
校院名稱:國立成功大學
系所名稱:航空太空工程學系碩博士班
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:2002
畢業學年度:90
語文別:中文
論文頁數:93
中文關鍵詞:混合式火箭
外文關鍵詞:hybrid rocket
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  • 被引用被引用:3
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近代火箭應用的範圍越來越多樣化,因此為了提昇發射能量以及次世代發射載具之發展,數種推進系統被提出來廣泛地研究,例如:固態火箭、液態火箭、混合式火箭和氣態火箭等等。而混合式火箭(Hybrid Rocket)是在這數個推進系統中擁有大量減低成本、提高安全性、可靠度及飛行性能的一種發射載具。
混合式火箭可以看成是攜帶固態燃料的液態火箭,或是攜帶液態氧化劑的固態火箭,其燃燒特徵為液態氧化劑噴入裝有固態燃料的燃燒室中與燃料氣化物進行混合後點火燃燒,產生的高溫高壓之燃氣再經由噴嘴噴出產生飛行時所需之推力。由於混合式火箭結合了固態火箭及液態火箭的特性,混合式火箭也因此擁有許多特點,如:便宜、簡單、安全、對環境影響低等優點。
本文主要目的是利用數值模擬方法針對混合火箭燃燒室進行數值模擬,並與實驗所量測之數據做分析比對,以確定合理性。由於在燃燒室的數值模擬與理論分析上,已經累積相當多的研究成果,尤其是固態燃料之退縮率(Regression rate)。因此本研究將試圖改變氧化劑噴入燃燒室之速度與壓力來做探討;另外藉由改變氧化劑流量,來觀察固態燃料退縮率之變化情形。於固態燃料之平均退縮率圖中可知由數值計算之退縮率與實驗量測之退縮率,其吻合度相當良好。
Hybrid rocket offers many advantages which merit practical application as potential space propulsion systems and has been studies over the past decades. The hybrid rocket propulsion system concept in which one component of the propellant is stored in liquid phase while the other is stored in stored in solid phase. Such systems most commonly employ a liquid oxidizers and solid fuel. But in our study, we use gaseous oxygen as the oxidizer.
In hybrid rocket combustor concept, oxidizer is injected in to a precombustion or vaporization chamber upstream of the primary fuel grain. The fuel grain contains numerous axial combustion ports that generate fuel vapor to react with the injected oxidizer. An aft mixing chamber is employed to ensure that all fuel and oxidizer are burned before exiting the nozzle. The main advantages of a hybrid rocket are : (1) safety during storage and fabrication ; (2) start-stop-restart capabilities ; (3) relatively low system cost ; (4) higher specific impulse than solid rocket and higher density-specific impulse than liquid rocket.
In our study, we will use numerical simulation method to analyze the hybrid rocket combustor. The numerical simulation conceives that a pipe with solid fuel surrounded and inlet flow is oxidant with high temperature. The inlet flow is turbulent. After obtain the flow information of the flow field, we can realize what parameters and mechanisms will effect the regression rate.
中文摘要
英文摘要
誌謝
目錄
表目錄
圖目錄
符號說明
第一章 導論
1-1 序論
1-2 研究動機
1-3 文獻回顧
1-4 本文概述
第二章 燃燒流場物理及數學模式
2-1 簡介
2-2 數學及物理模式
2-2-1 數學模式
2-2-2 物理模式
第三章 數值方法
3-1 簡介
3-2 格點系統
3-3 流場數值推導計算
3-4 收斂標準
3-5 求解步驟
第四章 結果與討論
4-1 燃燒室行為分析
4-2 流場資訊分析
第五章 結論與建議
第六章 未來工作
附錄A
參考文獻
附表
附圖
自述
著作權聲明
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