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研究生:蔡照輝
研究生(外文):Jiu-Fai Tsai
論文名稱:混合式火箭的設計與性能分析
論文名稱(外文):Design and Performance Analysis of Hybrid Rockets
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
學門:工程學門
學類:機械工程學類
論文種類:學術論文
畢業學年度:87
語文別:中文
論文頁數:77
中文關鍵詞:混合式火箭固態燃料液態氧推力比推力
外文關鍵詞:Hybrid Rocketssolid fuelliquid oxidizerthrustspecific impulse
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混合式火箭具有許多優於液態及固態火箭的優點︰例如成本低、可重複啟動、可靠度及安全性佳…等等。燃燒室內部因為氧化劑的快速蒸發使燃燒火焰穩定,更可增加其使用壽命。
本研究利用先進的液滴模式及紊流模式來模擬兩相的燃燒流場,包含液滴蒸發模式、液滴交互作用模式、液滴阻力模式以及可適用於高或低雷諾數流場的紊流模式,並對固態燃料壁面蒸發的效應作修正。考慮一個圓柱形容器,在中央安置噴嘴並將液態氧化劑 緩緩噴入燃燒室中,邊界則由固態燃料 (polyethylene)所構成,利用噴霧技術進行混合反應,燃氣再經由後端噴嘴噴出,進而產生推力。在燃燒室的設計上,則必須耐高溫並且體積要小,後端噴嘴的設計,則採用底拉瓦噴嘴(De Laval)。
為了達到較高的燃燒效率,試圖改變操作條件,研究發現液滴半徑在80~120 m之間,推力會隨著液滴平均大小、噴霧角度與噴入流量增加而遞增。當流量在0.0724kg/s時,推力分布大約在240~290牛頓左右,而比推力則大約分布在340~390秒。

Hybrid rockets have more advantages than liquid and solid rockets have. These advantages include more simplicity, better safety, restartability, and lower cost for their development and operation. Rapid evaporation of oxidizer in the combustion chamber makes combustion flame stable and still extends its usage life.
This research uses advanced droplet model and turbulent model to simulate two-phase combustion field. It includes droplet evaporation model, droplet interaction model, droplet drag force model, and turbulent model which is suited for high or low Renold number field. There also corrects solid fuel evaporation effect. In a rocket, the oxidizer is injected into the chamber through the injector centrally located at the inlet of a cylindrical combustor. It mixes and burns with solid propellant polyethylene, which is lomasome of the combustion chamber and then, generates fuel vapor. It spurts out through the post-nozzle and results in thrust. The combustion chamber must be anti-hyperthermia and small, and the post-nozzle is by use of De Laval nozzle.
In order to getting higher combustion efficiency, we try to change operating conditions. There finds that thrust would increase with volume-mean droplet radius, spray cone angle and augmented inlet flow rate as droplet radius is between 80 to 120 micron. With flow rate of 0.0724kg/s, thrust ranges approximately from 240 to 290 NT and specific impulse is 340~390 sec.

中文摘要 ----------------------------------------------------------------------- i
英文摘要 -----------------------------------------------------------------------ii
誌謝 -----------------------------------------------------------------------------iv
目錄 -----------------------------------------------------------------------------v
圖目錄 --------------------------------------------------------------------------viii
符號說明 -----------------------------------------------------------------------ix
第一章 導論 ---------------------------------------------------------------1
1-1 序論 ---------------------------------------------------------------1
1-2 研究動機 ---------------------------------------------------------2
1-3 文獻回顧 ---------------------------------------------------------3
1-4 本文概要 ---------------------------------------------------------6
第二章 物理及數學模式 -----------------------------------------------7
2-1 前言 --------------------------------------------------------------7
2-2 統御方程式 -----------------------------------------------------9
2-2-1 通式 -------------------------------------------------------9
2-2-2 氣相方程式 ----------------------------------------------10
2-2-3 液相方程式 ----------------------------------------------16
2-3 物理模式 --------------------------------------------------------18
2-3-1 油滴燃燒模式 -------------------------------------------18
2-3-2 液氣間的輸送現象 -------------------------------------19
2-3-3 噴霧模式 -------------------------------------------------20
2-3-4 氣液相燃燒模式 ----------------------------------------20
2-3-5 紊流模式 -------------------------------------------------22
2-3-6 燃燒效率 -------------------------------------------------23
2-3-7 噴嘴分析 -------------------------------------------------23
第三章 數學方法 --------------------------------------------------------27
3-1 簡介 ----------------------------------------------------------------27
A. 燃燒室數值分析
3-2 氣相流場 ----------------------------------------------------------27
3-2-1 擬似速度在x方向的推導 ----------------------------27
3-2-2 壓力場的計算 -------------------------------------------30
3-2-3 壓力修正量的推導 -------------------------------------31
3-3 液相流場 ------------------------------------------------------32
3-3-1 液滴數量密度的推導 ----------------------------------32
3-3-2 液滴之速度與溫度方程式的推導 -------------------33
3-3-3 純量性質的推導 ----------------------------------------34
3-4 入口及邊界條件 ---------------------------------------------35
3-5 求解步驟 ------------------------------------------------------36
B. 噴嘴數值分析
3-6 界面分析 ------------------------------------------------------37
第四章 結果與討論 -----------------------------------------------------39
4-1 燃燒室部份 ------------------------------------------------------39
4-2 火箭性能 ---------------------------------------------------------39
4-2-1 推力分析 ---------------------------------------------------42
4-2-2 比推力分析 ------------------------------------------------44
參考文獻 ---------------------------------------------------------------------46
圖附錄 ------------------------------------------------------------------------51
附錄表 ------------------------------------------------------------------------75
自述
著作權聲明

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