臺灣博碩士論文加值系統

摘 要
目前國際間正在積極發展無毒性液態火箭推進劑，其中以過氧化氫最被重視，甚至被視為未來最主要的推進劑，並希望以過氧化氫逐漸取代所有有毒推進劑。過氧化氫火箭雖然早在二次大戰期間就已經開始發展，而且也有不錯的成果，只是後來被聯胺等推進劑取代，直到近幾年才又受到重視，而且發展成果相當豐碩。
本研究的目的則在於實際建造一具60磅推力的小型雙推進劑液態火箭引擎，使用的氧化劑為50%過氧化氫，燃料則為汽油，催化劑為過錳酸鉀；初步設計主要參考SS67B-3小型火箭。此一火箭是一種二階段反應的液態火箭，第一階段為過氧化氫與過錳酸鉀反應，分解產生氧氣與水，第二階段則是汽油與氧氣的燃燒反應。
現階段已完成60磅級雙推進劑液態火箭推力室的設計、製作及組裝，推力台架也已完成，液體供應系統、點火系統及量測系統也都裝設妥當，所有實驗設備都已完成聯接。目前已進行點火能量測試、過氧化氫分解反應測試及初步的點火測試。
點火測試主要在於確定適當的可點火條件，測試的條件包含汽油與過氧化氫流量比、霧化器種類、燃燒室內筒形式。在點火測試中，已有點火成功的經驗，只是火燄仍無法在燃燒室內持續燃燒，也還無法建壓。測試結果顯示在燃燒室內筒前端加一渦漩器，可提高點火的成功率，也具有穩定火燄的效果。未來仍將繼續測試可點火條件，並以產生推力為目標。

Abstract
As environmental protection and safety requirement are increased, the use of non-toxic propellants is inevitable. Hydrogen peroxide is seen to be the most powerful non-toxic propellant and will take the place of all toxic propellants gradually in future. Hydrogen peroxide rocket engine was developed during World War II, but some other more powerful rocket replaced it soon. In recent tears, hydrogen peroxide rocket engine is reemphasized.
The subject of this experimental study is to develop a subscale bipropellant liquid rocket using 50% hydrogen peroxide as oxidizer, gasoline as fuel, and potassium permanganate as catalyst. The rocket is a two-step reaction liquid rocket. The First step is the decomposition of hydrogen peroxide catalyzed by potassium permanganate, and the products of this reaction are oxygen and water. The Second step is the combustion of gasoline with oxygen from the first step.
A subscale bipropellant liquid rocket engine with 60 lb thrust has been successfully established and tested. The test facility includes thrust chamber, thrust testing stand, liquid feed system, ignition system and measurement system. In the process of testing, some parameters are changed to find suitable ignition conditions, including fuel/oxidizer ratio, types of combustion chamber, fuel injectors. The engine was successfully firing at certain conditions, but the combustion performance is not satisfied the expectancy. The flame is unable to be held in the combustion chamber, and the pressure is not established. From some successful firing experience, it seems to be helpful to stabilize and hold the flame by adding a swirler at the inlet of the combustion chamber. The future work is to improve the performance of the engine.
1.1 前言 1
1.2 文獻回顧 2
1.2.1 過氧化氫引擎之發展歷史 2
1.2.2 過氧化氫引擎之近期研究 4
雙推進劑火箭 4
觸媒床 6
自燃燃料 7
1.3 研究動機及目的 9
第二章 雙推進劑液態火箭設計 10
2.1 任務需求 10
2.2 性能估算 10
2.2.1 燃料/氧化劑混合比 11
2.2.2 燃燒室溫度、壓力 11
2.2.3 比衝值 (specific impulse) 12
2.3 推力室設計 14
2.3.1 燃燒室 14
2.3.2 噴嘴 15
2.3.3 霧化器 15
2.3.4 點火裝置 16
第三章 實驗設備及儀器 17
3.1 推力室 17
3.2 推力台架 18
3.3 液體供應系統 18
3.4 點火系統 20
3.5 量測系統 20
3.5.1 熱電偶(Thermocouple) 20
3.5.2 壓力傳送器(Pressure Transducer) 21
3.5.3 推力感測器(Load Cell) 21
3.5.4 資料擷取系統(Data Acquisition System) 22
第四章 實驗方法及步驟 23
4.1 實驗方法 23
4.1.1 點火能量測試 23
4.1.2 過氧化氫分解反應測試 23
4.1.2 點火測試 23
4.2 實驗步驟 24
4.1.1 實驗前準備工作 24
4.2.2 點火程序 24
4.2.3 熄火程序 25
第五章 結果與討論 26
5.1 點火能量測試結果 26
5.2 過氧化氫分解反應測試 26
5.3 點火測試 27
5.3.1 實驗一 27
5.3.2 實驗二 28
5.3.3 實驗三 29
5.3.4 實驗四 29
5.3.5 實驗五 30
5.3.6 實驗六 31
5.3.7 實驗七 32
第六章 結論 33
第七章 未來工作 34
參考文獻 35

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