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研究生：	莊振軒 Zhuang, Zhen-Xuan
論文名稱：	火箭初步設計的GUI介面開發與應用 Development and Application of GUI Interface for Preliminary Rocket Design
指導教授：	楊憲東 Yang, Ciann-Dong
學位類別：	碩士 Master
系所名稱：	工學院 - 航空太空工程學系碩士在職專班 Department of Aeronautics & Astronautics (on the job class)
論文出版年：	2024
畢業學年度：	112
語文別：	中文
論文頁數：	153
中文關鍵詞：	火箭設計、火箭質量分配、火箭性能預估、拉格朗日乘數法、圖像化使用者介面
外文關鍵詞：	Rocket Design, Rocket Mass Distribution, Rocket performance estimates, Lagrange Multiplier Method, Graphical User Interface
相關次數：	點閱：70 下載：11
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近年來，隨著太空探索活動的增加與人造衛星不斷的輸送，火箭技術的發展受到了前所未有的關注。本研究探討了火箭設計中質量分配的優化問題，並提出讓使用者在初步設計階段，即可以更直觀便利的使用GUI介面來進行火箭質量優化分配。火箭的質量分配直接影響其達到預定軌道的能力，包括酬載的質量、推進劑質量和結構質量等。藉由應用高階數學模型和優化算法，試圖找到一種優化的質量分配方式，旨在最大化酬載質量，同時保持火箭結構的穩定性和可靠性。
本文研究首先回顧了火箭發展歷史，並討論火箭採用脫節的方式進行設計，質量分配的現有理論和方法，包括經典的齊奧爾科夫斯基火箭方程的應用。接著，我們引入了基於拉格朗日乘數法的優化方式，允許在考慮多個設計約束條件的情況下進行合理的火箭質量優化分配，以及基礎的軌道方程式，最後基於上述的數學模型，進行火箭初步設計系統的開發。其中介紹該系統的使用方法，接著，展示其應用具體功能，透過實際的火箭進行分析，驗證了該GUI在火箭初步設計中的有效性和實用性。最後，討論了該系統的潛在改進方向和未來應用前景。

In recent years, with the increase in space exploration activities and the continuous deployment of artificial satellites, the development of rocket technology has received unprecedented attention. This study explores the optimization of mass distribution in rocket design and proposes a method for users to optimize mass distribution through a GUI interface, making the preliminary design phase more intuitive and convenient. The mass distribution of a rocket directly affects its ability to reach the designed orbit, including the mass of the payload, propellant, and structural mass. By applying advanced mathematical models and optimization algorithms, we aim to find an optimized mass distribution method that maximizes payload mass while maintaining the stability and reliability of the rocket structure.
This paper first reviews the history of rocket development and discusses the current theories and methods of mass distribution in rocket design, including the application of the classic Tsiolkovsky rocket equation. Next, an optimization method based on the Lagrange multiplier method is introduced, which allows for reasonable mass distribution optimization of the rocket considering multiple design constraints, as well as the basic orbital equations. Based on the mathematical models, a preliminary rocket design system is developed. The usage of this system is introduced, followed by a demonstration of its specific functions. Through the analysis of actual rockets, the effectiveness and practicality of the GUI in the preliminary design of rockets are verified. Finally, the potential improvements and future application prospects of the system are discussed.

摘要 I
SUMMARY II
致謝 IX
目錄 X
表目錄 XIII
圖目錄 XIV
符號表 XVII
縮寫表 XX
第1章 緒論 1
     1.1 研究背景 1
     1.2 文獻回顧 4
     1.3 研究動機 8
     1.4 論文組織架構 9
第2章 火箭系統介紹 12
     2.1 座標系系統 12
          2.1.1 當地水平座標 12
          2.1.2 行星固定座標 14
          2.1.3 慣性座標 15
          2.1.4 軌道面座標 17
          2.1.5 風軸座標 20
          2.1.6 體座標 21
     2.2 推進系統 22
          2.2.1 固態火箭推進系統 27
          2.2.2 液態火箭推進系統 31
          2.2.3 混合火箭推進系統 33
     2.3 結構系統 36
          2.3.1 第1節火箭段 37
          2.3.2 節間段 38
          2.3.3 第n+1節火箭段 39
          2.3.4 整流罩 39
     2.4 自由飛行系統 40
          2.4.1 GNC系統 40
          2.4.2 通信系統 41
第3章 火箭數學模型 43
     3.1 火箭推力 43
          3.1.1 Tsiolkovsky 火箭方程式 43
          3.1.2 比衝 45
          3.1.3 總衝 46
          3.1.4 推重比 46
          3.1.5 燃燒時間 47
     3.2 火箭質量 47
          3.2.1 單節火箭 48
          3.2.2 多節火箭質量 50
     3.3 火箭速度 51
          3.3.1 理想火箭速度 51
          3.3.2 實際火箭速度 53
     3.4 火箭參數設計 61
          3.4.1 火箭質量優化分配 61
          3.4.2 火箭推力計算 64
     3.5 火箭外型設計 66
     3.6 火箭軌跡數學方程式 69
          3.6.1 火箭運動學方程式 70
          3.6.2 火箭動力學方程式 73
第4章 GUI介面開發與設計 75
     4.1 GUI 開發背景 75
          4.1.1 GUIDE 75
          4.1.2 App Designer 75
     4.2 火箭初步設計系統準備工作 76
          4.2.1 火箭質量優化 77
          4.2.2 火箭性能計算 83
          4.2.3 火箭軌跡模擬 87
第5章 火箭初步設計系統應用 91
     5.1 驗證系統的正確性 91
     5.2 三節與四節火箭結果 102
          5.2.1 HyImpulse SL1火箭 102
          5.2.2 Arianespace VEGA C火箭 106
          5.2.3 JAXA Epsilon 火箭 110
          5.2.4 CASIC Kaizhou-11 火箭 114
第6章 結論 118
     6.1 結果與討論 118
     6.2 未來研究工作 120
參考文獻 121
附錄A 理想火箭推進公式推導 123
附錄B Tsiolkovsky火箭方程式推導 125
附錄C 火箭理想速度與比衝關係 126
附錄D 拉格朗日乘數推導 130
附錄E 橢圓軌道速度推導 131
                                    

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