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題名 | 高節火箭噴嘴之數值模擬 |
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作者 | 邱慶龍; 賈澤民; | 書刊名 | 筧橋學報 |
卷期 | 2 1995.09[民84.09] |
頁次 | 頁81-93 |
分類號 | 462.17 |
關鍵詞 | 高節火箭; 噴嘴; 數值模擬; Upper-stage rocket; Nozzle; Numerical simulation; |
語文 | 中文(Chinese) |
中文摘要 | 在人造衛星的發射過程中,最後一節火箭的任務在於將衛星送入既定的最後軌道 ,而此種火箭通常採用固體燃料火箭,這是因為固體火箭製造容易,性能穩定且價錢又便宜 。通常這種高節火箭推送大造衛星發射後會採用自旋的方式作為穩定系統。在本研究中,首 先建立初步的火箭設計模式, 這模式包含燃燒室尺寸及噴嘴大小之預估,進而利用 ADI 數 值方法計算無旋轉效應的噴嘴流場,以驗證設計模式之準確性並瞭解噴嘴內流場之特性。 |
英文摘要 | During the launching processes of a satellite, the upper-stage rocket motor is used to kick the satellite into its final orbit. Usually, solid-propellant rocket is adopted as the kick motors. This is due to the reliable and economic characteristics of solid propellant rockets. solid-propellant rocket is adopted as the kick motors. This is due to the reliable and economic characteristics of solid propellant rockets. The upper-stage rocket will spin by itself during operation process, which can enhance the stability of the motor. In this research, a the oretical model is set up, which includes the combustor size, nozzle characteristics, and grain properties. An ADI numerical method is adopted to solve the model. Finally, detailed flowfield behaviors are obtained, which are helpful for the actual rocket motor design and manufacture. |
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