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題名 | 雙節探空火箭之設計分析 |
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作者姓名(中文) | 賈澤民; 邱慶龍; | 書刊名 | 筧橋學報 |
卷期 | 1 1994.11[民83.11] |
頁次 | 頁105-130 |
分類號 | 447.75 |
關鍵詞 | 固體火箭; 彈道分析; 探空科學; Solid rocket; Ballistics; Atmosphere science; |
語文 | 中文(Chinese) |
中文摘要 | 固體探空火箭因為具有簡單、經濟、且較高安全性及可靠度等特性,成為在眾多 探空推進系統中最為廣泛使用的推進載具。為因應國家航太科技的推動,本文提出雙節探空 火箭的設計與分析,藉此輔助奠定探空研究的基礎。本文以現有的固體火箭設計方法加以改 良,並加入飛行彈道分析使結果更符合實際任務要求。由初步設計的結果與實際火箭比較, 發現( 1 )在設計方法上的改良是正確的,( 2 )空氣阻力及大氣密度的變化必須考慮, ( 3 )經與國外實際探空火箭數據比較,其誤差甚小。 因此在火箭彈道性能分析上,本文 所提出的計算方法是簡便及可信賴的。而在結構應力分析方面,利用有限元素法求解固體火 箭在燃燒過程中,承受內部高溫及高壓變化時,其固體推進劑與箭身之應力與應變的變化, 以及推進劑的變形情況,由計算所得的結果相當符合要求。 |
英文摘要 | Solid rocket has been widely used as a space propulsion vehicle, which is due to its simple, economic, and reliable characteristics. The purpose of this paper is to design a two-stage solid sounding rocket, and based on the results to build up the fundamental capability in atmosphere science research. In ballistic analysis, the theoretical model has been improved based on some realistic consideration of the ballistic parameters, such as the drag of the air, the density variation of the air, and gravity effect, etc. In comparison with the theoretical results and a actual sounding rocket, the deviation between them is 2.6%, which shows the ballistic model is quite accurate. In this paper, the structure analyses of the propellant grains and rocket cases are also executed. The finite-element method is used in the stress-strain analysis. Especially, the thermal effects and mechanical effects are couplely analyzed in the model. From the stress-strain results, it is found that the structure design of the sounding rocket is within the safety region. |
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