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題 名 | 飛彈用沒入式進氣道性能分析與擇優設計=A Study on the Performance and Optimum Design of the Submerged Intake for Missile Application |
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作 者 | 謝政道; | 書刊名 | 新新科技年刊 |
卷 期 | 3 2007.01[民96.01] |
頁 次 | 頁21-31 |
分類號 | 595.95 |
關鍵詞 | 進氣道; 沒入式進氣道; 渦輪引擎; Intake; Submerged intake; Turbojet engine; |
語 文 | 中文(Chinese) |
中文摘要 | 現代吸氣式渦輪引擎飛彈進氣道有採用沒入式進氣道的趨勢,然而有關於沒入式進氣道的流場特性與性能分析的研究卻相當少。本文介紹各種不同型式的進氣道並且針對沒入式進氣道利用計算流體力學的方法進行性能分析與研究。根據NACA的設計理念完成初步設計與性能分析後發現氣流能量損耗過大,於是透過修改進氣斜坡與進氣導管來釐清沒入式進氣道流場特性與解決問題,並且透過飛行狀態與進氣道幾何外形參數變化之計算模擬結果進行性能比較加權分數的方法,擇優篩選出最佳化沒入式進氣道,以提供沒入式進氣道設計參考。 |
英文摘要 | The application of the submerged intakes has been more popular for the modern missiles which are powered by turbojet or turbofan engine; however, the investigation of the features of flow and performance are short on the submerged intake. In this article, some different types of intakes for missiles will be introduced and the submerged intake will be selected to study and analyze by computational fluid dynamics. From the study of the preliminary submerged intake which original design concept is from NACA, we find that the flow into the intake which energy loss is too much. It is necessary to understand the flow characteristics in the intake and overcome this problem by modification the intake ramp and duct shapes. Some numerical simulations of various modified intake geometries in fly conditions are obtained and the method of the performance weighting score is used to get the most optimum submerged intake. We hope this study can help someone who designs the submerged intake. |
本系統中英文摘要資訊取自各篇刊載內容。