high wing aircraft 中文意思是什麼
high wing aircraft
解釋
上單翼機-
Tilt - rotor aircraft combine the vertical takeoff and landing ( vtol ) capability of helicopters with the high speed performance of turboprop airplanes. located at the tips of the wing, the prop - rotors act as helicopter rotors when flying vertically and as airplane propellers in cruising flight
傾轉旋翼飛機翼尖安裝可以傾轉的發動機短艙和旋翼系統，可以在飛行中根據需要在固定翼模式和直升機模式之間轉換，充分發揮直升機垂直起降、懸停及固定翼飛機高速巡航的優點。 -
Compared with a delta wing aircraft, the double - delta wing configuration has better aerodynamic performance at high angles of attack. an operational analysis was introduced as a method for evaluating training effectiveness of trainer aircraft. approaches to the engineering estimation of aerodynamic characteristics for aircraft with a double - delta wing configuration were studied, and the procedures for determining aircraft performance indices formulated. taking training effectiveness as the objective function and geometric parameters of the wing platform as design variables, through a numerical multivariate optimization arithmetic, the conceptual design optimization for a certain fighter trainer aircraft with double - delta wing configuration was carried out under the constraints of tactical and technical requirements and interrelated geometry. agreement of a calculation example with engineering practice indicates that the optimal design has higher training effectiveness than the baseline design, and in addition, improves the structural force - bearing conditions
雙三角翼氣動布局比三角翼飛機具有更好的大攻角空氣動力特性.引入了評估教練機訓練效能的作戰分析法，研究了雙三角機翼布局飛機空氣動力特性的工程計算途徑以及飛機性能指標的確定方法.以訓練效能作為目標函數並選取機翼平面形狀的幾何參數為設計變量，採用多變量數值尋優方法，在戰術技術指標及相關幾何約束條件下，對某高級教練機的雙三角機翼氣動布局方案進行了優化選擇.算例表明最優方案不僅比原準方案具有更高的訓練效能，還改善了結構的受力情況，與工程實踐吻合 -
Optimal layout about wing amp; amp; fuselage on bi - fuselage aircraft with high aspect ratio straight wing
大展弦比聯接翼結構重量估算 -
Combined with modem structural finite element analysis, modern structural optimization algorithms, composite structures mechanics and aeroelastic tailoring of composite wing as well as relative high performance numerical method, a system named the composite synthesis optimization for aircraft structures ( cosoas ), has been developed in this paper, which has own independent component of finite element analysis
本文結合現代結構有限元分析方法、現代結構優化演算法、復合材料結構力學、復合材料氣動彈性剪裁設計方法以及相關的高性能數值計算工具開發出了擁有自己獨立有限元程序的復合材料飛機結構綜合優化設計系統（ cosoas ） 。在內容上本文突出復合材料應用特色。
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