翼型曲面 的英文怎麼說
中文拼音 [yìxíngqūmiàn]
翼型曲面
英文
airfoil camber-
Some typical schemes are implemented via this data structure ( loop subdivision, catmull - clark subdivision, do - sabin subdivision, hybrid subdivision, adaptive subdivision ). the technique of opengl is utilized to accomplish some basic operations, such as rotation, zoom, pan, pick and so on. finally the algorithms studied by our research group are integrated, and a prototype system based on subdivision surface is developed
（ 4 ）改進了適合於曲面細分的的翼邊數據結構，並實現了典型的細分演算法（ loop細分、 catmullclark細分、 doo - sabin細分、混合細分、自適應細分） ；採用opengl技術實現了旋轉、縮放、平移、拾取等圖形的基本幾何操作；最後將本課題組研究成果加以集成，開發了一個基於細分曲面的原型系統。Firstly, the paper analyzes the basic airfoil profile in theory. its forepart adopts ellipse column shape and its back - end adopts plane shape. simultaneously, the 3d parametrizing model is set up
首先，本文是從理論上對基準翼型進行了分析，前段曲線部分採用橢圓柱結構，后緣部分採用平面結構，建立了飛機機翼的三維參數化模型。In this paper the direct iterative surface curvature ( disc ) design method is presented for designing airfoils at transonic speeds
本論文採用直接表面曲率迭代方法（ disc ）進行跨聲速翼型設計。On the assumption of ignoring the distortion of thickness, this paper determines the rough shape by the geometric modeling method of equal area developing using mixed mesh cell of triangle and quadrangle for the first time, presents the equal area developing arithmetic of quadrangle - triangle. on the virtual geometric symmetry axis, we puts forward the method of determining the developed coordinate of the point on the base band in the development of using regular quadrangle cell, determines the developed shape of internal structure in plane utilizing point - to - point mapping theory. furthermore, we realize the approximate developing of undeveloped - irregular boundary surface using a few triangle cells
本文結合型號研製中小曲率機翼整體壁板類零件坯料展開課題，基於板料厚向變形忽略不計的先驗假設，首創混合四邊形-三角形網格等面積展開的幾何模擬法確定壁板類零件毛坯外形，給出了混合四邊形-三角形網格等面積展開演算法；提出了虛擬分割線的概念，採用虛擬幾何對稱軸，給出了規整四邊形單元展開基帶上結點的計算方法；採用映射原理和求交演算法確定了壁板內部結構信息的展開定位。Lastly, previous vane are analysed by fluent, we calculate the pressure distribution chart and report chart of each wing form, then alter the torsion angle and the airfoil form of the vane respectively, finally ascertain the influence curve of the torsion angle and the airfoil form of the vane on which act the lift power
最後，通過fluent對設計出的葉片分析，得出其壓力分布圖和報告圖。然後從改變葉片的扭轉角度和翼型兩個方面分析其對升力和阻力的影響。得出葉片的扭轉角和翼型對升阻比的影響曲線，在文章的結尾部分估算了無人機的一些性能參數。After comparing between the finite - element analysis and experimental results, the author verified the fem. then according to the chinese code, the nonlinear finite model of the beam - to - column is established which are made of different size components. the responses of beam - to - column web moment connections which are made of different size components are compared and analyzed from three facets, and the conclusions about the joints behavior are drawn : thicken the connection plate, lengthen the connection plate or use a back - up stiffer can improve the connection behavior, consist of improving the behavior of load - supported and reducing the stress convergence in the flange moment plates
本文根據我國規范的有關規定，自行建立了12個不同構件尺寸的樑柱腹板連接的三維有限元模型，對不同構件尺寸的樑柱腹板剛性連接節點在單向荷載作用下的反應進行了研究，從結構的mises應力等值線示意圖、梁端加載處的荷載? ?位移曲線、翼緣連接板兩端的mises等效應力以及翼緣連接板與柱相連接的三邊的mises應力等值線示意圖四方面進行了比較與分析，從而得出了不同構件尺寸的樑柱腹板剛性連接的在受力行為上的結論：增加翼緣連接板的厚度、增加翼緣連接板的長度以及採用柱的橫向加勁肋均可以改善節點的受力性能：提高節點的承載能力；減小翼緣連接板內部與柱翼緣邊的的應力不均勻現象，從而避免試件過早地發生破壞。Second, change the diaphragm ’ s space between, retain the other thing, analyze the influence of the stress and deformation of box ? girder cross section and the beam web. based on the analysis upwards, the writer studied the rule of the influence of the stress and deformation box ? girder cross section and the beam web with different diaphragm ’ s space between. according to the results of finite element analysis, the writer puts forward some suggestions which will provide some reference for the following design
本文利用ansys有限元分析程序，對指定斷面，不同曲率的曲箱梁，建立完備的有限元模型，分別對二個方面的問題進行了分析:其一，通過對箱梁在有無跨中橫隔板時截面頂板及腹板的變形和應力分佈的對比分析，闡述了設置跨中橫隔板的重要性;其二，在相同工況下，通過改變橫隔板的設置間距，分析對箱梁翼緣及腹板的受力影響。分享友人