翼形設計 的英文怎麼說

中文拼音 [yìxíngshèjì]
翼形設計 英文
airfoil design
  • 翼 : Ⅰ名詞1 （翅膀） the wing of a bird 2 （像翅膀的東西） the wing of an aeroplane etc : 鼻翼 wing of...
  • 設 : Ⅰ動詞1 （設立; 布置） set up; establish; found 2 （籌劃） work out : 設計陷害 plot a frame up; fr...
  • 計 : Ⅰ動詞1 （計算） count; compute; calculate; number 2 （設想; 打算） plan; plot Ⅱ名詞1 （測量或計算...
  • 設計 : devise; project; plan; design; excogitation; layout; layout work; styling
  1. The company might not be willing to part with the motorola brand, its batwing logo or the patents that underlie the devices ' operations, design and manufacturing, some of which are used by other divisions at motorola

    該公司可能不願放棄摩托羅拉品牌，蝙蝠翼形狀的標識以及作為設備運作、設計和製造基礎的專利權，而摩托羅拉的其它一些部門也在使用這些。
  2. The method of wing shape optimization of space shutlle has been developed with penalty function approach in which the objective function is the mass of the wing and the constraints are the hypersonic re - entry flight cross range, lift / drag ratio, and subsonic flight lift / drag ratio, the margin of the longitudial static stability and the magnitude of the horizontal landing speed etc

    摘要介紹了在滿足高超音速再入橫向機動航程，高超音速再入飛行時的升阻比，亞音速進場飛行時的升阻比，縱向靜穩定性裕度和水平著陸速度等飛行性能設計要求下，用罰函數法尋求使航天飛機機翼質量為最小的外形優化方法並給出了算例。
  3. The bottom edges of the endplates are mated to another winglike device, the lower main plane, which in turn is attached to the rear crash structure ? a carbon fibre cone bolted onto the gearbox

    終板末端邊緣被設計成與另一個翼狀地設備相配合，這個翼狀設備是一個較低的平面，附著在尾部碰撞結構上? ?變速箱上面的碳纖維錐形螺釘。
  4. In this thesis, four types of steel beam - rectangular cfst column connections, including normal welded flange plate ( wfp ) connection, bolted flange plate ( bfp ) connection, stiffened end plate ( sep ) connection and double split - tee plate ( dst ) connection, were designed based on the configuration of steel frame connection. total 8 models, 2 models of each kind of connections were tested under low - reversed cyclic loading at the end of cfst columns. the relationships between force and displacement at the end of columns, the relationships between the moment and rotation of the joints, degradations of strength and stiffness, ductility, failure mechanism and failure characteristics of these four connections under different axial - compression ratios were presented

    本文借鑒鋼框架節點構造，設計了四種類型矩形鋼管混凝土柱與鋼梁連接節點，包括常規栓焊（ wfp ）節點、翼緣全螺栓連接（ bfp ）節點、雙t板連接（ dst ）節點以及加勁端板連接（ sep ）節點，進行了四類節點8個模型試件在柱端低周反復荷載作用下的抗震性能試驗研究，比較了不同軸壓比下節點的滯回性能、強度與剛度退化、延性、破壞機理與破壞特徵，主要結論有： 1 、節點的位移滯回曲線與轉角滯回曲線為塊型分佈，沒有或略有捏攏現象，耗能能力強； 2 、軸壓比對節點滯回曲線有顯著影響，全部節點都有顯著的剛度退化； 3 、位移與轉角骨架曲線在峰值荷載後有較長的水平或下降段，具有良好的延性性能； 4 、從整體抗震性能上看，翼緣全螺栓連接節點、雙t板連接與加勁端板連接節點都優于常規栓焊節點，可在實際工程中加以推廣。
  5. The numerical algorithm of solving the adjoint equations for different design cases have been developed by using finite volume methodology which is usually used to solve the flow governed equation. it includes the some important aspects, such as flux formulation, wall and far - field boundary treatment methodology, dissipative term formulation, etc. after the solution of the adjoint equations is obtained, the derivatives of the cost function with respect to all the design variables can be evaluated with the same operation. this can yields a significant saving over the other gradient - based techniques when there are many design variables

    （ 3 ）進行了應用控制理論和三維歐拉方程的機翼氣動反設計研究，以及有升力約束情形下機翼跨音速減阻問題研究，分別推導了相應的共軛方程及邊界條件數學表達形式，研究與發展了三維共軛方程的有限體積數值求解方法，及相應梯度公式的數值求解方法，通過對計算網格生成、流場計算、共軛方程數值求解、梯度求解和優化演算法等多方面的有效結合，成功發展了三維機翼的氣動反設計和跨音速減阻優化設計程序，成功地進行了多個設計算例研究。
  6. This paper has mainly made a research on the aerodynamic configuration design of " w " tailless aircraft and the design idea has been presented here. according to the configuration design requirement of certain uav, aerodynamic configuration design has been carried out and two configuration projects are given out at last : forward - swept wing tailless configuration and " w " tailless configuration. the longitudinal and lateral aerodynamic characteristics are obtained by using two aided soft : ug to build up geometrical models and mgaero to calculate flow field

    本文研究了「 w 」型無尾布局的氣動外形設計，闡述了該布局的氣動設計思想，根據型無人機的總體設計技術指標，進行了氣動外形設計，提出了兩種氣動布局方案：前掠翼無尾氣動布局和「 w 」型無尾氣動布局，利用ug建模軟體和mgaero氣動分析計算軟體計算了兩種布局的縱、橫向氣動性能，分析了前掠翼前緣掠角和翼身融合對氣動性能的影響，計算結果表明， 「 w 」型氣動布局的設計思想是正確的，所設計的「 w 」型無尾氣動布局方案的氣動性能優越，超過了總體設計技術指標。
  7. Then an thorough computer modeling using finite element program with material, geometry and state triple - nonlinear taken into account is carried out on a series of influencing factors, such as comparison with npn - beam splice connection, comparison of varies designed theories, and the varying of fraction coefficient, diameter, grade, pretension and arrangement of bolts, thickness of web and flanges of beam and column, splicing location, axial loading on column, etc. lots of useful conclusions are drawn form computer modelling. finally, design and construction suggestions are given out. this study fills the black in the field of steel beam - to - column connection with cantilever beam high - strength bolted - splicing at both home and abroad

    然後，本文在考慮材料、幾何和狀態三重非線性的基礎上，對該連接形式進行了全面的計算機模擬，主要考慮了帶懸臂梁段全螺栓拼接的樑柱連接節點與無拼接的樑柱連接及翼緣對接焊接腹板拼接的連接節點的對比，各種設計方法之間的對比，以及翼緣拼接和腹板拼接的螺栓間距、直徑和數量，拼接點與梁端之間的距離，梁和柱的翼緣、腹板厚度，柱的軸力，接觸面的摩擦系數，翼緣和腹板拼接板的厚度等因素的影響。
  8. Abstract : the effects of airfoil geometric parameters on wing " s spacial and polarized scattering characteristics have been systematically revealed. the results of the study indicated that the calculating value of diffraction from trailing edge by using the formula of the straight wedge is very far from experimental results for vertical polarization, and the contribution of thickness of the trailing edge to scattering must be considered in the calculation. the scattering peak of leading edge depends only on radius of airfoil for horizontal polarization. but for vertical polarization, it depends on maximum thickness and the location of maximum thickness. engineering formulas for evaluating all scattering peaks were given in the paper. it is important for the design of low - rcs wing

    文摘:系統地揭示了翼形幾何參數對機翼的空間散射特性、極化散射特性的影響規律.研究發現，在垂直極化狀態下用理論尖劈公式計算機翼后緣繞射的計算結果與實驗結果相差甚遠.提出在垂直極化狀態下機翼后緣繞射的計算必須將后緣厚度考慮在內的見解.對於水平極化，前緣散射波峰只與前緣半徑有關；而對於垂直極化，前緣散射波峰與翼形最大厚度以及最大厚度位置有關.給出前後緣散射波峰的工程估算公式，為低雷達散射截面（ rcs ）機翼設計提供依據
  9. 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
  10. In this paper, the researching and developing situating at home and abroad on aseismic properties of the masonry structures are reviewed. aiming to the defects of the calculated formulas of the aseismatic shear strength of brick walls in the code for seismic design of building ( gb50011 - 2001 ) and the code for design of masonry structures ( gb50003 - 2001 ), through test on brick wall models between the single wall and the wall with flanges, restoring force characteristics, the behavior at failure of the brick masonry wall and the effect of longitudinal wall under cyclic horizontal loading were analyzed the aseismic capacity has increased by 31 % for wall with flanges, the rigidity and deformation of the wall has gone up greatly too. the conclusion that the effect of longitudinal wall should be comprised in the aseismatic formulas was proposed

    本文回顧了國內外關于砌體結構抗震性能的研究與發展現狀，針對建築抗震設計規范（ gb50011 - 2001 ）和砌體結構設計規范（ gb50003 - 2001 ）中墻體抗震驗算公式中的不足之處，通過單片墻和帶翼緣墻在垂直荷載和水平反復荷載作用下的對比試驗，研究了帶翼緣墻在水平反復荷載作用下的恢復力特性曲線、磚墻破壞特徵以及縱墻的影響等，翼緣墻的存在，主墻抗剪能力可以提高31 ，剛度及變形能力也均有較大提高的結論，墻體驗算公式中應當考慮縱橫墻共同作用的影響。
  11. Abstract : approximate methods for calculating aerodynamic heating rates on space shuttles are discussed. various methods are given for predicting the heating rate at axisymmetric stagnation points, general three dimensional stagnationpoints and the leading edge stagnation point of wings. numerous laminar and turbulent heating techniques for flat plates and cones are analyzed and compared. a brief review of some methods is presented to predict heating rate for winward centerline and lateral direction off the symmetry plane. the results show that the methods are simpler and can guarantee enought precision for predicting aerodynamic heating environment of space shuttles

    文摘:介紹了國內外預測航天飛機氣動加熱的工程計算方法.給出了軸對稱、非軸對稱和機翼前緣等各種外形駐點熱流密度的計算，分析和比較了平板、錐體的層流和湍流熱流密度計算的各種方法，概述了航天飛機迎風面中心線和離開中心線橫向熱流密度的計算.計算結果表明，本文方法用在航天飛機氣動熱環境初步設計中比較簡單並且有足夠精度
  12. In spite of these advantages, we should concentrate on how to extend the representation of modes, how to apply to unstructured grids, etc. and when combining pod and saa, it is necessary to know how to represent the shape and how to control the range of seeking and iteration number

    但在研究的過程中，我們發現正交分解方法也存在如下問題:如何增強基模態的表達能力，如何將該方法應用於非結構網格的計算等。在利用模擬退火演算法結合解算器進行翼型反設計時，則需要考慮如何表達幾何外形形狀，怎樣控制搜索范圍以及如何減小搜索次數等實際問題。
  13. This design has evolved from a previous version seen last year in japan, where the wave - like main profile formed part of a double - decker layout

    這個設計是從去年在日本所見到的版本中演變而來的，當時主風翼型面是呈波浪形狀的，組成了一個雙層風翼的布局。
  14. The results of test cases indicate that the flow parameters for the final design met the requirements and that the geometric parameters were fairly close to the desired values

    算例設計結果表明，最終設計翼型的流動參數和形狀參數都很接近要求的值。
  15. Mechanical standardization of semiconductor devices - general rules for the preparation of outline drawings of surface mounted semiconductor device packages - design guide for gull - wing lead terminals

    半導體器件的機械標準化.表面安裝的半導體器件封裝外形圖繪制的一般規則.海鷗翼式鉛端子的設計指南
  16. Mechanical standardization of semiconductor devices - part 6 - 1 : general rules for the preparation of outline drawings of surface mounted semiconductor device packages ; design guide for gull - wing lead terminals

    半導體器件的機械標準化.第6 - 1部分:平面式安裝半導體器件外殼外形圖繪制的一般規則.海鷗翼式鉛終端的設計指南
  17. In response to the sculptural form of the former theatre, various functions within the new wing are organized around a flexible and free - flowing promenade

    為配合舊劇場的弧形設計模式，新翼內設有一條相同弧度的長廊流暢地貫穿劇場左右兩側。
  18. Finally, a special form allows the user to prescribe any number of segments so that practical airfoils can be designed

    最後，一種特殊形式允許用戶指定任何數目的片段，可以使實際翼型設計
  19. After the airfoil is designed, the velocity distributions, airfoil shape, converged input file ( with phi2 adjusted, see details below ) and airfoil coordinates are returned for display

    翼型設計后的速度分佈、機翼形狀、匯流輸入檔案（ phi2調整細節見下文） 、翼型坐標送返展示
  20. The design method used here is relatively independent with the direct procedure of calculation of flow solver by finite volume method, other flow solvers can also be easily coupled with this design method

    本文的設計方法與正計算過程有相對的獨立性，可分別和不同的流場分析程序耦合，形成翼型設計軟體。
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