翼結構 的英文怎麼說

中文拼音 [yìjiēgòu]
翼結構 英文
wing cellule
  • 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...
  • 結 : 結動詞（長出果實或種子） bear （fruit）; form （seed）
  • 構 : Ⅰ動詞1 （構造; 組合） construct; form; compose 2 （結成） fabricate; make up 3 （建造; 架屋） bui...
  • 結構 : 1 （各組成部分的搭配形式） structure; composition; construction; formation; constitution; fabric;...
  1. Based on basic principles of grillage method, an improved grillage model of wide cantilevers bridge deck is brought forth and its effectiveness is verified after generalizing rules of grillage meshing and sectional characteristic

    基於梁格法的基本原理，提出了寬翼緣上部結構分析的改進梁格模型，並總結了梁格單元劃分和截面特性計算的一般方法，最後通過算例驗證了該模型和方法的有效性。
  2. If this load centroid is behind the elastic axis of the wing structure, then a nose-down twist of the main wing surface results.

    如果該載荷重心在機翼結構彈性軸之後，則引起主機翼表面前端向下的扭轉。
  3. Bat : any of various nocturnal flying mammals of the order chiroptera, having membranous wings that extend from the forelimbs to the hind limbs or tail and anatomical adaptations for echolocation, by which they navigate and hunt prey

    蝙蝠：一種翼手目的夜間飛行的哺乳動物，它們具有能從前肢伸到後肢或尾巴的膜狀翅膀，其生理結構能夠靠聲波定位，並以此導航和捕食。
  4. The philosophy that i followed thereafter was to get the wing flying controllable with an absolute minimum of additional parts.

    再往後，我所遵循的信條是，把控制機翼飛行的其它附加結構，搞得越小越好。
  5. Joined - wing configuration features diamond - shapes in both the plan and front views. the front wing is aft swept with positive - dihedral angle and the rear wing is forward swept with negative dihedral angle

    聯結翼飛機是指帶上反角的后掠前翼和帶下反角的前掠后翼聯結成菱形框架結構的飛機。
  6. In addition to, the fatigue crack between web and upper flange of welded steel crane beam on heavy duty service was discussed, and based on long - term observation and research, the author classified fatigue crack into bearing type and middle type crack along the horizontal direction. the causation, distributive law and mechanism of the crack were analyzed, and the precautions to take and the measures to remedy crack were presented. the main defacts including damage, crack, erosion and aging in structures, especially in concrete structure were introduced ; the defact mechanism was analyzed and the precautions to take were also given

    另外，作者對重級工作制焊接鋼吊車梁腹板與上翼緣連接焊縫的縱向水平疲勞裂縫進行了長期的觀察和研究，根據疲勞裂縫產生的不同機理，將其分為支點裂縫和肋間裂縫，並討論了兩類裂縫產生的原因、分佈規律、機理以及防治的措施；對工程中經常遇到的結構構件，尤其混凝土構件的幾種主要病害（損傷、裂縫、腐蝕與老化）進行了機理分析並提出了防治措施。
  7. Three structures have exhibited cracking at the ends of flange gusset plates.

    已有三個結構在翼緣節點板端部出現了裂紋。
  8. Based on the real structure of the forewing and hindwing of dragonfly, the plane geometric models of biomimetic wings are created using some cad software. then the three - dimensional finite element models of biomimetic wings are built by choosing the suitable element types and characteristic parameters

    本文基於蜻蜓真實的翅翼樣本，利用相應cad軟體分別建立了前、后翅翼的幾何結構模型，並通過選擇適當的單元類型及設定特性參數，完成三維仿蜻蜓前、后翅翼的有限元建模。
  9. 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。
  10. " the front of the car will be different, as far as the monocoque is concerned, with differently shaped sidepods, and the wing will be new too

    「只要改動將涉及單體橫造結構，前車身將會有所不同，不同的側箱結構，翼篇也將是全新的。 」
  11. Although aircraft designers and engineers continued to employ wing - warping techniques for years afterward ( especially on early monoplanes such as the bleriot xi ), ever faster flight speeds eventually led them to beef up wing structures to resist the resulting stresses

    雖然其後許多年間，飛機設計師和工程師仍繼續採用翹曲機翼設計（尤其是布雷修xi型等早期單翼機） ，但由於飛行速度不斷提升，終于迫使他們加強機翼結構，以承擔所增加的應力。
  12. In order to affirm that our ideal and project of lab ' s establishment are right, we then introduce an example about lab ' s establishment, which is about remote real - time health monitoring system for structure of an aeromodelling ' s wing

    為了驗證我們建立實驗室的框架和方案是行得通的，文章接著又研究了採用一架航模飛機作為研究對象，來建立一套監控航模飛機機翼結構的健康監控系統。
  13. In this system, we use a computer model to simulate the true aeromodelling ' s wing, and then we simulate the state of aeromodelling ' s wing under the real flying conditions by computer. moreover, we simulate two fault - models for wing ' s model, and then we get the state ' s date of wing ' s model structure when the two faults are happening

    在建立這個健康監控系統中我們採用在計算機上建立的模型來模擬航模飛機的機翼並在計算機上模擬了飛機在真實情況下的飛行受力狀態，接著我們在計算機上針對機翼模型模擬了二個故障，並計算出了在這二個故障發生時機翼結構的受力狀況。
  14. Tailless flying wing aerodynamic configuration being optimal selection in ucav general layout design

    大展弦比復合材料機翼結構建模與氣動彈性分析
  15. So, when we get the dates of stress and distortion of wing ' s model structure, which have been calculated by computer, we can simulate the dates of the real wing ' s structure, which we will get through stress sensors and distortion sensors. when we transmit those dates to the center computer through remote wireless transmission devices, the computer will analyze those dates according as scientific fault criterion. so we can carry out the remote real - time health monitoring for wing ' s structure

    這樣，我們讀取計算出的機翼結構模型在受力時的應力、變形值就可以模擬出在採用實體機翼作為研究對象時應力、變形傳感器傳回的數據，把這些數據通過遠程無線數據傳輸設備傳到數據處理計算機上採用科學的故障判據對這些數據進行處理就可以實現對機翼結構的實時遠程健康監控。
  16. 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
  17. It arrives at each grand prix fully prepared with six complete nosecone and wing sections, two for each race car and two for the spare, ready to bolt on at a moment ' s notice

    每一站比賽我們都準備6套完整的前鼻翼和小翼結構，每一個車手有2套，還有2套最為零部件為車手所共享使用。
  18. At last, considering the practical application, the preceding contents have been integrated altogether as a soft system in this paper and the design objective of the composite synthesis optimization for aircraft structures have been realized through the multilevel hybrid optimization model when a specific application of the forward - wing design has been tested

    最後本文從工程實際應用角度考慮，把上述內容通過一個具體的前掠機翼結構設計問題集成為一個軟體系統，通過多級混合優化模型，實現了本文提出的復合材料飛機結構的綜合優化設計目標。
  19. Layout optimization of aircraft wing with topology shaping sizing variables all considered

    基於雜交演算法的機翼結構布局優化設計
  20. Because of the special structure of smart rotor, the problem, online secondary path modeling, should be solved when adaptive filter is used to actively control the helicopter vibration. auxiliary random noise is one of the resolve methods

    出於智能旋翼結構的特殊性，在應用自適應濾波的方法進行主動控制時須解決次級通道在線建模問題。
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