翼梁 的英文怎麼說

中文拼音 [yìliáng]
翼梁 英文
box spar
  • 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...
  • 梁 : 名詞1 （屋架中架在柱子上的長木） beam 2 （通常也指檁） purlin 3 （橋） bridge4 （物體中間條狀隆起...
  1. In order to prove the feasibility of the control method mentioned, both the semiphysical test for the plant simulated by analogue computer and the model test for the cantilever beam are designed and finished with the study of the parameter selection in realization

    對離線建模的智能旋翼頻域神經控制方法進行了試驗驗證研究，試驗分兩種情況：以模擬計算機模擬受控對象的半物理模擬試驗與懸臂梁振動響應控制試驗，並研究了實現中的參數選擇問題。
  2. The web and flanges of the main girders were fabricated from astm a441 steel.

    主梁的腹板和翼緣用ASTMA441鋼製造。
  3. 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。
  4. It is the key of ebfs, therefore, furthermore calculation about link are carried out in this thesis, introduced achieved research, summarized the affect of link on whole capability in the first, the second, numerical calculation are proceeded on link with ansys : with the purpose of discussing yielding mode critical length of link, established five different specimens ; with the purpose of discussing the influence of h / tw of web, b / tf of flange and h / b, established eighteen different specimens ; with the purpose of discussing the affect of stiffener, established four different specimens, and elaborated the affect of stiffener on link based on achieved test researches

    因此，本文對耗能梁段進行進一步計算分析，概述耗能梁段對整體性能的影響，並利用有限元程序ansys對耗能梁段進行數值計算：針對耗能梁段的屈服類型建立5種不同長度的模型，計算討論耗能梁段屈服類型的長度劃分；針對耗能梁段腹板高厚比、翼緣寬厚比以及梁段截面形狀等因素共建立了18種模型進行計算分析；針對加勁肋對耗能梁段的作用建立了4種模型，並結合已有的試驗闡述了加勁肋對耗能梁段的影響。
  5. 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。
  6. During fabrication slots for the stringers flanges were flame cut into box girders.

    製造時，為安裝縱梁翼緣，在箱型梁中用焰割法開槽口。
  7. Cracks have been found in the flange and web splices at groove welds in at least four bridges.

    至少在四座橋梁的翼緣板和腹板拼接坡口焊縫中發現了裂紋。
  8. The initial retrofit consisted of removing the gaps between the stringer flange and floor beam by providing shims.

    最初的修復工作是通過墊片來消除縱梁翼緣和橫梁之間的間隙。
  9. Abstract : a model of self - excited ae rodynamic forces acting on a sectionof bridge deck with additional surface atta ched below the trailing edge is established

    文摘:首先建立了下風側附加翼板橋梁主梁截面的自激氣動力模型。
  10. The work in this thesis mainly includes following parts : 1. as for box girder cross section, the three - bar stimulation method under typical loads and supports has been introduced. the force and stress formulae for flanges have been derived from the three - bar method. by reasonable simplification for multi - cell box girder, the three - bar method has been applied in multi - cell box girder ' s shear lag analysis

    對于箱形截面主梁，本文介紹了三桿比擬法上、下翼板中比擬桿的計算公式，以及在典型荷載和支承的情況下翼板內各桿的應力計算公式，並對多箱式主梁截面進行合理簡化，使三桿比擬法應用於多室箱梁的剪力滯分析。
  11. Two hypothesises, different from the traditional viewpoints, about stress distribution in beam section at the connection of beam and end - plate are presented by author to determine the ultimate moment of end - plate connection

    其計算過程分為兩步： （ 1 ）計算梁受拉翼緣的極限拉力； （ 2 ）計算端板連接的極限彎矩。
  12. Elastic theory and plastic theory are adopted in the analysis of the two section composite beam. elastic theory suggests, on the condition of the same steel beam section size, the composite beam for the floorslab is suited lower flanges convertion section stiffness cuts down by 75. 1 %, elastic limit bending resistant capability cuts down by 47. 9 %, than the composite beam for the floorslab is suited on the top flange. it s conversion section stiffness is lifted 8. 0 %, elastic limit bending resistant capability is lifted 0. 20 %, than the steel beam

    彈性理論分析的結果表明，在鋼梁截面大小相同的條件下，樓板位於鋼梁下翼緣的組合梁和樓板位於鋼樑上翼緣的組合梁相比，其換算截面剛度降低75 . 1 ，梁的彈性極限抗彎承載力降低47 . 9 ，樓板位於鋼梁下翼緣的組合梁和純鋼梁相比，其換算截面剛度提高8 . 0 ，梁的彈性極限抗彎承載力提高0 . 2 。
  13. 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。
  14. In the engineering background of a suspension bridge tender project, taking the bridge and the airflow as a whole system, the effectiveness of the surface in the flutter stability of the system is studied by a multi - mode flutter analysis approach

    以某懸索橋設計方案為工程背景，把橋梁與氣流作為一系統，應用多模態顫振分析方法，研究了在主梁下風側設置翼板這種控制措施對改善該系統顫振穩定性的效果。
  15. At the top flange there would be enough slack so that no relative twist of any significant magnitude would be introduced into the girder web.

    在上翼緣處有足夠的松動，因而在主梁腹板上並不會引起很大的相對扭轉。
  16. Based on the research of influenced parameters on constant and varying depth solid web box girder before, the shear lag aroused by the parameters including width - span ratio, outstanding flange on base slab and the position of the tendons are further studied. the investigation show that shear lag values diminish along with the decease of width - span ratio and the departure from the symmetrical axis of anchor position, but outstanding flange is contrary to the former

    在前人對等截面、變截面實腹箱梁剪力滯效應影響參數研究的基礎上，本文進一步對腹板開孔的連續箱梁的寬跨比、底板翼緣伸出以及預應力錨固位置改變等參數對箱梁剪力滯的影響進行研究。
  17. Study of the accelerated corrosion tests of aluminum alloy flanges for aircraft structures

    飛機結構鋁合金翼梁緣條的加速腐蝕研究
  18. Abstract : a new method, collaborative allocation ( ca ), is proposed to solve the large - scale optimum allocation problem in aircraft conceptual design. according to the characteristics of optimum allocation in aircraft conceptual design. the principle and mathematical model of ca are established. the optimum allocation problem is decomposed into one main optimization problem and several sub - optimization problems. a group of design requirements for subsystems are provided by the main system respectively, and the subsystems execute their own optimizations or further provide the detailed design requirements to the bottom components of aircraft, such as spars, ribs and skins, etc. the subsystems minimize the discrepancy between their own local variables and the corresponding allocated values, and then return the optimization results to main optimization. the main optimization is performed to reallocate the design requirements for improving the integration performance and progressing toward the compatibilities among subsystems. ca provides the general optimum allocation architecture and is easy to be carried out. furthermore, the concurrent computation can also be realized. two examples of optimum reliability allocation are used to describe the implementation procedure of ca for two - level allocation and three - level allocation respectively, and to validate preliminarily its correctness and effectiveness. it is shown that the developed method can be successfully used in optimum allocation of design requirements. then taking weight requirement allocation as example, the mathematical model and solution procedure for collaborative allocation of design requirements in aircraft conceptual design are briefly depicted

    文摘:探討了一種新的設計指標最優分配方法- -協同分配法，用於處理飛機頂層設計中的大規模設計指標最優分配問題.分析了飛機頂層設計中的設計指標最優分配特徵，據此給出了協同法的原理並建立了數學模型.協同法按設計指標分配關系將最優分配問題分解為主系統優化和子系統優化，主優化對子系統設計指標進行最優分配，子優化以最小化分配設計指標值與期望設計指標值之間的差異為目標，進行子系統最優設計，或對底層元件（如飛機翼梁、翼肋和翼盒等）進行設計指標最優分配，並把最優解信息反饋給主優化.主優化通過子優化最優解信息構成的一致性約束協調分配量，提高系統整體性能，並重新給出分配方案.主系統與子系統反復協調，直到得到設計指標最優分配方案.兩層可靠度指標分配算例初步驗證了本文方法的正確性與可行性，三層可靠度指標分配算例證明了本文方法的有效性.最後，以重量指標分配為例，簡要敘述了針對飛機頂層設計中設計指標協同分配的數學模型和求解思路
  19. A new method, collaborative allocation ( ca ), is proposed to solve the large - scale optimum allocation problem in aircraft conceptual design. according to the characteristics of optimum allocation in aircraft conceptual design. the principle and mathematical model of ca are established. the optimum allocation problem is decomposed into one main optimization problem and several sub - optimization problems. a group of design requirements for subsystems are provided by the main system respectively, and the subsystems execute their own optimizations or further provide the detailed design requirements to the bottom components of aircraft, such as spars, ribs and skins, etc. the subsystems minimize the discrepancy between their own local variables and the corresponding allocated values, and then return the optimization results to main optimization. the main optimization is performed to reallocate the design requirements for improving the integration performance and progressing toward the compatibilities among subsystems. ca provides the general optimum allocation architecture and is easy to be carried out. furthermore, the concurrent computation can also be realized. two examples of optimum reliability allocation are used to describe the implementation procedure of ca for two - level allocation and three - level allocation respectively, and to validate preliminarily its correctness and effectiveness. it is shown that the developed method can be successfully used in optimum allocation of design requirements. then taking weight requirement allocation as example, the mathematical model and solution procedure for collaborative allocation of design requirements in aircraft conceptual design are briefly depicted

    探討了一種新的設計指標最優分配方法- -協同分配法，用於處理飛機頂層設計中的大規模設計指標最優分配問題.分析了飛機頂層設計中的設計指標最優分配特徵，據此給出了協同法的原理並建立了數學模型.協同法按設計指標分配關系將最優分配問題分解為主系統優化和子系統優化，主優化對子系統設計指標進行最優分配，子優化以最小化分配設計指標值與期望設計指標值之間的差異為目標，進行子系統最優設計，或對底層元件（如飛機翼梁、翼肋和翼盒等）進行設計指標最優分配，並把最優解信息反饋給主優化.主優化通過子優化最優解信息構成的一致性約束協調分配量，提高系統整體性能，並重新給出分配方案.主系統與子系統反復協調，直到得到設計指標最優分配方案.兩層可靠度指標分配算例初步驗證了本文方法的正確性與可行性，三層可靠度指標分配算例證明了本文方法的有效性.最後，以重量指標分配為例，簡要敘述了針對飛機頂層設計中設計指標協同分配的數學模型和求解思路
  20. Structural modifications focus on increasing the minimum life of the wing main spar ( originally set at 800 hours ) have carried through several proposed progressive stages of modification with the intention of reducing fatigue problems and providing a life extension of up to 1, 250 hours for a complete refurbishment with a newly manufactured main spar

    機體結構上的修改著重於延長主翼梁的最低壽命（ 800小時） ，以進行多次漸進式階段的改造方法來達到減少疲勞和延長壽命至1250小時的目標。
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