翼載荷 的英文怎麼說

中文拼音 [yìzǎihé]
翼載荷 英文
wing loading
  • 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...
  • 載 : 載Ⅰ名詞（年） year : 一年半載 six to twelve months; six months to a year; 三年五載 three to five ...
  • 荷 : 荷名詞（蓮） lotus
  • 載荷 : load; loading載荷變化 load fluctuation; variation in load; 載荷裝置 load device
  1. 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。
  2. Flying boat is a controllable aircraft that can flying in the air, the flotage provided by the helum - filled bag inside the flying boat can support the boat and it s load in the air, motor pushing it forward ; the direction is guided by the device on it s tail, going down of the boat is made by escaping the gas inside, it can rise or fall straightly or stay in the air, no necessity of special site for taking off

    飛艇是一種可操縱的浮於空中的飛行器。在飛行中主要依靠內部充滿氦氣的氣囊提供的浮力，將飛艇及其載荷支持在空中，發動機為其提供前進的動力，通過操縱尾翼上的升降舵和方向舵控制飛艇的俯仰和方向運動，飛艇的下降是通過排放氣來實現的。飛艇可以垂直起降空中懸停，不需要有專用設備的起降場。
  3. The smart rotor with active trailing edge is a new system for reducing the vibration which can adjust the air load of the blade to actively counteract the main harmonic of the force to the fuselage by controlling the deflection of the trailing edge

    主動后緣附翼控制是一種較新的旋翼減振系統，它通過控制后緣附翼的偏轉，調節槳葉的氣動載荷，實現對機體激振力主要諧波分量的主動抵消。
  4. 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。
  5. 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。
  6. Pitch control system consist of three channels which is formed by three drive units. base on need of bench, drive system scheme is designed. single channel three - loop position servo system which is formed by linear motor is simulated. then kinetic behavior of rotor and system ’ s force coupling relation is analyzed. a compensation method for dynamic load which is caused by rotor rotation is presented base on structure - invarient theory

    根據實驗臺的技術要求，設計了整個驅動系統方案。對由直線電機構成的單通道三環位置伺服系統進行了設計和模擬。分析了旋翼運動的動力學特性、系統力耦合關系，並根據結構不變性原理對由旋翼運動產生的動態載荷提出了補償方法。
  7. The software designed for the system is validated by experiments and proved correct. the system can s imulate the real air - stream and put it on missile ' s wings to make them work under the same force environment as the real spread process, so the relationship of explosive stuff and attack angle can be calculated

    本文所設計的監控軟體已通過實際系統的驗證，說明整個系統的設計是合理正確的，能夠真實的模擬力矩，產生一種類似真實氣流阻力的載荷，並將其正確施加於彈翼（尾翼）上，使彈翼（尾翼）能在與展開過程中實際受力相同的狀態下工作。
  8. This thesis, which is devoted to the research on the smart rotor with actively controlled trailing - edge flap for hub oscillatory load reduction, offers a potential approach for the vibration reduction of helicopter

    本文對帶有主動控制后緣附翼的智能旋翼用於降低槳轂交變載荷進行探索性的研究，為降低直升機飛行中機體振動水平提供一條有效的新途徑。
  9. Because of the periodicity of the hub oscillatory load and the nonlinearity of the i / o relationship of the smart rotor, the neural control methods with both off - line and on - line modeling in frequency domain on the smart rotor and their realization procedures are presented

    飛行中直升機的槳轂交變載荷以周期性的為主，而智能旋翼的輸入輸出關系具有非線性特徵。據此，本文提出離線建模的和在線建模的智能旋翼頻域神經控制方法，並給出實現的具體方案細節。
  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. Problems appearing at work and tackling methods are both presented. recently, the research result has been applied to the helicopter airscrew harmony loading test. the results of harmony loading test show that it has high performance

    目前，論文的研究成果已經成功地應用在某型直升機旋翼載荷模擬加載試驗系統中，實際加載試驗表明，該加載控制系統能很好的完成加載試驗控制，保證系統的控制性能指標。
  12. Abstract : aimming at the defects of the brick masonry norm, through test on masonry wall models, the monolithic spacial effect for longitudinal and lateral walls of brick masonry buildings is studied and suggestions of calculated formulas for seismic resistance design and analysis are proposed

    文摘:針對砌體規范中墻體抗震驗算中的不足之處，通過模型磚墻試驗，研究了帶翼緣墻在水平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，並提出了在墻體抗震驗算中應當考慮縱橫墻共同作用的建議
  13. In elementary beam bending theory, it is assumed that the stresses are constant through the width of the beam. however, for the wide flange girders, the stresses are not uniform

    按照初等梁理論即假定翼緣板具有無限抗剪剛度，寬翼緣箱梁在荷載作用下翼緣的正應力沿著寬度方向上是均勻分佈的。
  14. Self - diagnosing system based on the fiber optic smart network is built, which function is force identification of wing box

    構建了基於光纖智能傳感網路的自診斷系統，實現了機翼盒段試驗件的載荷識別。
  15. The load control system has already passed the test ' s validate. it shows that the design of whole system is correct. the system can truly simulate the real air - stream and put it on missile ' s wings to make them work on the same force situation as in the real spread process, so the relationship of explosive stuff and attack angle can be confirmed

    本文所設計的加載控制系統已通過實際系統的驗證，說明整個系統的設計是合理正確的，它能夠真實地模擬類似真實氣流阻力的載荷，並施加於彈翼或尾翼，模擬其在真實工作環境下的受力狀態，可以測算導彈攻角與火工品填藥量的關系。
  16. Firstly, itis explained that the application research of smart layer. to laod detecting and simulative damage for the model of wing - box, fbg fiber smart layer and pzt smart layer are designed, and manufactured. so, those are surface - mounted respectively on the stiffened skin of aluminum alloy and carbon fiber reinforced. data acquisition system based on different signal processing technique are designed

    針對機翼盒段試件結構載荷識別和模擬損傷監測的功能要求，結合智能夾層的設計製作工藝，設計製作了基於fbg傳感器的光纖和壓電兩種智能夾層，並分別安裝在機翼盒段試件上的鋁合金和碳纖維制蒙皮上。
  17. The rayleigh - ritz method is used to lead to analytical expressions for the stiffness and mass matrices and load vector as well as their sensitivities, which uses the simple polynomials to define assumed displacement functions, geometry and construction of wing structures. excluding some selected terms from the displacement functions or using stiff springs at the specified locations imposes boundary conditions. the accuracy of calculated results is improved by including transverse shear effects and using multiple sets of ritz functions in the analysis

    它使用簡單多項式作為ritz基函數、定義翼面的幾何和結構參數，利用rayleigh - ritz方法導出翼面結構的剛度矩陣、質量矩陣和載荷向量及其靈敏度的解析表達式，通過排除位移函數中某些選定的項或在指定點使用約束彈簧施加各種邊界條件，考慮橫向剪切變形和使用多組ritz基函數改進分析的質量，使用等效蒙皮和等效夾芯技術提高計算效率。
  18. The results of research show that the rotor thrust increase 4 % and the download force on the wing can be as large as 10 percent of the total rotor thrust

    研究結果表明：旋翼的拉力大約增加4 ，旋翼的下洗載荷相當于整個旋翼拉力的10左右。
  19. An analysis method of loads on aircraft elastic wing with its real deformation considered

    方程的彈性機翼載荷分析方法研究
  20. A distributed computer control system which is used in an helicopter airscrew multi - channel harmony loading test project is introduced in this paper. the paper analyses the construct and the model of the system

    論文結合實際的工程項目，以某型號直升機旋翼氣動載荷模擬為研究內容，對加載計算機控制系統的組成、系統數學模型進行分析和研究。
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