翼載 的英文怎麼說

中文拼音 [yìzǎi]
翼載 英文
wind 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 ...
  1. In order to improve the capability of asw, navy has, preliminarily been equipped with modern anti - submarine weapons, among which helcopter serves as the core. consequently, for the formation of the powerful combat capability, there is an urgent need of building an airborne anti - submarine tactical data system ( tds ), which carries out comprehensive information processing and fulfils inflight commanding and guiding

    為了提高我軍的航空反潛水平，我軍已初步具備以旋翼飛機為核心裝備的硬體航空反潛能力，急需構建適應我軍現役搜、攻潛武器裝備的機載反潛戰術數據系統（ tds ） ，使我海軍在航空反潛方面形成強大的戰鬥力。
  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. 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。
  4. Breakthroughs in modern gyroplane technology - an introduction to the advances in gyroplane technology and the emerging market opportunities for a new generation of gyroplanes ranging from small vtol & ustol gyroplanes to large vtol gyrodyne airliners or freighters with 20 ton payload capacity

    現代旋翼機科技的突破-介紹旋科技的進步，以及新一代旋翼機的市場機會，從小型超短距離升降和垂直升降的旋翼機到可垂直升降，載重20噸以上的大型直升旋翼客機和貨運機
  5. 3. taking use of wing - fuselage fusion lifting body design technology, which not only achieves good aerodynamic characteristic, but also is good to stealth and agility to system arrange. 4

    採用翼身全融合?升力體設計技術，不僅獲得了優越的氣動性能，而且也將對隱身性能帶來好處，為總體布置和裝載帶來極大的靈活性。
  6. With additional capabilities in rotorcraft, electronic and defense systems, missiles, rocket engines, satellites, launch vehicles and advanced information and communication systems, the company ' s reach extends to customers in 145 countries

    加上旋翼飛機、電子和防禦系統、導彈、火箭發動機、衛星、運載火箭和先進信息及通訊系統等方面的研製能力，本公司的客戶已經遍及145個國家。
  7. The four - dimensional company adopts the technology of the composite to succeed in producing carrying man and plundering sea wing ship in 1998, finish trying out demonstration, has got the favorable comment of the internal and external expert

    1998年四維公司全部採用復合材料的工藝和技術成功生產出載人掠海地效翼船，完成試飛論證工作，得到了國內外專家的好評。
  8. There are two fuselage tanks and a wing tank in each inboard section, total 338 us gal ( 1, 280 liters )

    機身內有兩個油箱，機翼內段各有一個機翼油箱，共可載1280升燃油。
  9. Obviously weapons can ' t be ten times the size of their hardpoint type, this would give severe clipping errors with surrounding meshes ( unless it ' s located at a wingtip or something )

    很明顯武器不能幾倍於它們掛載點的尺寸，這將和四周的其他船體表面物件產生嚴重的網格糾纏（除非它位於翼尖或其他什麼地方） 。
  10. 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。
  11. 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。
  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. The main popular theoretical method adopted to study end - plate connection is finite element technique under monotonic loading at present. this paper applies nonlinear ( material, geometry and contact ) finite element method to analyze the behaviors of connections under cyclic load at fist time. contact elements are set between end plate and column flange, screw cap and neighborhood plane, bolt bar and hole

    對于端板連接的理論分析，目前國內外的研究主要局限在單向加載有限元分析范疇，本文首次採用三維非線性（包括材料、幾何與狀態非線性）有限元對端板連接進行了循環加載分析，端板與柱翼緣間、螺栓頭（帽）與相鄰板件間、螺栓桿與孔壁間都設置了反映邊界狀態的接觸單元。
  14. 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。
  15. 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。
  16. 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。
  17. The wing - in - ground - effect ( wig ) vehicle is a new type of high performance vehicle with many advantages such as high speed, good economics, good stealth, easy to take off or land, and so on

    地效翼船作為一種高性能的新型高速運載工具，具有經濟性好，起降方便，隱蔽性強等多種優點，具有巨大的軍事和民用應用價值。
  18. As brothers of the son of man, rise up, o men of god ! rocka my soul

    禱告之時甘甜之時，如有隻翼載我願辭，
  19. 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。
  20. 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
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