尾旋翼 的英文怎麼說

中文拼音 [wěixuányì]
尾旋翼 英文
tail rotor
  • 旋 : 旋Ⅰ動詞1 （旋轉） whirl 2 （用車床切削或用刀子轉著圈地削） turn sth on a lathe; lathe; pare Ⅱ名詞...
  • 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...
  • 旋翼 : helicopter rotor
  1. Also important are the rotation of the slipstream and the change of downwash at the tail.

    此外，滑流的旋轉和尾翼處下洗的變化也是重要的因素。
  2. In chapter 2, a simplified analytical model is presented for the analysis of the bvi mechanism, adopting the beddoes " prescribed wake model. by this model, the azimuthal location and miss - distance of the bvi and the radiation directivity of the bvi noise are calculated and discussed, and some conclusions are obtained

    在第二章，使用beddoes預定尾跡模型，建立了一個用於旋翼槳-渦干擾特性機理分析的簡化數學模型，分別對旋翼槳-渦干擾位置、槳-渦干擾距離和聲輻射方向性等進行了計算和分析，得出了有意義的結果。
  3. In chapter 5, a new dynamic wake model is developed by employing the rotor free - wake method in chapter 2, and is used to investigate the curve distortion during the conversion of tiltrotor aircraft between helicopter flight conditions and airplane flight conditions

    在第二章方法的基礎上，第五章建立一個傾轉旋翼動態尾跡模型，使用該模型對傾轉旋翼機傾轉過渡狀態的尾跡彎曲變形進行了研究，得出了一些結論。
  4. Enhanced unsteady and nonlinear rotor wake model for real - time flight simulation

    一種適合飛行模擬應用的非定常非線性旋翼尾跡增強模型
  5. < uk > the configuration has two tractor propellers, full - span double slotted flaps deflected 45, and a high tail. < / uk >

    < uk >實驗模型有二兩拉力螺旋槳，全翼展雙縫襟翼偏轉45 ，並有高置的水平尾翼。 < / uk >
  6. Based on the green ' s formula and the assumption of the propeller blade ' s thin sections, a lifting - surface method of propellers with the vortex lattice and equal source panel distributions on the mean camber surface has been introduced for the prediction of steady propeller ' s hydrodynamics in this paper. an approximate kurta condition was applied

    基於creen公式和薄翼理論假設導出的升力面方法，採用在螺旋槳拱弧面上分佈離散渦、源布置方法預報均勻流場中的螺旋槳的定常性能，螺旋槳尾渦面上壓力連續性條件採用近似的kutta條件處理。
  7. The configuration has two tractor propellers, full-span double slotted flaps deflected 45°, and a high tail.

    實驗模型有二兩拉力螺旋槳，全翼展雙縫襟翼偏轉45，並有高置的水平尾翼。
  8. With the helicopter upright flying sideways straight and level from left to right, as the helicopter passes in front of the pilot, apply collective and right cyclic to complete an outside loop

    保持機尾朝向操控者，由左向右開始橫向水平飛行，當直升機通過操控者的前方時，加大主旋翼的螺距並且將副翼打右舵完成一個外浸斗。
  9. With the helicopter upright flying sideways tail - in straight and level from left to right, as the helicopter passes in front of the pilot, apply collective and left cyclic to complete an inside loop

    保持機尾朝向操控者，由左向右開始橫向水平飛行，當直升機通過操控者的前方時，加大主旋翼的螺距並且將副翼打左舵完成一個內浸斗。
  10. With the helicopter flying sideways nose - out straight and level from right to left, tumble the helicopter forward while traveling sideways, use collective to maintain altitude and speed across the ground, complete at least one ( 1 ) tumble

    保持機尾朝向操控者，由右向左開始橫向水平飛行，將升降舵打降舵，控制主旋翼的螺距，使機體能保持固定的高度及橫向速度，至少完成一個前滾翻。
  11. With the helicopter flying sideways nose - out straight and level from right to left, roll the helicopter to the left ( the same direction as the helicopter is flying ), use collective to maintain altitude and speed across the ground, complete at least one ( 1 ) roll

    保持機尾朝向操控者，由右向左開始橫向水平飛行，將副翼打左舵（與橫向飛行的方向同向） ，控制主旋翼的螺距，使機體能保持固定的高度及橫向速度，至少完成一個側滾。
  12. And a pair of flaps, mounted on the stern stabilizers, enables the vehicle dive or surface in a spiral form, thus ensuring the vehicle almost directly under the support ship

    在潛水器的尾部穩定翼上裝有一對小襟翼，它可使潛水器在上浮下潛時，在母船的正下方作螺旋狀盤旋。
  13. The design of configuration and other primary structures of the helicopter have been finished. in order to analysis the stability and control of the helicopter, a flight mechanical modeling has been founded based on a single - rotor helicopter

    本文以常規單旋翼帶尾槳的直升機配平和操穩計算方法為基礎，建立了帶涵道共軸式直升機飛行動力學模型，對碟形無人直升機進行了配平和操縱性和穩定性分析計算。
  14. Based on the mechanism of slipstream interaction, described in this thesis is firstly the interaction of the propeller slipstream with the wing 、 fuselage and horizontal tail. subsequently, the changes in lift 、 drag and pitching moment are derived, giving an engineering model for the prediction of the increments in the aerodynamic characteristics caused by the interference between the propeller slipstream and the other parts of aircraft. this method offers a powerful means to the calculation of the aerodynamic interaction between the propeller and the aircraft, providing reliable data for the design of and aerodynamic calculation on propeller - powered aircraft

    本文以滑流干擾的機理為出發點，研究了螺旋槳滑流與飛機機翼、機身、平尾組合體之間的相互影響，推導出滑流引起的飛機升力、阻力和俯仰力矩的變化，給出了滑流干擾對機體氣動特性影響的工程估算方法，為研究螺旋槳與飛機部件之間的相互干擾提供了有力的工具，為以螺旋槳發動機為動力的飛機的設計和氣動計算提供可靠的依據。
  15. The superposition between the helicopter rotor induced flow and the warship airwake leads to the formation of the complex wake, which affects the helicopter ' s control response and flight safety during take - off and landing from a warship

    摘要直升機旋翼誘導流與艦船空氣尾流疊加后形成復合流場，對直升機艦上起降時的操縱響應及飛行安全有很大的影響。
  16. The test results show that the rotor induced flow changes the warship airwake and the influence of the rotor can be reduced by opening the hangar door

    結果表明，旋翼誘導速度改變了艦船尾流分佈，打開機庫門可減弱旋翼的影響。
  17. When pilots attempted to maneuver with the tail ' s rudder in the wake turbulence from a preceding aircraft, the entire vertical stabilizer separated from the airplane, sending the a300 into a death spiral

    當飛機碰上由前一架飛機所殘留的亂流，機長試圖操縱尾翼的方向舵時，就造成整個垂直平衡器與機身分離，也使得那架a300飛機?旋直下，邁向死亡。
  18. The durable semi - enclosed tail rotor gearbox protects the tail rotor gears while at the same time allowing easy inspection

    耐用的半封閉式保護尾槳尾旋翼變速箱齒輪同時允許容易查閱
  19. In order to understand the rotor / wing interaction each other, firstly, the change of the isolate rotor thrust with the collective pitch and rotate speed is tested, secondly, the change of the rotor thrust with the collective pitch, rotate speed and the wing / rotor distance is scaled, when the wing is placed underside the rotor, lastly, the pressure on the wing due to the rotor wake is scaled

    為了搞清楚它們之間的相互影響，本文首先測量孤立旋翼的拉力隨總距和轉速的變化；再測量有機翼時旋翼的拉力隨總距及轉速的變化以及隨旋翼機翼間的距離變化；最後測量旋翼尾流對機翼表面壓力的影響。
  20. The principal contributions of this dissertation are : 1. a high fidelity and real - time rotor wake inflow model was built up. based on peters - he finite states wake theory, a new influence coefficient matrix for high speed flight was derived, the modified wake model is better suitable for the flight state with a large wake skew angle

    本模型以peters - he有限狀態尾跡理論為基礎，修正了大尾跡傾斜角時的誘導速度影響系數矩陣，並結合了王氏渦流理論，導出了旋翼誘導速度垂向分量和旋轉分量的表達式，可計算平尾、尾槳和垂尾氣動中心處誘導速度各分量。
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