helicopter rotor 中文意思是什麼

helicopter rotor 解釋
直升機旋翼
  • helicopter : n 直升機。vt 用直升機載送。 helicopter sb aboard the ship 用直升機把某人送到船上。vi 乘直升機。n ...
  • rotor : n 1 【電機】轉子 〈cf stator〉; 動片，轉片。2 【航空】水平旋翼。3 【物理學】旋度。4 （風筒船的）...
  1. Many factors were considered in the algorithm such as the helicopter nonlinear flight dynamic model, the time delay of rotor wake, the air compressibility at advancing blade, the stall of retreating blade, the unsteady flapping motion of rotor blades and the aerodynamic interaction among rotor, fuselage, tail rotor and empennage

    根據這一方法可以確定為完成直升機機動飛行所需的駕駛員操縱輸入及直升機的飛行速度、角速度和飛行姿態的變化歷程。
  2. Helicopter is hard to hover precisely for its bad stability. ordinarily, it is improved by flight control system, such like rotorcraft unmanned aerial vehicles which use bell bar or bell - hiller stabilizer bar. bell stabilizer bar, fixed across with teetering main rotor, consists of a bar and masses at two ends

    貝爾穩定桿由一桿與兩質量塊組成，它與貝爾直升機的蹺蹺板旋翼垂直交叉放置，這種旋翼裝置有助於加大角速度阻尼，改善貝爾直升機的穩定性，但同時也降低了操作性。
  3. Tilt - rotor aircraft combine the vertical takeoff and landing ( vtol ) capability of helicopters with the high speed performance of turboprop airplanes. located at the tips of the wing, the prop - rotors act as helicopter rotors when flying vertically and as airplane propellers in cruising flight

    傾轉旋翼飛機翼尖安裝可以傾轉的發動機短艙和旋翼系統，可以在飛行中根據需要在固定翼模式和直升機模式之間轉換，充分發揮直升機垂直起降、懸停及固定翼飛機高速巡航的優點。
  4. Model experiment and damping identification for aeroelastic stability of helicopter rotor with elastomeric lag damper

    帶粘彈減擺器旋翼系統氣彈穩定性試驗與阻尼識別
  5. As one of the basic problem of helicopter dynamics, the aeromechanical stability of the coupled rotor - body system has been paid a lot of attention

    直升機旋翼/機體耦合系統的氣動機械動穩定性問題是直升機動力學的基本問題之一，長期以來一直受到人們的普遍關注。
  6. In chapter 5, the uh - 1 model rotor, the model rotor measured in the present work and the helicopter z - 8 rotor are taken as numerical examples, the calculations on rotor noise under different flight conditions are carried out for validation purposes

    應用該模型，分別以uh - 1模型旋翼、本文試驗的模型旋翼以及z - 8直升機旋翼為算例，對不同飛行條件下的旋翼氣動噪聲進行了計算，驗證了本文的計算方法。
  7. 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。
  8. The method of eigenvalue analysis is used to investigate the ground resonance stability of the helicopter rotor / body coupled system with two connections of dampers

    採用特徵分析法計算了兩種減擺器連接形式的直升機地面共振穩定性。
  9. The unsteady flow around helicopter rotor in forward flight was numerically simulated by solving 3 - d euler ' s equations

    採用三維非定常歐拉方程數值模擬了旋翼前飛非定常流動。
  10. In addition, the services are adopting new preservation strategies to keep their aircraft flying in the middle east, where harsh environmental conditions and sand have wreaked havoc on helicopter rotor blades and aircraft engines, avionics and wiring

    除此之外，軍方正在採用新的維護計劃以保證有足夠的飛機在中東飛行，那裡惡劣的環境條件和沙塵將嚴重破壞直升機的旋漿、飛機的發動機以及航空電子設備。
  11. Along with development of tiltrotor vehicle ’ s research some theoretical productions have been appeared in some project ( aerodynamic behavior of rotor, kinetic behavior of rotor, rotor / wing aerodynamic interactions, etc. ). in order to carry on further research and experimentation of these project, national - defence science and technology helicopter rotor kinetic lab of our school begin to building tiltrotor model bench. base on need of this bench, this paper study / design pitch control system on it

    隨著對傾轉旋翼飛行器的深入研究，傾轉旋翼的氣動特性、動力學特性、旋翼/機身間的氣動干擾等課題方面已有一定的理論成果出現。為了對這些課題進行深入研究和試驗驗證，我校直升機旋翼動力學國防科技重點實驗室著手建造了傾轉旋翼模型實驗臺。
  12. 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。
  13. Develops and manufactures helicopter rotor system vibration analysis, and track and balance systems. worldwide network of vibration technical and service representatives. products serve military, commercial, and individual operators

    開發生產直升機旋翼系統校正分析、跟蹤和平衡系統。技術服務網路遍布全球。
  14. Combining cfd technology and aeroacoustic theory in time domain, the high - speed impulsive ( hsi ) noise of helicopter rotor in hover and in forward flight was predicted and investigated

    本文結合cfd （計算流體力學）技術與氣動噪聲時域理論，求解直升機旋翼懸停和前飛流場及流場氣動噪聲。
  15. Identification of helicopter rotor power transfer coefficient

    直升機旋翼功率傳遞系數確定方法
  16. Abstract : the radar echo of a helicopter rotor is modeled and analyzed theoretically at first, then a new method is proposed to detect hovering helicopter by using low - pass filter and multilevel hypothesis examination

    文摘:首先對直升機旋翼的雷達回波進行建模和分析，在此基礎上提出一種懸停直升機積累檢測新方法即低通濾波和多級假設檢驗相結合的方法。
  17. An analytical model is developed for the dynamic stability analysis of helicopter rotor / fuselage coupled systems with general connections or inter - blade connections for the nonlinear elastomeric lag dampers

    摘要建立了粘彈減擺器不同連接形式時的旋翼機體耦合動穩定性分析模型。
  18. By means of dual - time stepping method and moving grids technique, we solved the 3 - d unsteady euler ' equations for helicopter rotor in forward flight, and obtained the near - field hsi noise

    為了多槳旋翼旋轉、變距等復合運動的準確描述，採用了多塊分區運動網格技術。
  19. A new method for predicting high - speed impulsive noise generated by a helicopter rotor

    預測直升機旋翼氣動噪聲的新方法
  20. Analysis of kinematics and parameters for a nonlinear hydraulic damper of helicopter rotor

    直升機旋翼非線性液壓減擺器幾何耦合及參數影響分析
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