旋翼停轉 的英文怎麼說
中文拼音 [xuányìtíngzhuǎn]
旋翼停轉
英文
rotor shutdown-
The rotor / wing aerodynamic interactions of the tilt rotor vehicle in hover is described in this dissertation
本文主要研究的是傾轉旋翼飛行器懸停狀態時，旋翼機翼之間的氣動干擾問題。When the tilt rotor vehicle is in hover, the aerodynamic download of the rotor flowfield imposes on the wing. in this time, the rotor / wing interaction is severe
傾轉旋翼飛行器懸停時，旋翼的下洗流剛好作用在機翼上，此時，旋翼機翼間的氣動干擾非常劇烈。Variable diameter rotor is an effective method to improve the aerodynamic performance of tilt - rotor in both hover and cruise state. on the basis the research before, the variable diameter tilt rotor structure design has been finish, and in virtue of the technology of virtual prototyping to simulate and analyze the kinetic, dynamic and intensity property of it
變直徑傾轉旋翼能有效的改善傾轉旋翼機懸停和巡航狀態下的氣動效率，本文提出了變直徑傾轉旋翼試驗模型設計方案，完成了可變直徑傾轉旋翼的結構設計，並利用虛擬樣機技術對變直徑傾轉旋翼的運動特性、結構動力學特性以及結構強度進行了分析、研究。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。The quantitative calculations for a rotate point source, uh - 1h rotor and ah - l / ols rotor showed that the results were in good agreements with the experimental data and other researc her ' s
文中進行了這幾種預測方法的詳盡推導和說明，並給出了旋轉點源、懸停和前飛旋翼的噪聲預測算例。The acoustic noise generated by the rotate point source, uh - 1h rotor in hover and ah - l / ols in forward flight were calculated, and the computed results from several methods were compared with each other and with the experimental data
採用旋轉點源、 uh - 1h懸停旋翼、 ah - 1 / ols前飛旋翼作為算例，對所採用的各種噪聲預測方法進行了比較。With the helicopter hovering at a safe altitude, roll the helicopter to the left, until the rotor blades are vertical, the helicopter must remain horizontal during this maneuver, drop collective and add forward cyclic
先將直升機停懸在安全的高度，然後將副翼打左舵執行1 / 4側滾，直到主旋翼回轉面成為垂直，機體必須保持水平，降低主旋翼的螺距成為0 ，並且將升降舵打降舵。3. we put forward a combine algorithm for predicting the aerodynamically generated noise using different methods mentioned above, and developed a computer code named " nospre " to predict acoustic noise generated by rotors 4
Nospre集成了三種噪聲預測方法，可採用固定或旋轉的聲源面來預測跨音速旋翼懸停和前飛時的氣動噪聲。分享友人