tail rotor 中文意思是什麼
tail rotor
解釋
尾部螺旋槳-
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。 -
The synergy n9 tail rotor system is ready for hard 3d
協同n9號尾槳打制三維準備 -
Both tail rotor blades were severed
尾槳的兩片槳葉均折斷。 -
If at high speed, the helicopter will not visible react. you will probably not notice that your tail rotor has stopped spinning until the next time you slow down
在高速狀態下，直升機不會有任何不良反應，可能在你慢下來之前，你都不會注意到尾漿已經失效。 -
The machined self lubricating composite tail rotor gears will stand up to the most aggressive 3d flying
加工自潤滑復合尾槳齒輪將迎接最激烈的三維飛行 -
From a stationary hover, execute a tail rotor only turn of 360 degrees to either the right or the left
先保持靜止停懸，然後方向舵打右舵或左舵，使機體原地旋轉360 。 -
For a conventional helicopter, the tail rotor is one of primary sources for helicopter noise
尾槳是直升機的主要噪聲源，降低尾槳噪聲對控制直升機的噪聲水平具有重要意義。 -
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 -
This thesis provides an approach for the prediction of the tail rotor noise and the design of a tail rotor with low noise level
本文的研究結果為今後發展或逐步完善能用於工程計算的直升機尾槳噪聲的預測方法提供了一些指導。 -
Chapter 4 presents the mechanism of helicopter tail rotor noise, developed a new analytical model to investigate the noise of tail rotor when helicopter fly forward
在第四章中，通過對直升機尾槳噪聲的機理分析，建立了前飛狀態下尾槳噪聲的計算模型。 -
The theoretical deduction in chapter 3 shows that the shape of load distribution used in the arithmetic is a decisive fact of the error margin size, the more the adoptive shape looks like the actual case, the smaller the error margin will be, therefore the tilt parabola shape can instead of the actual shape of load distribution in the permissible error margin when we predicting constant loading noise caused by the tail rotor of helicopter
在第三章中通過理論推導和計算比較發現，在預測直升機尾槳定常載荷噪聲時，其誤差大小取決于演算法中槳葉弦向載荷分佈的數學描述與實際弦向載荷分佈的吻合程度，而選取一種與實際弦向載荷分佈較為相似的斜拋物線形來預測噪聲所導致的誤差是很小的。 -
In this thesis, the major contributions of the author ’ s research work are as follows : at first, the classification of helicopter tail rotor noise sources and the existent method of helicopter noise research is introduced briefly
本文採用諧波分析法對直升機前飛狀態下的尾槳噪聲進行了理論分析研究。主要工作包括:本文首先簡要介紹了直升機噪聲的分類以及國內外直升機噪聲研究方法的現狀，總結了前人的研究成果。
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