noise tail 中文意思是什麼
noise tail
解釋
噪殘尾-
The exhaust gas spews out of the exhaust valve and enters into the muffler along the exhaust manifold before draining into the atmosphere from the tail pipe. this process yields wide band exhaust noise
發動機廢氣從排氣門高速沖出，沿著排氣歧管進入消聲器，最後從尾管排入大氣，在這一過程中產生了寬頻帶的排氣噪聲。 -
Implementations of video integrators, which are based on two - pole filter, are discussed in the last. the initialization, tail and noise integrating problems are analyzed and improvements are given
最後，本文對非相參視頻積累器的實現進行了討論，分析了雙極點濾波器存在的初始化、拖尾和噪聲電平問題，並提出了改進的方法。 -
It is thus of importance to develop an l - band edfa. however, a conventional l - band edfa is relatively inefficient and has low gain and high noise figure since they are operated at the tail of the erbium gain band. therefore, it is very important to design and analyze a high performance l - band edfa with simultaneously high gain, low noise and low gain ripple for a dwdm system
開發新的l - bandedfa是十分必要的，然而傳統的l - bandedfa由於工作在鉺光纖增益譜的尾部，其存在增益低、工作轉換效率低、噪聲大等缺點，因此，分析和設計符合dwdm系統發展要求的具有優良性能（高增益、低噪聲、動態增益均衡）的l - bandedfa是十分有意義的。 -
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。 -
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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