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   flight flutter 的翻译结果: 查询用时:0.17秒
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flight flutter
相关语句
  飞行颤振
     Investigation on Improving the Accuracy of Parameter Identification Based on Morlet Wavelet in Flight Flutter Testing
     基于Morlet小波改善飞行颤振试验参数识别精度的方法
短句来源
     APPLICATION OF IDENTIFICATION METHOD OF MODAL PARAMETER TO FLIGHT FLUTTER TEST
     模态参数识别在飞行颤振试验中的应用
短句来源
     Flutter test data processing was the important component of flight flutter testing of aircraft.
     颤振试验数据处理是飞行颤振试验的重要组成部分。
短句来源
     ARMAX model method and subspace-based state space method were used to process the flight flutter test data, and identify the flutter modal parameters of aircraft.
     论文使用了现代参数辨识技术的ARMAX模型递推法和状态子空间辨识法,对飞行颤振试验数据进行处理,辨识飞机的颤振模态参数。
短句来源
     DATA ANALYSIS AND SOFTWARE DEVELOPMENT FOR FLIGHT FLUTTER TEST
     飞行颤振试验数据处理方法及软件研制
短句来源
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  “flight flutter”译为未确定词的双语例句
     Wavelet Denoising of Flight Flutter Testing Data for Improvement of Parameter Identification
     用于提高辨识效果的颤振试验数据小波去噪(英文)
短句来源
     Frequency-Domain GTLS Identification Combined with Time-Frequency Filtering for Flight Flutter Modal Parameter Identification
     基于时频域滤波及频域广义整体最小二乘辨识的飞机颤振模态参数辨识(英文)
短句来源
     The Application of the Structured Singular Value Theory on Flight Flutter Test
     结构奇异值理论在颤振飞行试验中的应用
     1. A new wavelet denoising method is introduced for flight flutter test excited by rocket impulse.
     1 为提高小火箭激励条件下试飞试验数据的信噪比,提出了一种用于颤振飞行试验数据处理的小波去噪方法。
短句来源
     A detail flutter analysis is performed from the perspective of engineering andairworthiness in this paper, combining with flutter calculations and the results of the groundvibration testing and the Y7-200A aircraft flight flutter testing.
     本文结合Y7-200A型飞机的研制过程,主要从工程应用和适航性的角度,以理论计算为主,结合全机地面共振实验、颤振飞行试验、颤振模型风洞试验等结果,对Y7-200A型飞机可能出现的各类颤振形式进行了比较深入的研究。
短句来源
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  相似匹配句对
     FLYINGIEXPERIENCE OF THE FLUTTER FLIGHT TEST FOR AIRCRAFT Y-12
     Y-12飞机的颤振试飞体会
短句来源
     DATA ANALYSIS AND SOFTWARE DEVELOPMENT FOR FLIGHT FLUTTER TEST
     飞行颤振试验数据处理方法及软件研制
短句来源
     On Capital Flight
     资本外逃话题
短句来源
     Bird flight
     鸟类的飞翔(英文)
短句来源
     Flutter as Butterfly
     彩蝶飞舞
短句来源
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  flight flutter
General observations are made regarding the value of low speed wind-tunnel flutter models and the safety aspect of flight flutter tests.
      


A least Pth optimization method is developed for estimation of structural dynamic parameters from estimated response spectrum power density function. In this method not only a one-degree-of-freedom model but also a multi-degree-of-freedom model of estimation can be used. A certain amount of ordinates with high signal to noise ratio of the response spectrum can be selected to fit the model. A suggestion of selecting initial guess is made to find the global minimum and not to be trapped at a local minimum. As...

A least Pth optimization method is developed for estimation of structural dynamic parameters from estimated response spectrum power density function. In this method not only a one-degree-of-freedom model but also a multi-degree-of-freedom model of estimation can be used. A certain amount of ordinates with high signal to noise ratio of the response spectrum can be selected to fit the model. A suggestion of selecting initial guess is made to find the global minimum and not to be trapped at a local minimum. As an example, the structural dynamic parameters of a tower platform with dynamic absorber under wave and wind load are estimated. In this example, two peak frequencies are so close that the methods based on a one-degree-of-freedom model of estimation, such as the half-power bandwidth method orthe spectral moment method, fail in estimating its structural dynamic parameters. However, it can be easily completed by using the two-degree-of-freedom model of estimation in the least Pth optimization method. Another example, an aircraft in flight-flutter test also shows the least Pth optimization method is very flexible and effective. Combining the Maximum Entropy Method with least Pth optimization is suggested for estimating structural dynamic parameters from ambient measuremet.

本文提出用最小p乘优化方法从响应功率谱估算结构的动力参数。此法不仅可用单自由度的估算模型而且可用多自由度的估算模型。这里,可选用一定数量的、具有高信噪比的响应谱纵坐标来拟合估算之模型。给出了一种选取初始猜测的建议以使优化过程收敛于总体之最小值而不陷于局部的极小值。作为一个例题,对一个具有动力消振器的塔式平台在波浪和风载作用下的结构动力参数进行了估算。在此例中两个峰频是如此接近以致用单自由度估算模型,譬如用半功率带宽法或谱矩法,就无法进行估算。但这可很容易地用最小p乘优化来估算。另一个例题是飞机颤振试验中的结构动力参数估算。它也表明本方法适应性强、很有效。建议在从实测响应记录估算结构动力参数时用最大熵法和最小p乘优化。

This paper introduces the compendium of flight flutter test and the features and specific reguirements of data processing with flight flutter test. It outlines the fundamentals and the basic mathematical model of identifying modal frequency and damping by means of parameter identification with frequency domain and time domain. It emphatically describes appropriate measures taken for solving the contradication with lower signal-to-noise ratio of signal obtained from flight flutter test and higher...

This paper introduces the compendium of flight flutter test and the features and specific reguirements of data processing with flight flutter test. It outlines the fundamentals and the basic mathematical model of identifying modal frequency and damping by means of parameter identification with frequency domain and time domain. It emphatically describes appropriate measures taken for solving the contradication with lower signal-to-noise ratio of signal obtained from flight flutter test and higher accuracy of identified modal damping, and for short endng the time of data-analysis.

本文介绍了飞机飞行颤振试验的简况、颤振试飞数据处理的特点和一些特殊要求。简要介绍了用频域参数识别方法和时域参数识别方法识别模态频率和阻尼的基本原理和基本数学模型。文中着重介绍了为解决颤振试飞中所获得的信号的信噪比差,而又要求识别的模态阻尼值的精度比较高这个矛盾和为了尽量缩短数据分析所花费的计算时间而采取的若干措施。

ata analysis methods and software development for the flight flutter test with transj-ent excitations are discussed.The features of the case are briefly introdueed.Emphasis is placed on data preproeessing and parameter estimation in the time domain and frequency domain.It is proved that the method in the time domain is theoretically equivalent to the method in the frequency domain.However,in practical situations,the latter is better than the former.The simulation and practical applications show the feasibility...

ata analysis methods and software development for the flight flutter test with transj-ent excitations are discussed.The features of the case are briefly introdueed.Emphasis is placed on data preproeessing and parameter estimation in the time domain and frequency domain.It is proved that the method in the time domain is theoretically equivalent to the method in the frequency domain.However,in practical situations,the latter is better than the former.The simulation and practical applications show the feasibility of the proposed procedure and the software.

介绍了用脉冲激振进行飞行颤振试验时的数据处理方法及软件研制。讨论了数据预处理方法和时域、频域参数识别方法。证明了时域和频域方法理论上是等价的,但实际应用中,因频域方法可选频段拟合,识别结果比时域方法好。仿真计算和实际应用结果表明该方法和软件是有效的。

 
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