aircraft flutter
英 [ˈeəkrɑːft ˈflʌtə(r)]
美 [ˈerkræft ˈflʌtər]
网络 飞机颤振
双语例句
- Nonlinear separable least square algorithm for the aircraft flutter model parameter identification
基于非线性可分离的最小二乘法的飞行器颤振模态参数辨识 - Forgetting Factor Algorithm for Aircraft Flutter Modal Parameter Identification
基于遗忘因子算法的飞行器颤振模态参数辨识 - Aircraft calls for structural intensity rigidity and stability of flutter on the phrase of designing.
飞机在打样设计阶段除了需要满足结构强度和刚度要求外，还必须满足颤振稳定性要求。 - A generalized total least square algorithm in frequency domain is adopted for aircraft flutter modal parameter identification under noisy environment.
采用一种适用于噪声环境的广义整体最小二乘算法，准确地辨识飞机的颤振模态参数。 - The purpose of this report is to investigate two kinds of instabilities of the whole aircraft low speed flutter model found in the duration of the wind tunnel test, those are the longitudinal static instability and longitudinal dynamic instability.
研究全机低速颤振模型在风洞试验时出现的两种全机不稳定性：纵向静不安定和纵向动不稳定。 - First choose the flutter model of aircraft, identify the parameters of the model, then validate the identified model, and get the flutter modal parameters of aircraft by analyzing the frequency response function of the model at last.
首先建立飞机的颤振模型，然后辨识模型参数，并对模型结果进行合理性分析，最后分析模型的频域响应函数，得到飞机的颤振模态参数。 - Research on Aircraft Flutter Modal Parameter Identification
飞机颤振模态参数识别方法研究 - A Stability Approach of the Whole Aircraft Low Speed Flutter Model Suspended in the Wind Tunnel Analysis
全机低速颤振模型的全机稳定性分析 - By using ground resonance test results from certain type of aircraft with full external stores, the analysis and research are performed on the flutter characteristics of external stores jam of aircraft wing.
利用某型飞机全机带外挂物的地面共振试验结果，对飞机机翼&外挂干扰的颤振特性进行了分析研究。 - Active aeroelastic wing ( AAW) technology is a new idea in modern aircraft design, and active flutter suppression and gust alleviation for multi input/ multi output systems is the main research aspect in AAW.
多输入/多输出系统的颤振主动抑制与阵风减缓是主动气动弹性机翼技术的重要研究方面。 - Asymmetric store flutter, a very important problem in aircraft engineering, is investigated in detail in this paper according to the mode localization theory and the transition mechanism of flutter modes.
根据模态局部化理论及颤振模态的转变机理，详细研究了不对称外挂颤振这一重要的飞机工程问题。 - The conditions for raising flutter speed of aircraft are discussed systematically. A simple but effective approach of using asymmetric stores is introduced, which is valuable in aircraft flutter design.
系统讨论了利用不对称外挂提高飞机颤振速度的条件，为飞机抗颤振设计提供了一条新途径。 - This method can be used to evaluate the unsteady aerodynamic loads and derivatives of elastic aircraft. The equations of motion of an elastic aircraft are presented. And a unified method is employed to analyse the overall body motion stability and the flutter characteristics of an elastic aircraft.
本文应用非定常气动力理论计算了刚体运动与弹性运动耦合的飞机运动方程中的非定常气动力及广义气动力导数，给出一种分析飞机总体运动稳定性及颤振特性的统一方法。 - After reviewing the application of system identification to aircraft flutter research, three methods of system identification are presented in this paper.
本文在简要综述了系统识别技术在飞机颤振研究中的应用后，介绍了三种系统识别方法。 - System identification and aircraft flutter
系统识别与飞机颤振 - In the flight of transonic speed equal amplitude vibration of a certain type of aircraft encountered during the type finalization test, a study on the flutter analysis and vibration data measured in real flight test are performed.
针对某型机定型试飞中遇到的跨音速等幅振动现象，对该机的颤振分析和试飞实测振动数据进行了研究。 - Chinese aircraft cnginccrs arc becoming intcrcsted in some strange localized vibration phenomena that occur during ground vibration test and flutter test: mode localization and frequency loci veering.
研究了某机简化模型线性振动的模态局部化现象，以及与此现象密切相关的频率曲线转向现象。 - During aircraft preliminary design, the control effectiveness and flutter speed are concerned.
对于采用飞翼布局的飞机，在设计初期，操纵面的操纵效率和颤振临界动压是比较关心的两个问题。 - The trends of air critical velocity at which the instability phenomena appears is determined with variation of different factors in order to increase the critical velocity and to perform the whole aircraft flutter wind tunnel test smoothly and completely.
研究它们出现时的气流速度（临界速度）随哪些因素变化及其变化规律，以便找到提高临界速度的方法，从而使全机低速颤振风洞试验能顺利进行。 - Generalized Total Least Squares in Frequency Domain for Aircraft Flutter Modal Parameter Identification
飞机颤振模态参数辨识的频域广义整体最小二乘算法 - On Semi-Active Aircraft Flutter Control by ER Fluid Damping Pivot
电流变液在飞机操纵面颤振半主动控制中的应用研究 - When the March number of the aircraft flights is quite large, the aerothermal effect factor should be considered for the reason that it affects the structural stiffness of the panel, and finally affects the critical flutter speed of the panel.
其中当飞行马赫数很大时，必须考虑气动热效应因素，因为气动热效应会影响壁板的结构刚度，进而会影响其颤振临界速度。 - As a consequence, the gust load alleviation system based on active control technology is introduced, which can inhibit the response of the aircraft against the gust, slow wing flutter intensity, improve the fatigue strength of the wing structure, and improve the ride quality.
基于主动控制技术的阵风减缓系统，可以抑制飞机对阵风的响应，减缓机翼的颤振强度，提高机翼的结构疲劳强度，改善飞机乘坐品质。 - In the process of aircraft design and development, the wind tunnel test of flutter model is an important technique measures to validate flutter analyze result and its result provide important test basis for flutter flight-test.
在飞机研制设计过程中，颤振模型风洞试验是验证颤振理论计算结果是否正确合理的重要技术手段，其试验结果为颤振飞行试验提供重要的风洞试验数据。 - The Aircraft flutter model is the main subject of the wind tunnel flutter test. Its performance is the key factor to determine the success of the flutter test.
飞机颤振缩比模型是颤振风洞试验的主体，其性能的优劣是决定颤振试验能否成功的关键。 - The research results are partly applied to new aircraft flutter testing, and achieve great military and economy benefit.
其中的部分研究成果已成功应用于某型飞机的颤振试飞试验数据分析，产生了显著的军事和经济效益。