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   aerodynamics model 在 航空航天科学与工程 分类中 的翻译结果: 查询用时:0.842秒
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aerodynamics model    
相关语句
  气动模型
    On the basis of these, a simplified iced aerodynamics model is established, describes the effects of aircraft icing on aerodynamic parameters.
    在此基础上,建立了简化的飞机结冰气动模型,以描述结冰对气动参数的影响;
短句来源
  空气动力学模型
    A Study on the Aerodynamics Model and Wind Tunnel Test of Pantograph
    受电弓空气动力学模型及风洞试验研究
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  aerodynamics model
All these motions of flying insects are interrelated by the kinematics equations, attitude equations, aerodynamics model and dynamics equations of the insects' centroid.
      
The WST contains a host computer that runs the aircraft aerodynamics model and numerous subsystem models such as the inertial navigation system.
      


This paper briefly introduces the creation of aerodynamics model of pantographand the analysis and comoutation method for aerodvnamiC forces,The wind tunnel test method and results of a full-scale pantograph are also introduced.It is found through prelimi-nary study of the results that theoretieal computation agrees basically with wind tunnel test results.

本文简要介绍电力机车受电弓空气动力学模型的建立和气动力学的分析计算方法;介绍实际受电弓气动力风洞试验方法和试验结果。初步的研究表明,理论计算与风洞试验结果基本吻合。

A fuzzy logic model of nonlinear unsteady aerodynamics with the elevator deflection angle is developed,using a fuzzy logic algorithm.The model is proved by large amplitude pitch up oscillation test data.The results show that the developed model has a good ability of predicting the unsteady aerodynamics.Therefore,this method can be used to develop other nonlinear unsteady aerodynamics models with multiple variables complex motions.

应用模糊逻辑算法 ,建立了带升降舵偏角影响的非线性非定常气动力模糊逻辑模型 ,并进行了验证。结果表明 :所建立的非定常气动力模糊逻辑模型有较强的预测能力。此方法为今后建立多变量、复杂运动的非线性非定常气动力数学模型 ,提供很好的借鉴。

An improved state-space representation for the unsteady aerodynamics of high angle of attack is presented. The first order differential equation first given by Goman is used to model the dynamics of flow separation and vortex burst, but we make some improvements by considering the unsteady influence of the rate of the dynamic motion of the airframes. In the state-space equation, we introduce a dependent variable of the pitching rate of the airframes. The aerodynamic coefficients are determined with eq.(6) which...

An improved state-space representation for the unsteady aerodynamics of high angle of attack is presented. The first order differential equation first given by Goman is used to model the dynamics of flow separation and vortex burst, but we make some improvements by considering the unsteady influence of the rate of the dynamic motion of the airframes. In the state-space equation, we introduce a dependent variable of the pitching rate of the airframes. The aerodynamic coefficients are determined with eq.(6) which expresses aerodynamic coefficient as an algebraic series in terms of input variables. The minimum mean-square error approach and maximum likely-hood method are used to identify the unknown parameters in the model from the wind tunnel test data. Three examples of the unsteady aerodynamics model of high angle of attack are built up here with the method given in this paper: (1) an airfoil pitching up with constant rate; (2) an oscillating delta wing; (3) an oscillating aircraft. The comparison of the results obtained with the Goman′s original model and the method given here shows that the performance of present model is much better, especially in high angle of attack region.

在 Goman提出的状态空间模型的基础上 ,开展了有关建立大迎角非定常气动力数学模型问题的研究。针对以往在运用状态空间模型建立大迎角非定常气动力数学模型中存在的问题 ,通过分析状态方程中非定常影响参数与减缩频率 (或无量纲俯仰角速率 )的关系 ,建立了改进数学模型的基本思路。同时运用插值方法给出了二者之间的关系 ,并将此结果引入到状态方程中。经过辨识验算后表明 ,改进后的模型不仅改善了该模型对气动力的预测准确度 ,同时也提高了描述大迎角非定常气动力的能力。

 
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