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aircraft empennage
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  飞行器尾翼
     In the test of the empennage first bending mode and revolving mode, the aircraft empennage’s non linear dynamic characteristic resulting from fit clearance is analyzed by measuring its natural frequency exciting force curve in which natural frequency of empennage varies with exciting force.
     通过尾翼的一阶弯曲振动和舵面旋转振动模态试验 ,得到了尾翼固有频率随激振力变化的力 频曲线 ,初步分析了由配合间隙造成的飞行器尾翼结构非线性动态特性
短句来源
     Preliminary Analysis of Non-linear Vibration Characteristic of Aircraft Empennage
     飞行器尾翼结构的非线性动态特性初步分析
短句来源
     Starting from aircraft empennage’s non linear characteristic, the non linear reason is discribed,and the identification method of structure dynamic characteristic is discussed.
     从飞行器尾翼非线性特征出发 ,描述了非线性成因 ,讨论了结构动态特性的辨别方法 .
短句来源
  相似匹配句对
     Preliminary Analysis of Non-linear Vibration Characteristic of Aircraft Empennage
     飞行器尾翼结构的非线性动态特性初步分析
短句来源
     Magnetization of aircraft
     飞机的磁化
短句来源
     AIRCRAFT MAINTENANCE
     飞机维修
短句来源
     Starting from aircraft empennage’s non linear characteristic, the non linear reason is discribed,and the identification method of structure dynamic characteristic is discussed.
     从飞行器尾翼非线性特征出发 ,描述了非线性成因 ,讨论了结构动态特性的辨别方法 .
短句来源
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  aircraft empennage
The present research provides advances in the predictive capability and our understanding of aircraft empennage buffet.
      


Starting from aircraft empennage’s non linear characteristic, the non linear reason is discribed,and the identification method of structure dynamic characteristic is discussed. In the test of the empennage first bending mode and revolving mode, the aircraft empennage’s non linear dynamic characteristic resulting from fit clearance is analyzed by measuring its natural frequency exciting force curve in which natural frequency of empennage varies with exciting force.

从飞行器尾翼非线性特征出发 ,描述了非线性成因 ,讨论了结构动态特性的辨别方法 .通过尾翼的一阶弯曲振动和舵面旋转振动模态试验 ,得到了尾翼固有频率随激振力变化的力 频曲线 ,初步分析了由配合间隙造成的飞行器尾翼结构非线性动态特性

Purpose.There exist already some aeroelastic model empirical designs for empennage non-lift type buffeting but how to analyze their wind tunnel test data effectively appears to remain an unsolved problem.Northwestern Polytechnical University has engaged in aeroelastic research for decades and,based on our experience,we propose a buffeting characteristic index,which we believe can analyze effectively wind tunnel test data for such buffeting.Aircraft empennage non-lift type buffeting is a typical dynamic...

Purpose.There exist already some aeroelastic model empirical designs for empennage non-lift type buffeting but how to analyze their wind tunnel test data effectively appears to remain an unsolved problem.Northwestern Polytechnical University has engaged in aeroelastic research for decades and,based on our experience,we propose a buffeting characteristic index,which we believe can analyze effectively wind tunnel test data for such buffeting.Aircraft empennage non-lift type buffeting is a typical dynamic aeroelastic response phenomenon which is usually excited by nonlinear aerodynamic forces in turbulent or separated wake flow which is induced by blunt body installed on the aircraft fuselage.Flight tests and wind tunnel tests are often used to study this aeroelastic problem to avoid the difficult aerodynamic force calculation.In the full paper,we explain in detail the research done by us.In this abstract,we just list the topics of our explanation:(1) empirical design and building of our aeroelastic model for empennage non-lift type buffeting;(2)wind tunnel tests of our model;(3) effective analysis of wind tunnel test data with the above mentioned buffeting characteristic index;this index is denoted by r and r=_b/_s,where _b is the mean-square strain at the fin root caused by its dynamic response with blunt body on the fuselage,_s is that without blunt body.Fig.4 in the full paper gives the variations of characteristic index r with the pitch angle θ in the range of θ=-10° to θ=10° for four different values of yaw angle ψ:0°,2.5°,5°,and 8°.The four curves in Fig.4 show that yaw angle has little effect on the characteristic of empennage non-lift type buffeting while the pitch angle has considerable impact on it.The effective analysis using characteristic index r shows preliminarily that our empirical design of aeroelastic model for non-lift type of buffeting is fairly satisfactory.

针对尾翼非升力型抖振问题,提出尾翼非升力型抖振试验气动弹性模型设计的经验性原则和一种实用的非升力型抖振特性指标。设计制作了某机尾翼气动弹性抖振模型,进行了不同俯仰角和偏航角下的风洞试验。风洞试验结果表明随着机身俯仰角的增加尾翼振动响应没有突变现象发生,偏航角的改变对尾翼振动响应变化趋势影响不大。

 
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