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first order vibration mode
相关语句
  第一阶模态
     The experiment result shows that the method mentioned above can obviously restrain its main mode(i.e.the first order vibration mode) vibration,and can be applied to controlling vibration of the structure.
     结果表明,该方法能明显抑制其主要模态(即第一阶模态)的振动,可以应用于该结构的振动控制。
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  “first order vibration mode”译为未确定词的双语例句
     In the method, three dimensional FEM is used to compute the temperature field and thermal bending deformation of rotor, or a first order vibration mode distribution procedure is adopted to estimate the thermal bending deformation of rotor.
     采用三维有限元法计算轴的温度场及热弯曲变形,或采用一阶振型分配法估算轴的热弯曲变形,采用传递矩阵法计算热弯曲振动响应,计算结果与有关理论解吻合良好。
短句来源
     From the view point of mechanical resonance,the first order vibration mode are analyzed as the dynamic characteristics of the floater servo system without built model,and it provides some bases for the design of servo system and the optimization of frame.
     从机械谐振的角度 ,将结构的第一阶振型作为浮子伺服系统未建模动特性进行分析 ,为力反馈伺服系统设计和结构优化提供了重要依据
短句来源
     Numerical results show that the intervals of the elastic modulus of the dam concrete and the rock basement could be reliably identified by using the first order vibration mode values at several fixed points in the dam.
     结果表明 ,在只有一阶圆频率和几个固定点处有一阶振型观测数据的情况下 ,可以可靠地识别出坝体混凝土和基础岩石的动弹性模量所在区间范围 ;
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In 1985 Roddcn et al considered the coupling of rigid motion and elastic vibration. But their mathematical model appears to be inconvenient in engineering design. In this paper. the authors present a simplified mathematical model,which allows the authors to study the effect of sensor position on stability of elastic vehicle.Appropriate sensor's position along longitudinal axis. Analyaing zero-pole distribution. the authors can obtain rather optimal sensor position. Taking SAM-1 missile as example,we calculate...

In 1985 Roddcn et al considered the coupling of rigid motion and elastic vibration. But their mathematical model appears to be inconvenient in engineering design. In this paper. the authors present a simplified mathematical model,which allows the authors to study the effect of sensor position on stability of elastic vehicle.Appropriate sensor's position along longitudinal axis. Analyaing zero-pole distribution. the authors can obtain rather optimal sensor position. Taking SAM-1 missile as example,we calculate the appropriate distance of sensor from nose to be 5.45m. This calculated position agrees fully with the actual distance found in SAM-1 missile.In general, the authors believe that the following design suggestions can be made:(1)Normal type of flight vehicle. The group of sensors should be placed behind valley of first order vibration mode and ahead of those of 2nd and 3rd order vibration modes. In the SAM-1 numerical example mentioned above, the distance of 5.45m from nose to sensor farees with this design suggestion.(2) canard type of night vehicle. The suggestion for normal type nceds to be reversed in the case of canard type, i.e., the group of sensors should be placed ahead of valley of first order vibration mode and behind those of 2nd and 3rd order vibration modes.(3) Rotory wing type of flight vehicle. When actuator position is ahead of c.g., of flight vehicle, the suggestion for normal typeof flight vehicle should be followed; when it is behind c.g., the suggestion for canard type should be followed.

研究了弹性飞行器建模问题,分析了敏感元件位置对飞行器纵向稳定性的影响,提出了几类飞行器自动驾驶仪敏感元件合适位置的选择准则.最后通过算例得到的陀螺位置与飞行器实际陀螺位置较好地符合.

In this paper, a numerical analysis method of rotor′s thermal deflection and its affection on vibration response is studied. In the method, three dimensional FEM is used to compute the temperature field and thermal bending deformation of rotor, or a first order vibration mode distribution procedure is adopted to estimate the thermal bending deformation of rotor. A transfer matrix method is also employed to compute thermal bending vibration response. The results obtained...

In this paper, a numerical analysis method of rotor′s thermal deflection and its affection on vibration response is studied. In the method, three dimensional FEM is used to compute the temperature field and thermal bending deformation of rotor, or a first order vibration mode distribution procedure is adopted to estimate the thermal bending deformation of rotor. A transfer matrix method is also employed to compute thermal bending vibration response. The results obtained from this paper fit well with theoretical and experimental ones. The numerical method presented here can be applied to the analyses of thermal deflection and its affection on vibration response of a real rotor.

研究了转子热弯曲及其对振动影响的数值分析方法。采用三维有限元法计算轴的温度场及热弯曲变形,或采用一阶振型分配法估算轴的热弯曲变形,采用传递矩阵法计算热弯曲振动响应,计算结果与有关理论解吻合良好。这些方法在热弯曲试验器分析中得到了验证。本文提出的数值分析方法可以用于实际发动机转子热弯曲及其影响的分析

Based on the coupled dynamic model for the spatial rotation and elastic vibration of a body, the aeroelastic stability of rockets in flight is studied by Laplace transform equations Under the consideration of a first order vibration mode, the static aeroelastic stability condition is obtained According to the Hurwitz discriminance of stability, the dynamic stability conditions are derived and the diagram of dynamic stability is determined The results are of great importance...

Based on the coupled dynamic model for the spatial rotation and elastic vibration of a body, the aeroelastic stability of rockets in flight is studied by Laplace transform equations Under the consideration of a first order vibration mode, the static aeroelastic stability condition is obtained According to the Hurwitz discriminance of stability, the dynamic stability conditions are derived and the diagram of dynamic stability is determined The results are of great importance to the design of projectiles or rockets having large L/D ratios

本文从弹箭空间摆动和弹性振动耦合的动力学模型出发 ,利用拉普拉斯变换方程对飞行弹箭的气动弹性稳定性进行了研究。在一阶振动模态情况下得到了气动弹性的静态稳定性条件 ,并根据胡尔威茨判别法 ,推导出了动态稳定性条件和确定了动态稳定区域图的形式。

 
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