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模态截断
相关语句
  mode truncation
    Simulation results show that the H 2 norm model reduction is more appropite than the general mode truncation method.
    仿真算例表明 ,基于H2 范数的模态缩减法明显优于普通的模态截断方法。
短句来源
  “模态截断”译为未确定词的双语例句
    This paper presents a kind of VSC to stabilize LFSS based on the relative order of LFSS equal to 2, if avoids the selection of major poles and solves the problem of " control spillover". Finally.
    本文从LFSS的相对阶为2的特点出发设计了用于LFSS的镇定控制的变结构控制器,从而避免了主导极点的选择(模态截断),解决了“控制溢出”问题。
短句来源
    Bifurcation problems of the model system similar to the Lorenz equations of the Navier-Stokes equations for the flow between two concentric rotating spheres are discussed.
    本文对同心球间旋转流动的Navier-Stokes方程谱展开后进行三模态截断,研究了所得到的类Lorenz型方程组的分歧问题.
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  mode truncation
A new six-mode truncation of the Navier-Stokes equations on a two-dimensional torus: A numerical study
      
A model obtained via a six-mode truncation of the Navier-Stokes equations for an incompressible fluid on a two-dimensional torus is studied.
      
A five-mode truncation of the Navier-Stokes equations on a three-dimensional torus
      
In the former case a behavior is found which is quite similar to the ones of the Lorenz model and of a 5-mode truncation of the two-dimensional Navier-Stokes equations previously studied.
      
Sequences of infinite bifurcations and turbulence in a five-mode truncation of the Navier-Stokes equations
      
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This paper presents a kind of VSC to stabilize LFSS based on the relative order of LFSS equal to 2, if avoids the selection of major poles and solves the problem of " control spillover". Finally. satellite attitude control during deployment solar panels as an example, simulation on computer is performed.

本文从LFSS的相对阶为2的特点出发设计了用于LFSS的镇定控制的变结构控制器,从而避免了主导极点的选择(模态截断),解决了“控制溢出”问题。以太阳帆板展开过程中航天器姿态控制为例,作了计算机仿真。

The behavior of the satellites and their flexible solar arrays are imitated on the single axis gas bearing turntable (SAGBT) and flexible beam separately. The dynamic equations of the SAGBT are derived.The analysis of inertial perfection index is given for non restrained modality with inertial perfection rule and the dynamic equations with modaltrumcation are got. The controller using reaction flywheel on the SABGT is designed and then computer simulation is obtained.

用单轴气浮台和挠性梁分别模拟卫星本体和太阳帆板。推导了其动力学方程,采用惯性完整性准则进行了模态截断,给出了模态截断的动力学方程。用反作用飞轮作为控制执行机构,设计了控制器,进行了相关的计算机仿真。

In this paper, a double loops controller design method is provided in accordancewith the characteristics of large flexible spacecraft, such as low frequency, low damping and coupling between rigid body and flexible appendages. Optimal sliding-modecontrol method is used, and robust stability is considered. Finallyg numerical simulations show that vibration suppression and accurate pointing are accomplishedby using two separate control loops with certain robust property. Based on modetruncation modle of the flexible...

In this paper, a double loops controller design method is provided in accordancewith the characteristics of large flexible spacecraft, such as low frequency, low damping and coupling between rigid body and flexible appendages. Optimal sliding-modecontrol method is used, and robust stability is considered. Finallyg numerical simulations show that vibration suppression and accurate pointing are accomplishedby using two separate control loops with certain robust property. Based on modetruncation modle of the flexible spacecraft.

针对大型挠性空间结构频率低、阻尼小,刚体与各挠性模态之间互相耦合等特点,提出了一种双回路控制器的设计方法.回路的设计采用了最优滑动模态的变结构设计方法.且考虑了鲁棒稳定性问题.最后,给出了结果的数字仿真,从仿真曲线可以看出,对于基于模态截断的大型挠性空间飞行器,该设计方法具有一定的鲁棒性.

 
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