:Boundary condition modelling and identification for cantilever-like structures using natural frequencies论文

:Boundary condition modelling and identification for cantilever-like structures using natural frequencies论文

本文主要研究内容

作者(2019)在《Boundary condition modelling and identification for cantilever-like structures using natural frequencies》一文中研究指出:The actual boundary conditions of cantilever-like structures might be non-ideally clamped in engineering practice, and they can also vary with time due to damage or aging. Precise modelling of boundary conditions, in which both the boundary stiffness and the boundary mass should be modelled correctly, might be one of the most significant aspects in dynamic analysis and testing for such structures. However, only the boundary stiffness was considered in the most existing methods. In this paper, a boundary condition modelling and identification method for cantilever-like structures is proposed to precisely model both the boundary stiffness and the boundary mass using sensitivity analysis of natural frequencies. The boundary conditions of a cantilever-like structure can be parameterized by constant mass, constant rotational inertia,constant translational stiffness, and constant rotational stiffness. The relationship between natural frequencies and boundary parameters is deduced according to the vibration equation for the lateral vibration of a non-uniform beam. Then, an iterative identification formulation is established using the sensitivity analysis of natural frequencies with respect to the boundary parameters. The regularization technique is also used to solve the potential ill-posed problem in the identification procedure.Numerical simulations and experiments are performed to validate the feasibility and accuracy of the proposed method. Results show that the proposed method can be utilized to precisely model the boundary parameters of a cantilever-like structure.

Abstract

The actual boundary conditions of cantilever-like structures might be non-ideally clamped in engineering practice, and they can also vary with time due to damage or aging. Precise modelling of boundary conditions, in which both the boundary stiffness and the boundary mass should be modelled correctly, might be one of the most significant aspects in dynamic analysis and testing for such structures. However, only the boundary stiffness was considered in the most existing methods. In this paper, a boundary condition modelling and identification method for cantilever-like structures is proposed to precisely model both the boundary stiffness and the boundary mass using sensitivity analysis of natural frequencies. The boundary conditions of a cantilever-like structure can be parameterized by constant mass, constant rotational inertia,constant translational stiffness, and constant rotational stiffness. The relationship between natural frequencies and boundary parameters is deduced according to the vibration equation for the lateral vibration of a non-uniform beam. Then, an iterative identification formulation is established using the sensitivity analysis of natural frequencies with respect to the boundary parameters. The regularization technique is also used to solve the potential ill-posed problem in the identification procedure.Numerical simulations and experiments are performed to validate the feasibility and accuracy of the proposed method. Results show that the proposed method can be utilized to precisely model the boundary parameters of a cantilever-like structure.

论文参考文献

  • [1].Surface integrity of GH4169 affected by cantilever finish grinding and the application in aero-engine blades[J]. Li Xun,Ma Shuang,Meng Fanjun.  Chinese Journal of Aeronautics.2015(05)
  • [2].Analytical solution for functionally graded anisotropic cantilever beam subjected to linearly distributed load[J]. 黄德进,丁皓江,陈伟球.  Applied Mathematics and Mechanics(English Edition).2007(07)
  • 论文详细介绍

    论文作者分别是来自Chinese Journal of Aeronautics的,发表于刊物Chinese Journal of Aeronautics2019年06期论文,是一篇关于,Chinese Journal of Aeronautics2019年06期论文的文章。本文可供学术参考使用,各位学者可以免费参考阅读下载,文章观点不代表本站观点,资料来自Chinese Journal of Aeronautics2019年06期论文网站,若本站收录的文献无意侵犯了您的著作版权,请联系我们删除。

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