MSU ME 424 - Marc.TaperedBeamVibration (36 pages)

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Marc.TaperedBeamVibration



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Marc.TaperedBeamVibration

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Pages:
36
School:
Michigan State University
Course:
Me 424 -
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Application of the Finite Element Method Using MARC and Mentat 6 1 Chapter 6 Modal Analysis of a Cantilevered Tapered Beam Keywords elastic beam 2D elasticity plane stress convergence modal analysis Modeling Procedures ruled surface convert 6 1 Problem Statement and Objectives It is required to determine the natural frequencies and mode shapes of vibration for a cantilevered tapered beam The geometrical material and loading specifications for the beam are given in Figure 6 1 The geometry of the beam is the same as the structure in Chapter 3 The thickness of the beam is 2h inches where h is described by the equation h 4 0 6 x 0 03x 2 Geometry Length L 10 Width b 1 uniform Thickness 2h a function of x Material Steel Yield Strength 36 ksi Modulus of Elasticity 29 Msi Poisson s Ratio 0 3 Specific Weight 0 284 lbf in3 Loading Free vibration x 2h L Figure 6 1 Geometry material and loading specifications for a tapered beam 6 2 Analysis Assumptions Because the beam is thin in the width out of plane direction a state of plane stress can be assumed The length to thickness ratio of the beam is difficult to assess due to the severe taper By almost any measure however the length to thickness ratio of the beam is less than eight Hence it is unclear whether thin beam theory will accurately predict the vibratory response of Application of the Finite Element Method Using MARC and Mentat 6 2 the beam Therefore both a 2D plane stress elasticity analysis and a thin elastic beam analysis will be performed 6 3 Mathematical Idealization Based on the assumptions above two different models will be developed and compared The first model is a beam analysis In this model the main axis of the beam is discretized using straight two noded 1D thin beam finite elements having a uniform cross sectional shape and mass distribution within each element Thus the geometry is idealized as having a piecewise constant cross section as shown in Figure 6 2 The uniform thickness within each element is taken to be equal to the actual thickness of the tapered beam at the x coordinate corresponding to the centroid of that element Note that this type of geometry approximation also leads to an approximation of the overall mass as well as its distribution Since the mass distribution plays a strong role in vibratory motion the effect of this approximation should be considered carefully As the mesh is refined the error associated with this approximation will be reduced Because beam elements are designed to capture three dimensional behavior the beam model will predict three dimensional modes of vibration unless additional constraints are imposed In the present case we are most interested in the modes of vibration that occur within the plane shown in Figures 6 1 and 6 2 Therefore we should apply constraints to the model such that the beam cannot translate or rotate out of the plane x L Figure 6 2 Idealized geometry for a tapered beam The second model is a 2D plane stress model of the geometry as shown in Figure 6 1 The 2D finite element model of this structure will be developed using 2D plane stress bilinear four noded quadrilateral finite elements In the present analysis the geometry and material properties are Application of the Finite Element Method Using MARC and Mentat 6 3 symmetric about the mid plane of the beam However the vibratory response is not symmetric about this plane Hence it is necessary to model the entire domain of the beam as shown in Figure 6 1 Note that the mass distribution is accurately represented in the 2D model In free vibration analysis no loads are applied The goal of the analysis is to determine at what frequencies a structure will vibrate if it is excited by a load that is applied suddenly and then removed These frequencies are called natural frequencies and they are a function of the shape the material and the boundary constraints of the structure Mathematically the natural frequencies are associated with the eigenvalues of an eigenvector problem that describes harmonic motion of the structure The eigenvectors are the mode shapes associated with each frequency 6 4 Finite Element Model The procedure for creating the finite element model and obtaining the finite element solution for each type of model is presented at the end of this chapter The 1D beam analysis should be performed three times each with a different mesh Meshes consisting of 2 4 and 6 elements should be developed The 2D analysis should be performed only one time using the mesh described within the procedure 6 5 Model Validation Simple analytical formulas are available for predicting the axial and bending natural frequencies of a uniform cantilevered beam These results can be used to estimate the natural frequencies in a tapered beam and thus to assess the validity of the finite element results i e to make sure that the finite element results are reasonable and do not contain any large error due to a simple mistake in the model For the case of axial vibratory motion an analytical solution can be developed as follows We assume that the axial displacement of the bar u x t is separable in space and time or u x t U x F t where F t is a harmonic function When the material and geometric properties are uniform throughout the bar the governing eigenvalue equation for axial vibratory motion is d 2U 2U 0 2 dx 2 2 m EA Application of the Finite Element Method Using MARC and Mentat 6 4 In the above equation 2 f is the circular frequency measured in radians per second f is the frequency measured in cycles per second m is the mass per unit length of the bar E is the modulus of elasticity and A is the cross sectional area The solution to the above equation takes the form U A sin x B cos x where A and B are constants of integration that must be determined from the boundary conditions In the present problem the boundary conditions are of the form U 0 0 F x L EA dU dx 0 x L The first boundary condition yields B 0 The second boundary condition yields A cos L 0 Since 0 and A 0 is the trivial solution we must have cos L 0 which is referred to as the characteristic equation There are many solutions to this equation n for n 1 3 5 7 2 The circular frequencies of the motion are then obtained as nL n n 2 EA mL2 The eigenfunctions or mode shapes are then found to be U n An sin n x 2L where An are the amplitudes of the shapes which cannot be determined uniquely The lowest natural frequency associated with axial motion of the bar is found for n 1 Application of the


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