In this work, rotating beams which are isospectral to non-rotating beams are studied. A rotating beam is isospectral to a non-rotating beam if both the beams have the same spectral properties i.e; both the beams have the same set of natural frequencies under a given boundary condition. The Barcilon-Gottlieb transformation is extended, so that it converts the fourth order governing equation of a rotating beam (uniform or non-uniform), to a canonical fourth order eigenvalue equation. If the coefficients in this canonical equation match with the coefficients of the non-rotating beam (non-uniform or uniform) equation, then the rotating and non-rotating beams are isospectral to each other. The conditions on matching the coefficients lead to a pair of coupled differential equations. We solve these coupled differential equations for a particular case, and thereby obtain a class of isospectral rotating and non-rotating beams. However, to obtain isospectral beams, the transformation must leave the boundary conditions invariant. We show that the clamped end boundary condition is always invariant, and for the free end boundary condition to be invariant, we impose certain conditions on the beam characteristics. The mass and stiffness functions for the isospectral rotating and non-rotating beams are obtained. We use these mass and stiffness functions in a finite element analysis to verify numerically the isospectral property of the rotating and non-rotating beams. Finally, the example of beams having a rectangular cross section is presented to show the application of our analysis. Since experimental determination of rotating beam frequencies is a difficult task, experiments can be easily conducted on these rectangular non-rotating beams, to calculate the frequencies of the isospectral rotating beams.

Submitted by Mateus de Andrade Zanitti (mateuszanitti@hotmail.com) on 2018-06-29T14:33:25Z No. of bitstreams: 1 Mateus_Zanitti.pdf: 5438696 bytes, checksum: 7b89dea41803feb908ac9a925a1476a6 (MD5) / Approved for entry into archive by Cristina Alexandra de Godoy null (cristina@adm.feis.unesp.br) on 2018-06-29T14:46:24Z (GMT) No. of bitstreams: 1 zanitti_ma_me_ilha.pdf: 5727118 bytes, checksum: 3fcb4fd3093903b37c0ec52a3df572ff (MD5) / Made available in DSpace on 2018-06-29T14:46:24Z (GMT). No. of bitstreams: 1 zanitti_ma_me_ilha.pdf: 5727118 bytes, checksum: 3fcb4fd3093903b37c0ec52a3df572ff (MD5) Previous issue date: 2018-06-28 / Coordenação de Aperfeiçoamento de Pessoal de Nível Superior (CAPES) / Este trabalho trata do desenvolvimento, análise e validação das equações do movimento de vigas flexíveis girantes formulada pelo método dos Elementos Finitos. A modelagem da viga é feita através do modelo proposto de viga de Euler-Bernoulli e a deformação é representada pelo tensor de deformação de Green-Lagrange. As equações globais para os modos longitudinal, lag e flap são obtidas pelo método de energia de Lagrange e a discretização é feita pelo método dos Elementos Finitos. São propostos modelos de viga elementar com dois e três graus de liberdade por nó e sua validação é feita, num primeiro momento, pela comparação das frequências naturais e posteriormente pela resposta, em regime transiente, dos deslocamentos da viga, através da comparação dos resultados obtidos com os dados disponíveis na literatura, sendo que a influência do acoplamento entre os modos longitudinal e lag é investigada para a dinâmica em regime transiente. O trabalho termina comentando as potencialidades da proposta apresentada, discutindo as facilidades e dificuldades encontradas na sua implementação e apontamentos para o desenvolvimento de trabalhos futuros. / This work deals with the development, analysis and validation of the motion equations of the flexible rotating beams formulated by the Finite Element method. The beam modeling is done through the proposed Euler-Bernoulli beam model and the deformation is represented by the Green-Lagrange deformation tensor. The global equations for the longitudinal, lag and flap modes are obtained by the Lagrange energy method and the discretization is done by the Finite Element method. A discrete beam model with two and three degrees of freedom per node is proposed and its validation is done, firstly, by comparing the natural frequencies and later by the transient response of the beam displacements, by comparing the results obtained with the data available in the literature, and the influence of the coupling between the longitudinal and lag modes is investigated for the transient dynamics. This work is concluded presenting the potentialities of the design methodology proposed and future developments to be implemented.

Orientador: Gustavo Luiz Chagas Manhães de Abreu / Resumo: Este trabalho trata do desenvolvimento, análise e validação das equações do movimento de vigas flexíveis girantes formulada pelo método dos Elementos Finitos. A modelagem da viga é feita através do modelo proposto de viga de Euler-Bernoulli e a deformação é representada pelo tensor de deformação de Green-Lagrange. As equações globais para os modos longitudinal, lag e flap são obtidas pelo método de energia de Lagrange e a discretização é feita pelo método dos Elementos Finitos. São propostos modelos de viga elementar com dois e três graus de liberdade por nó e sua validação é feita, num primeiro momento, pela comparação das frequências naturais e posteriormente pela resposta, em regime transiente, dos deslocamentos da viga, através da comparação dos resultados obtidos com os dados disponíveis na literatura, sendo que a influência do acoplamento entre os modos longitudinal e lag é investigada para a dinâmica em regime transiente. O trabalho termina comentando as potencialidades da proposta apresentada, discutindo as facilidades e dificuldades encontradas na sua implementação e apontamentos para o desenvolvimento de trabalhos futuros. / Abstract: This work deals with the development, analysis and validation of the motion equations of the flexible rotating beams formulated by the Finite Element method. The beam modeling is done through the proposed Euler-Bernoulli beam model and the deformation is represented by the Green-Lagrange deformation tensor. The global equations for the longitudinal, lag and flap modes are obtained by the Lagrange energy method and the discretization is done by the Finite Element method. A discrete beam model with two and three degrees of freedom per node is proposed and its validation is done, firstly, by comparing the natural frequencies and later by the transient response of the beam displacements, by comparing the results obtained with the data available in the literature, and the influence of the coupling between the longitudinal and lag modes is investigated for the transient dynamics. This work is concluded presenting the potentialities of the design methodology proposed and future developments to be implemented. / Mestre

A partial differential equation in space and time represents the physics of rotating beams. Mostly, the numerical solution of such an equation is an available option as analytical solutions are not feasible even for a uniform rotating beam. Although the numerical solutions can be obtained with a number of combinations (in space and time), one tries to seek for a better alternative. In this work, various numerical techniques are applied to the rotating beam problems: finite element method, meshless methods, and B-spline finite element methods. These methods are applied to the governing differential equations of a rotating Euler-Bernoulli beam, rotating Timoshenko beam, rotating Rayleigh beam, and cracked Euler-Bernoulli beam. This work provides some elegant alternatives to the solutions available in the literature, which are more efficient than the existing methods: the p-version of finite element in time for obtaining the time response of periodic ordinary differential equations governing helicopter rotor blade dynamics, the symmetric matrix formulation for a rotating Euler-Bernoulli beam free vibration problem using the Galerkin method, and solution for the Timoshenko beam governing differential equation for free vibration using the meshless methods. Also, the cracked Euler-Bernoulli beam free vibration problem is solved where the importance of higher order polynomial approximation is shown. Finally, the overall response of rotating blades subjected to aerodynamic forcing is obtained in uncoupled trim where the response is independent of the overall helicopter configuration. Stability analysis for the rotor blade in hover and forward flight is also performed using Floquet theory for periodic differential equations.

Rotating and non-rotating beams are widely used to model important engineering struc-tures. Hence, the vibration analyses of these beams are an important problem from a structural dynamics point of view. Depending on the beam dimensions, they are mod-eled using different beam theories. In most cases, the governing differential equations of these types of beams do not yield any simple closed-form solutions; hence we look for the inverse problem approach in determining the beam property variations given certain solutions. The long and slender beams are generally modeled using the Euler-Bernoulli beam theory. Under the premise of this theory, we study (i) the second mode tailoring of non-rotating beams having six different boundary conditions, (ii) closed-form solutions for free vibration analysis of free-free beams, (iii) closed-form solutions for free vibration analysis for gravity-loaded cantilever beams, (iv) closed-form solutions for free vibration analysis of rotating cantilever and pinned-free beams and (v) beams with shared eigen-pair. Short and thick beams are generally modeled using the Timoshenko beam theory. Here, we provide analytical closed-form solutions for the free vibration analysis of ro-tating non-homogeneous Timoshenko beams. The Rayleigh beam provides a marginal improvement over the Euler-Bernoulli beam theory without venturing into the math-ematical complexities of the Timoshenko beam theory. Under this theory, we provide closed-form solutions for the free vibration analysis of cantilever Rayleigh beams under three different axial loading conditions - uniform loading, gravity-loading and centrifu-gally loaded. We assume simple polynomial mode shapes which satisfy the different boundary conditions of a particular beam, and derive the corresponding beam property variations. In case of the shared eigenpair, we use the mode shape of a uniform beam which has a closed-form solution and use it to derive the stiffness distribution of a corresponding axially loaded beam having same length, mass variation and boundary condition. For the Timoshenko beam, we assume polynomial functions for the bending displacement and the rotation due to bending. The derived properties are demonstrated as benchmark analytical solutions for approximate and numerical methods used for the free vibration analysis of beams. They can also aid in designing actual beams for a pre-specified frequency or nodal locations in some cases. The effect of different parameters in the derived property variations and the bounds on the pre-specified frequencies and nodal locations are also studied for certain cases. The derived analytical solutions can also serve as a benchmark solution for different statistical simulation tools to find the probabilistic nature of the derived stiffness distri-bution for known probability distributions of the pre-specified frequencies. In presence of uncertainty, this flexural stiffness is treated as a spatial random field. For known probability distributions of the natural frequencies, the corresponding distribution of this field is determined analytically for the rotating cantilever Euler-Bernoulli beams. The derived analytical solutions are also used to derive the coefficient of variation of the stiffness distribution, which is further used to optimize the beam profile to maximize the allowable tolerances during manufacturing.

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