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Nonlinear Finite Element Numerical Computation and Stability Analysis of Thin-wall Structure

Author: XiongXiaoFeng
Tutor: SunQin
School: Northwestern Polytechnical University
Course: Aircraft design
Keywords: Thin-walled reinforced structure Geometric nonlinearity Nonlinear finite element Nonlinear buckling analysis Stability
CLC: V214
Type: Master's thesis
Year: 2006
Downloads: 504
Quote: 10
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Abstract


Thin-walled reinforced structural stiffness , light weight , simple manufacturing , ease of maintenance , etc. are widely used in modern aircraft structural engineering , in order to give full play to the favorable stiffness role of the various components , to improve structural performance and reduce the weight of the structure to meet the load capacity and other purposes. Large aspect ratio wings in a large external force , the structure will have a large deformation , generally speaking , structural deformation geometrically nonlinear problem , the theory of linear elastic analysis may lead to considerable error , and therefore need to use non- The linear method of analysis and research . This paper summarizes the nonlinear structural analysis of the domestic and international research profile and stability theory , discussed in detail the geometrically nonlinear problem of stress and strain of expression format , Lagrangian and updated Lagrangian expression in the form of the nonlinear equations format , also discussed in detail certain numerical methods for nonlinear equations . On the basis of discussions in the theoretical analysis , this paper nonlinear finite element analysis techniques detailed study of nonlinear deformation and stability characteristics of the plate and stiffened panel under compression , consider the boundary conditions , different loading mesh density on the critical buckling load and compare the nonlinear analysis under the structure of the critical buckling load with linear buckling analysis under the critical buckling load with increasing mesh density , the critical buckling load will tend to a constant value . Different position node stress / displacement curve simultaneous extraction of the board , and the analysis and discussion of the structure of non-linear characteristics , the application of numerical calculation simulation studies in different parts of the continuum structure nonlinear evolution and force transformation process . This purpose nonlinear stability characteristics of a small box section , and individually removed separately on siding and web nonlinear stability analysis . Combination - experimental analog multi wall aspect ratio straight wing box segment structure , according to the actual experimental boundary with the loading conditions , the use of large finite element structural analysis software ANSYS nonlinear stability analysis , and the results were analyzed and compared with the experimental results . Finally, a summary of this research work , and pointed out the direction of further research this article .

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CLC: > Aviation, aerospace > Aviation > Basic theory and experiments > Aircraft Structural Mechanics
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