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This model was to be tested well into the post-buckled regime.
The model was made of polycarbonate. It was strengthened with widely spaced longitudinal members with large, rectangular cross-section and a relatively high value of geometric moment of inertia so that they would not buckle locally. The mid-length ring geometry was slender.
This 180-degree model was subjected to torsion. Results are shown in the next slide.
This and the next two slides are from:
Tomasz Kopecki (Rzeszów University of Technology, Faculty of Mechanical Engineering and Aeronautics, Rzeszów, Poland; e-mail: tkopecki@prz.edu.pl), “Chapter 8: Numerical Reproducing of a Bifurcation in the Stress Distribution Obtaining Process in Post-Critical Deformation States of Aircraft Load-Bearing Structures”, in the book, “Nonlinearity, Bifurcation and Chaos – Theory and Applications”, edited by Jan Awrejcewicz and Peter Hagedorn, ISBN 978-953-51-0816-0, October 21, 2012, DOI: 10.5772/48069
INTRODUCTION: Modern aviation structures are characterised by widespread application of thin-shell load-bearing systems. The strict requirements with regard to the levels of transferred loads and the need to minimise a structure mass often become causes for accepting physical phenomena that in case of other structures are considered as inadmissible. An example of such a phenomenon is the loss of stability of shells that are parts of load-bearing structures, within the range of admissible loads.
Thus, an important stage in design work on an aircraft load-bearing structure is to determine stress distribution in the post-critical deformation state. One of the tools used to achieve this aim is nonlinear finite elements method analysis. The assessment of the reliability of the results thus obtained is based on the solution uniqueness rule, according to which a specific deformation form can correspond to one and only one stress state. In order to apply this rule it is required to obtain numerical model’s displacements distribution fully corresponding to actual deformations of the analysed structure.
An element deciding about a structure’s deformation state is the effect of a rapid change of the structure’s shape occurring when the critical load levels are crossed. From the numerical point of view, this phenomenon is interpreted as a change of the relation between state parameters corresponding to particular degrees of freedom of the system and the control parameter related to the load. This relation, defined as the equilibrium path, in case of an occurrence of mentioned phenomenon, has an alternative character, defined as bifurcation. Therefore, the fact of taking a new deformation form by the structure corresponds to a sudden change to the alternative branch of the equilibrium path [1-4].
Therefore, a prerequisite condition for obtaining a proper form of the numerical model deformation is to retain the conformity between numerical bifurcations and bifurcations in the actual structure. In order to determine such conformity it is required to verify the results obtained by an appropriate model experiment or by using the data obtained during the tests of the actual object. It is often troublesome to obtain reliable results of nonlinear numerical analyses and it requires an appropriate choice of numerical methods dependent upon the type of the analysed structure and precise determination of parameters controlling the course of procedures.
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