Numerical Simulation Of Static Failure Process Of Typical Aircraft Wing-box

Large numbers of multi-level structure experiments are needed during the process of aircraft design. With the rapid development of computational structure technology, it is possible that numerical simulation partially replace the real physical experiments. It can save many resources and shorten the period of development. At present, using virtual experiments to evaluate the strength of the real aircraft structure has become one of the most important research directions. Therefore it is significant and valuable to study the numerical simulation of failure process for typical aircraft structure.This article simulated the static damage process of the typical aircraft wing-box using ABAQUS. Firstly, a FEM model of the wing-box was founded according to its geometrical configuration characters. Using the least squares theory, the optimum load case that satisfied the foregone stress level was obtained. Secondly, by analyzing the global FEA model of wing-box, the dangerous locations were established exactly, which would be used in the following detail analysis. Finally, in order to simulate the damage process of the structure under simple loads, failure criterions and corresponding degradation schemes were defined based on the dangerous locations and configuration characters of the wing-box. The relationship between node displacement and loads of typical area was also discussed.Through the numerical simulation studies mentioned above, the ultimate strength of the typical aircraft wing-box and the process of the failure were abstractly carried out. The analysis results and conclusion of this paper can offer some useful reference to the wing-box structural experiment.