Parametric modeling based stiffened wall plate structure vibration fatigueresistance optimization method

Abstract

The invention discloses a parametric modeling based stiffened wall plate structure vibration fatigue resistance optimization method and relates to an aircraftstiffened wall plate structure. The method comprises the following steps of 1 stiffened wall plate structure design, 2 optimization variable selection, 3 optimization flow and program development performing based on commercially used finite element software, 4 finite element parameter modeling, 5 random vibration response calculation under basic accelerated speedbroadbandstimulation, 6 extraction of a global stressroot-mean-square value, to serve as an optimization objective,in random vibration response, and optimization using structure optimization parameters and structural weight as constraints. The shortcomings of shape optimization and topological optimization can be overcome, and a selectable optimization parameter range is wider. The convenience and effectiveness of the parametric modeling based optimization method are embodied based on a commercially used finite element software platform, the optimization method can be suitable for a more complicated engineering structure. The optimization method is oriented to the global stressroot-mean-square value of a structure, aglobally optimal solution of the structure under a random load is obtained, and the vibration fatigue life of the structure can be effectively prolonged.

Description

technical field [0001] The invention relates to a stiffened panel structure of an aircraft, in particular to a method for optimizing the anti-vibration fatigue of a reinforced panel structure based on parametric modeling. Background technique [0002] In the design of aerospace structures, reducing the weight of the structure under the premise of meeting the requirements of use is one of the most concerned issues for designers. Therefore, thin-walled and reinforced panel structures are widely used for large-scale cavities and fuselage skins. . In order to solve the vibration fatigue problem of the aerospace stiffened panel structure, the stiffeners are usually arranged reasonably on the surface of the skin structure to enhance the stiffness of the skin structure and reduce the stress level of the structure. For the composite structure of reinforced panels, different structural forms and arrangements of reinforcements, and the degree of matching between reinforcement and ski...

AI Technical Summary

Problems solved by technology

[0003] Although shape optimization, topology optimization, and layout optimization have also begun to consider fatigue life factors, there are relatively few studies on optimization calculations that take the root mean square response of structural dynamic stress as a constraint or optimization objective under broadband random excitation.

In addition, for structural topology optimization and shape, it is generally impossible to overcome the problem that when the design variables change greatly, the element mesh of the finite element model is prone to deformity and cannot continue to optimize the solution