Method of fast simulation,calculation and modeling of aircraft panel's riveting deformation based on sub-structures
The large-size aircraft panel is an important component that constitutes the aircraft's aerodynamic shape.It has such characteristics as large size,thin walls and weak rigidity.It is vulnerable to assembly deformation during the process of auto-matic drilling and riveting,including local deformation of the connection part as well as overall bending and torsion of the panel.In this article,in response to such problems as a large number of riveted aircraft panels as well as a large amount of deformation-based simulation and calculation,a finite-element method of fast simulation and modeling is proposed based on sub-structures.Firstly,the panel's riveting part is divided into some local sub-structures for separate calculation;then sub-structures are assem-bled with the peripheral panel;finally,the bending moment which is separately calculated can be applied as a load to the assem-bly entity for calculation.By setting up a sub-structure model,the final simulation model is greatly simplified while meeting the accuracy requirement.Such problems caused by the model of continuous calculation as a huge amount of calculation data,low ef-ficiency,and being prone to unit distortion are solved,thus making it possible to simulate and calculate a large amount of riveting for large-size panels as well as predict the overall riveting deformation.
aircraft panelassembly and rivetingdeformation analysisnumerical modelingfinite-element simulation
NETL
NSTL
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