Study On Shear Buckling Of Composite Beam Web

With the wide application of composite materials in the aerospace field, thecomposite beam webwith or without openings under pure shear condition becomesmore common.Technical personnel tend to get the buckling load of composite beamweb under such condition by using finite element and experiment methods. As to theresult of computing formula, which based on orthogonal anisotropic ideal laminatedplatewithout edge structure, is not accurate because the beam web is non-orthogonalanisotropy and has band structure in the actual application. What is more, there is noformula to compute the shear buckling load of beam web with openings.In this paper, orthotropic shear buckling calculation results of formula and finiteelement simulation results are compared to prove that the formula is available incomputing shear buckling loads of multi-layer symmetric composite laminates firstly.Secondly, by means of the finite element and experimental research, the finite elementsimulation is approved to be accuracy in predicting the shear buckling of compositebeam webs and those containing the openings. On this basis, by fitting a lot of finiteelement simulation data, the correction of formula for orthotropic laminated shearbuckling is completed which makes the new formula suitable for composite beam webwith edge structure. Based on the previous work, the formula for composite with acircular, rhombic, oblong opening is created also by fitting a lot of finite elementsimulation data.Verified by experimental data and finite element simulation, calculations showthat the new empirical formula results highly accurate and applicable.