| With the rapid development of advanced composite materials, composites stiffenedpanels are more and more widely used in aerospace and other main force component.When subject to compression load and cutting load, the panel can easily goes tobuckling instability, but the structure has strong instability of the post-buckling bearingcapacity. This paper mainly studies stiffness matching problem of composite stiffenedpanel subject to combined biaxial compression and shear load.First, two finie element anlysis models ,which one is not contain floor beam andthe other is contain floor beam, of three configurations was taken on MSC.PATRAN,linear buckling analysis under axial compress load, shear load and combined biaxialcompression and shear load was anlysised on MSC.NASTRAN, the buckling factor andbuckling mode was computed, the result of axial comprssive load and the results ofsimplified engneering comutation were compared.Secondly, static damage experiment study of composite stiffened pannel isconducted. A kind of combined load experiemnt device was designed, the experimentwas taken on the MTS 2500KN electro-hydraulic servo test machine, 3 confugurations9 samples was ,damage load and typical failure pattern was carried on stiifened panelsubject to combined biaxial comprssion and shear load, strain of key position anddisplacement of device curve was drawed. The three confiugations have the same trend,so the combined load experiment posses reapeatbility, and the test proves the rationalityof the designed devcie.Thirdly, considering the nonlinear static analysis, the process of the test wassimulated, the result of the finite element analysis and the experiments compared witheach other, the results show that the result of FEM in good agreement with the result oftest,which also validated the FEM model.One configuration which stiffeness matches good was selected through simulationanalysis and experiment study of stiffened panel, which prvides for the design ofcomposite stiffened panel. |
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