1. Compression-loaded cylindrical panels with circular holesarecommonlyfoundinaerospacestructuresandhave been the subject of considerableresearch in the past. The response of these panels is characterized by large local deformationsin theneighborhoodof thehole. Experimental and analyticalstudiesof the effects of circular holes on the postbucklingbehavior of composite cylindricalpanels have been performed16. This panel has been used herein to demonstrate the use of a curved interface element on a curved geometry. In addition, multiple and multiplyconnected interface elements and a closed interface are demonstrated. The panel is made of a 16-ply composite laminate [k45/02/P45/902]s. The panel length, L, and chord, c, are 14in., the hole diameter,a, is 2 in.,the panel radius, R, is 15 in. and the panel arc is 27.8 degrees. The loadingon the panel is uniform axialcompression,uo, (see Figure 5).The oppositeend of theplate is clampedandthe sidesaresimply-supportedby knife-edgerestraints.Theply properties are 19,600 ksi for the longitudinal Young's modulus, 1890ksi for the transverseYoung'smodulus,930 ksi for the shearmodulus, and 0.38forthemajor Poisson's ratio.Thenominalplythicknessis0.0056in.
2. Bathe,K.J., Finite Element Procedures inEngineering Analysis,PrenticeHall,NewJersey,1982.
3. Transition Plate Bending Elements with Variable Nodes