Elastic buckling of cylindrically curved laminated fibre reinforced composite panels with all edges simply-supported under biaxial loading.
Abstract:ESDU 94007 introduces a Fortran program, ESDUpac A9407, that calculates the buckling value of a uniform in-plane axial loading on the panel, with or without an additional circumferential loading due to normal pressure. Also output are the longitudinal buckle half wavelengths and, when pressure is considered, the circumferential buckle half wavelengths. The program applies to specially- orthotropic lay-ups, and will treat other lay-ups as if they were specially- orthotropic. It is based on elastic, thin plate, small deflection theory assuming the material to be homogeneous and orthotropic with the principal axes of orthotropy aligned with the rectangular plate edges. Through thickness shear is neglected. The equations on which the program is based are given, the input to the program is described in detail, its validation is discussed, and specimen input and output of several worked examples are included.
|Data Item ESDU 94007|
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- Fatigue - Endurance Data
- Fatigue - Fracture Mechanics
- Fluid Mechanics, Internal Flow
- Fluid Mechanics, Internal Flow (Aerospace)
- Heat Transfer
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- Stress and Strength
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- Vibration and Acoustic Fatigue
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Aerospace Materials Data
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