Wrinkling of sandwich panel face plates (isotropic face plates on orthotropic cores, in-plane loading or bending).
Abstract:ESDU 88032 provides comprehensive data for estimating the wrinkling stress of the faceplates. The effect is taken into account of the faceplate properties and dimensions, the core shear moduli and through-thickness modulus, and the core dimensions. For in-plane loads (any combination o8f direct and shear) both symmetric and antisymmetric wrinkling modes are considered. The effect of material plasticity can be allowed for and comprehensive example calculations illustrate that. The implications of the theoretical models used are considered and guidance is provided on conditions where they may lead to an under- or over-estimate of the wrinkling stress of real structures. A method is given for estimating the reduction in wrinkling stress due to initial faceplate irregularities. Notes discuss the effects of variations in core properties and the possible influence of the faceplate/core adhesive layer.
|Data Item ESDU 88032|
- Aircraft Noise
- Fatigue - Endurance Data
- Fatigue - Fracture Mechanics
- Fluid Mechanics, Internal Flow
- Fluid Mechanics, Internal Flow (Aerospace)
- Heat Transfer
- Physical Data, Chemical Engineering
- Stress and Strength
- Transonic Aerodynamics
- Vibration and Acoustic Fatigue
- Wind Engineering
Aerospace Materials Data
Additional Engineering References