Elastic stresses and deflections under uniform pressure of flat rectangular sandwich panels; long edges clamped, short edges simply-supported (isotropic face plates and orthotropic cores of zero flexural stiffness).
Abstract:ESDU 76022 gives graphs enabling the maximum deflection and the maximum direct and shear stresses to be found in initially flat panels. The method assumes the face plates have the same Poisson's ratio but they can have different thicknesses and moduli of elasticity. The curves were calculated from elastic small deflection theory assuming the face plates to be thin and the core infinitely stiff in the through-thickness direction. These assumptions will be valid for panel thickness/face plate thickness greater than 6, for panel length/panel thickness greater than 10, and for deflection/panel thickness less than 0.5.
|Data Item ESDU 76022|
- 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