2Composite panel design Laminate analysis gives the fundamental information on stiffness, elastic constants and uniaxial strengths.For structural analysis, we need in-plane stiffness [A] and flexural rigidity [D].
3A11D66D22D12A12D11A22Remember that these values depend on laminate thickness.
4Composite panel design For convenience, D1 = D11, D2 = D22, D3 = D D66For a homogeneous orthotropic plate, thickness h: D1 = Ex h3 / 12m D2 = Ey h3 / 12m D66 = Gxy h3 / 12 where m = 1 - nxy nyx = 1 - nxy2 Ey / Ex
5Composite panel design For in-plane loads, the elastic constants are used in the normal way.Under uniaxial compression, a plate is likely to buckle at some critical load Nx’.Buckling loads depend on geometry, edge conditions and flexural properties.Thin plates may fail by shear buckling before shear failure load.
6Buckling of Composite Panels For small aspect ratios (0.5 < a/b < 2):For long, simply-supported plates with a/b > 2, buckling is independent of length: where
7Transverse Loading of Composite Panels Transverse point load P, or uniform pressure p, so that P = p a b:Maximum transverse panel deflection is: with max bending moments andab
8Transverse Loading of Composite Panels The design parameters a, b1 and b2 depend on plate aspect ratio, flexural stiffness, edge conditions and load:Hollaway (ed), Handbook of Polymer Composites for Engineers
9Thin walled beam design Standard isotropic design formulae for deflections may be used, but check whether a shear correction is required: where D is the flexural rigidity and Q is the shear stiffness.
10Hollaway (ed), Handbook of Polymer Composites for Engineers
11Thin walled beam design In torsion, wall buckling may be a critical condition.In general, several failure modes are possible - a systematic design procedure is required.Laminates may have different tensile and compressive strengths.Powell, Engineering with Fibre-Polymer Laminates
12Sandwich Construction Thin composite skins bonded to thicker, lightweight core.Large increase in second moment of area without weight penalty.Core needs good shear stiffness and strength.Skins carry tension and compression loads.
13Sandwich panels are a very efficient way of providing high bending stiffness at low weight. The stiff, strong facing skins carry the bending loads, while the core resists shear loads. The principle is the same as a traditional ‘I’ beam:
14Bending stiffness is increased by making beams or panel thicker - with sandwich construction this can be achieved with very little increase in weight:
15The stiff, strong facing skins carry the bending loads, while the core resists shear loads. Total deflection = bending + shearBending depends on the skin properties; shear depends on the core
16Foam core comparisonPVC (closed cell) - ‘linear’ – high ductility, low properties - ‘cross-linked’ – high strength and stiffness, but brittle - ~ 50% reduction of properties at 40-60oC - chemical breakdown (HCl vapour) at 200oC
17Foam core comparisonPU - inferior to PVC at ambient temperatures - better property retention (max. 100oC)Phenolic - poor mechanical properties - good fire resistance - strength retention to 150oC
18Foam core comparisonSyntactic foam - glass or polymer microspheres - used as sandwich core or buoyant filler - high compressive strengthBalsa - efficient and low cost - absorbs water (swelling and rot) - not advisable for primary hull and deck structures; OK for internal bulkheads, etc?
21Why honeycomb? List compiled by company (Hexcel) which sells honeycomb!
22Sandwich constructions made with other core materials (balsa, foam, etc) have a large surface are available for bonding the skins.In honeycomb core, we rely on a small fillet of adhesive at the edge of the cell walls:The fillet is crucial to the performance of the sandwich, yet it is very dependent on manufacturing factors (resin viscosity, temperature, vacuum, etc).
23Honeycomb is available in polymer, carbon, aramid and GRP Honeycomb is available in polymer, carbon, aramid and GRP. The two commonest types in aerospace applications are based on aluminium and Nomex (aramid fibre-paper impregnated with phenolic resin).Cells are usually hexagonal:but ‘overexpanded’ core is also used to give extra formability:
24Core properties depend on density and cell size Core properties depend on density and cell size. They also depend on direction - the core is much stronger and stiffer in the ‘ribbon’ or ‘L’ direction:
25Aluminium generally has superior properties to Nomex honeycomb, e.g:
26Aluminum Honeycomb • relatively low cost • best for energy absorption • greatest strength/weight • thinnest cell walls • smooth cell walls • conductive heat transfer • electrical shielding • machinabilityAramid Fiber (Nomex) Honeycomb • flammability/fire retardance • large selection of cell sizes, densities, and strengths • formability and parts-making experience • insulative • low dielectric properties
27Sandwich Construction Many different possible failure modes exist, each of which has an approximate design formula.
31Design Formulae for Sandwich Construction core: tensile modulus Ec shear modulus Gcskin: tensile modulus Esd = c + t
32Sandwich Construction - flexural rigidity Neglecting the core stiffness:Including the core:If core stiffness is low:
33Sandwich Construction - flexural rigidity Shear stiffness is likely to be significant: where shear stiffness Q = b c GcIf D/L2Q < 0.01, shear effects are small.If D/L2Q > 0.1, shear effects are dominant.
34Sandwich Construction - flexural rigidity Plate stiffnesses can be calculated by CLA, but shear effects must be considered.Formula for plate deflection is of the form: where the transverse shear stiffness is now Q = c Gc. a is the longest side of a rectangular panel.
36Bending stresses in sandwich beams It is often assumed that the core carries no bending stress, but are under a constant shear stress. For an applied bending moment M:Skin stressCore shear stress: where S is the shear force y is distance from neutral axisIf core stiffness can be neglected: