Analysisof laminatesafterinitial...
Transcript of Analysisof laminatesafterinitial...
Analysis of laminates after initial failure
Accounting for the modificationof stiffness in the failed layers
Common practice: set all lamina properties to zero when failure occurs(gives a conservative estimate of the load carrying capacity)
for the failed ply
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Example: 5 mm symmetric cross‐ply constructed from 15 identical laminae9 li 0° d 6 li 90° l d i i N9 plies at 0° and 6 plies at 90°, load in traction Nx
Step 1: Failure of the 90° plies
Extensional stiffness matrix before failure of the 90° plyExtensional stiffness matrix before failure of the 90° ply
Step 2: failure of the first ply (maximum strain theory)
Failure stresses
Calculation of the failure strains
Failure strains
The 90° ply will fail when x=0.00153
The load Nx leading to the failure of the 90° ply is solution of
Step 3: Behaviour after failure of the first ply
After the failure of the 90° ply,
Q = 0
Step 3: Behaviour after failure of the first ply
Q 90° = 0
The failure occurs for
Flowchart for laminatestrength analysis
Short fiber composites
•Convenient for complex geometries•Convenient for complex geometries•Can be mixed with liquid resin and used in injection molding(in injection moulding, the final orientation of the fibers depends on the flow in the mould)•Random oriented fibers are nearly isotropic•Not suitable for critical structures (less strength and stiffness),
but this may change with carbon nanotubes
Glass fiber reinforced nylon with random fiber orientation (Agarwall, Fig 4.11) 1
Stress transfer theory for aligned discontinuous fibers composites
Matrix shear deformation in a representative volume (Gibson)
Equilibrium along z:
0
The stress at the fiber end is neglected
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We assume a rigid‐plastic behaviour of the matrix.(the interface shear stress is constant y)For short fibers the fiber stress is linearFor short fibers, the fiber stress is linear
And the maximum occurs at the middle of the fiber
However, the fiber stress cannot exceed the stress thatwould occur in a continuous fiber , for whichThis corresponds to
The load transfer length is the Minimum length which allowsMinimum length which allowsto reach this value
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For a fixed length l, if one increases the composite stress cThe fiber stress cannot exceed the fiber ultimate stress The fiber stress cannot exceed the fiber ultimate stress fuThe critical fiber length is that which allows to reach fu:
lc is also called« Ineffective length »
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Numerical results: 1. Elastic analysis
r<0: friction forces ll l d f iallow load transfer in
case of interface failure)
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Numerical results: 2. Elastic‐plastic analysis
Interfacial shear stress near fiberend is not constant, because of 3‐D
yield stress criterion is used.
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Modulus of aligned discontinuous fiber composites
Halpin‐Tsai (curve fitting on numerical solutions)
(Same as for transverse modulus of continuous fibers with =2l/d )
(Same as for transverse modulus of continuous circular fibers : =2 )
Variation of EL of aligned short fibers as a functionof the aspect ratio l/d, for differnet values of Ef/Em
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Asymptotic value of EL for large l/dL
(Halpin‐Tsai converges towards the rule of mixture)
Modulus of short fiber composites with randomly oriented fibers
Empirical formulae:
With EL and ET corresponding to aligned short fibers withthe same aspect ratio l/d and the same volume fraction Vf
Since the material is isotropic, 8
1. Aligned short fibers (Halpin‐Tsai)
2. Random fiber orientation
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2. Random fiber orientation
Strength of aligned short‐fiber composites
If l>lc, the fibers will reach the failure stress fu
For very small fiber volume fractions: the value for continuous fibers
is further lowered by large stress concentrations
Strength of randomly oriented short fibers
Strength predictions obtained by replacing the randomly oriented composite by a quasi‐isotropicStrength predictions obtained by replacing the randomly oriented composite by a quasi isotropiccontinuous laminate with the same volume fraction correlate well with experiments.
Equivalent quasi‐isotropic laminate:Analysis up to the failure of all plies
Maximum strain theory10
Sandwich structures
Plates with similar flexural rigidity EI
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Simplified stress analysis in sandwich structures
Bending stresses are in the skin only, and uniform. Shear stresses are in the core only, and uniform.The bending deflection is dependent on the tensile and compressive moduli in the skin material.The shear deflection is dependent on the shear modulus in the core
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The shear deflection is dependent on the shear modulus in the core.
Sandwich panel failure modes (Hexcel composites)
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14http://www.hexcel.com/Resources/DataSheets/Brochure‐Data‐Sheets/Honeycomb_Sandwich_Design_Technology.pdf