Package | Description |
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nxopen.cae.aerostructures.author |
Provides classes and interfaces relating to Aero Structures Author.
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Modifier and Type | Method and Description |
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ABB.MsPlateBucklingFlatShearData |
ABB.msPlateBucklingFlatShear(double e,
double nu,
double n,
double a,
double b,
double t,
ABB.EdgeSupportType bc,
ABB.MaterialBehaviour behaviour,
double[] sigma)
MS Plate Buckling Flat Shear
Computes margin of safety of a flat metallic rectangular panel under shear load
The formula is MS = sigmaAllowable / abs(sigma) - 1
where:
'sigmaAllowable' is the shear buckling stress allowable,
'sigma' is the compressive stress (MS is not calculated in case of tensile stress),
'MS' is the margin of safety
Allowable = eta * PI^2*ks*E/(12*(1-nu^2)) * (t/b)^2
where
'ks' is the bending buckling stress coefficient
'E' is the Young's modulus
'nu' is the elastic Poisson coefficient
't' is the panel thickness
'a' is the panel longer dimension
'b' is panel shorter dimension
'eta' is the plasticity reduction factor: SigmaAllowablePlastic = eta*SigmaAllowableElastic
eta = 1 if material is considered as elastic (Material behaviour = Elastic)
eta is obtain from following charts if material is considered as elastic-plastic (Material behaviour = Elastic-Plastic):
SigmaAllowablePlastic/Sigma0.7 = f(SigmaAllowableElastic/Sigma0.7)
MetallicPanelCompressivePlasticityCurveBC1, Warning: in fact graph is fig C5.13 but it is C5.7 graph divided by 2
Input
E Young's modulus
nu Elastic Poisson coefficient
n Ramberg-Osgood parameter
a Panel longer dimension
b Panel shorter dimension
t Panel thickness
BC Type of support along the edges {'Clamped';'Simply Supported'}
behaviour Material behaviour
nblc Number of load cases
sigma Stress coming from load extractor
Output
sigmaAllowable Stress allowable
MS Margin of safety
Return
Status of the calculation
License requirements: nx_masterfem ("Finite Element Modeling") Created in NX12.0.0 |
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