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.MsPlateBucklingCurvedShearData |
ABB.msPlateBucklingCurvedShear(double e,
double nu,
double n,
double a,
double b,
double t,
ABB.EdgeSupportType bc,
double r,
ABB.MaterialBehaviour behaviour,
double[] sigma)
MS Plate Buckling Curved Shear
Computes margin of safety of a curved metallic rectangular panel under shear load
The formula is MS = Allowable / |Stress| - 1
where:
'Allowable' is the compressive buckling stress allowable
'Stress' 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/c)^2
where
'ks' is the buckling coefficient
'E' is the Young modulus
'nu' is the elastic Poisson coefficient
't' is the panel thickness
'c' is the shorter panel dimension c = min(a,b)
'eta' is the plasticity reduction factor: SigmaAllowablePlastic = eta*SigmaAllowableElastic
eta = 1 if material is considered as elastic (Material behaviour = Elastic)
eta is obtained from the MetallicPanelCompressivePlasticityCurveBC1 charts if material is considered as elastic-plastic (Material behaviour = Elastic-Plastic):
SigmaAllowablePlastic/Sigma0.7 = f(SigmaAllowableElastic/Sigma0.7)
Sigma0.7 is the stress for secant modulus equal to 70% of Young modulus
Input
E Young modulus
nu Elastic Poisson coefficient
n Ramberg-Osgood parameter
a Longer panel dimension
b Shorter panel dimension
t Panel thickness
BC Type of support along edges
r Panel radius of curvature
behaviour Material behaviour
nblc Number of load cases
sigma Stress coming from load extraction
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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