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.MsPlateBucklingFlatBendingData |
ABB.msPlateBucklingFlatBending(double e,
double nu,
double n,
double a,
double b,
double beta,
double t,
ABB.MaterialBehaviour behaviour,
double[] sigma1,
double[] sigma2)
MS Plate Buckling Flat Bending
Computes margin of safety of a flat metallic rectangular panel under bending load
The formula is MS = sigmaAllowable / abs(sigma) - 1
where:
'sigmaAllowable' is the bending buckling stress allowable
'sigma' is the compressive stress at one edge of the panel, sigma = min( sigma1, sigma2 )
'MS' is the margin of safety
Allowable = eta * PI^2*kb*E/(12*(1-nu^2)) * (t/b)^2
where
'kb' 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 unloaded edge length
'b' is the loaded edge length
'beta' Loading length ratio, the factor which, divided by b, gives the edge length in compression (while the remaining edge length is in tension).
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