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.MsPlateBucklingFlatShearBendingCombinedData |
ABB.msPlateBucklingFlatShearBendingCombined(double e,
double nu,
double n,
double a,
double b,
double t,
ABB.UnloadedEdgeSupportType bcUnloaded,
ABB.EdgeSupportType bcLoaded,
ABB.MaterialBehaviour behaviour,
double[] sigma1,
double[] sigma2,
double[] tau)
MS Plate Buckling Flat Shear Bending Combined
Computes margin of safety of a rectangular flat metallic panel in buckling under combined bending and shear loads
Under longitudinal and shear loads, the interaction equation is:
MS = 1 / sqrt(Rb ^ 2 + Rs ^ 2)
This formula is derived from the interaction equation
Rb ^ 2 + Rs ^ 2 = 1.0
where:
Rb = sigmab / sigmabcr is the stress ratio due to bendoing stress with
sigmab is the given compressive stress due to bending
sigmabcr is the bending stress allowable for buckling
Rs = tau / taucr is the stress ratio due to shear stress with
tau is the given shear stress
taucr is the shear stress allowable for buckling (taucr and tau always positive)
Input
E Young's modulus
nu Elastic Poisson coefficient
n Ramberg-Osgood parameter
a Unloaded edge length
b Loaded edge length
t Panel thickness
BC_Unloaded Type of support along unloaded edges {'Clamped-Clamped';'Simply Supported-Clamped';'Simply Supported-Simply Supported';'Free-Clamped';'Free-Simply Supported'}
BC_Loaded Type of support along loaded edges {'Clamped';'Simply Supported'}
behaviour Material behaviour {'Elastic'; 'Elastic-Plastic'}
nblc Number of load cases
sigma1 Stress XX Side1
sigma2 Stress XX Side2
tau Stress XY
Output
taucr Shear stress allowable that takes into account compressive/tensile stress
sigmabcr Bending 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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