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.MsPlateBucklingFlatLongitudinalBendingCombinedData |
ABB.msPlateBucklingFlatLongitudinalBendingCombined(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)
MS Plate Buckling Flat Longitudinal Bending Combined
Computes margin of safety of a rectangular flat metallic panel in buckling under combined bending and longitudinal loads
This formula is derived from the interaction equation
Rb ^ 1.75 + Rc = 1.0
where:
Rc = sigmac / sigmacr is the stress ratio due to compression stress, with:
sigmac is the given longitudinal stress
sigmacr is the compression stress allowable for buckling
Rb = sigmab / sigmabcr is the stress ratio due to bending stress with
sigmab is the given compressive stress due to bending
sigmabcr is the bending stress allowable for buckling
Input
E Young's modulus
nu Elastic Poisson coefficient
n Ramberg-Osgood parameter
a Unloaded edge length
b Loaded edge length
beta Loading length ratio
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
nblc Number of load cases
sigma1 Stress XX Side1
sigma2 Stress XX Side2
Output
sigmacr Compressive stress allowable
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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