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.MsPlateBucklingFlatLongitudinalShearCombinedData |
ABB.msPlateBucklingFlatLongitudinalShearCombined(double e,
double nu,
double n,
double a,
double b,
double t,
ABB.UnloadedEdgeSupportType bcUnloaded,
ABB.EdgeSupportType bcLoaded,
ABB.MaterialBehaviour behaviour,
double[] sigma,
double[] tau)
MS Plate Buckling Flat Longitudinal Shear Combined
Computes margin of safety of a rectangular flat metallic panel in buckling under combined shear and longitudinal loads
Under longitudinal and shear loads, the interaction equation is:
MS=2/(RL + sqrt(RL ^ 2 + 4 * RS ^ 2)
This formula is derived from the interaction equation RL+R2S=1.0
RL + RS ^ 2 = 1.0
where:
RL = sigma / sigmacr is the stress ratio due to longitudinal stress, with:
sigma is the given longitudinal stress
sigmacr is the compression stress allowable for buckling (sigmacr < 0, as consequence RL < 0 in tension)
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)
The panel edges are either clamped or simply supported.
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