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.MsPlateBucklingCurvedLongitudinalShearCombinedData |
ABB.msPlateBucklingCurvedLongitudinalShearCombined(double e,
double nu,
double n,
double a,
double b,
double t,
ABB.EdgeSupportType bc,
double r,
ABB.MaterialBehaviour behaviour,
double[] sigma,
double[] tau)
MS Plate Buckling Curved Longitudinal Shear Combined
Computes margin of safety of a rectangular curved metallic panel in buckling under combined shear and longitudinal loads
Under compressive loads
Under compressive and shear loads, the interaction equation is:
RL^2 + RS^2 = 1.0
The Margin Safety is given by the following formula:
MS=2/(RL+sqrt(RL^2+4*RS^2))-1
where:
RL = sigma / sigma_cr is the stress ratio due to longitudinal stress, with:
sigma is the given longitudinal stress
sigma_cr is the compression stress allowable for buckling (sigma_cr < 0, as consequence RL < 0 in tension)
RS = tau / tau_cr is the stress ratio due to shear stress with:
tau is the given shear stress
tau_cr is the shear stress allowable for buckling (tau and tau_cr always positive)
Under tensile loads
Under tensile and shear loads, the interaction equation is:
1/2 * RL + RS = 1.0
The Margin Safety is given by the following formula:
MS = (2 - RL) / ( 2 * RS ) - 1
The panel edges are either clamped or simply supported.
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