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NXOpen .NET Reference Guide
1899
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NXOpen .NET Reference Guide
1899
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Represents a AeroStruct application building block (ABB) More...
Public Types | |
| enum | EdgeSupportType { SimplySupported, Clamped } |
| Support along the edges, the choice is between SimplySupported and Clamped More... | |
| enum | MaterialBehaviour { Elastic, ElasticPlastic } |
| Material behaivour type, the choices are: {Elastic, Elastic-plastic} More... | |
| enum | PlaneStressBoundaryConditions { Ssss, Cscs, Scsc, Cccc, Sfss } |
| Plane stress boundary conditions, the choices are: {SSSS, SCSC, CCCC, SFSS} More... | |
| enum | Status { Success, Failed } |
| ABB return status More... | |
| enum | UnloadedEdgeSupportType { ClampedClamped, SimplySupportedClamped, SimplySupportedSimplySupported, FreeClamped, FreeSimplySupported } |
| Support along unloaded edges, the choices are: {Clamped-Clamped, Simply Supported-Clamped, Simply Supported-Simply Supported, Free-Clamped, Free-Simply Supported} More... | |
Public Member Functions | |
| unsafe NXOpen.CAE.AeroStructures.Author.ABB.Status | CurvedMetallicPanelCompressiveBucklingCoefficient (NXOpen.CAE.AeroStructures.Author.AbbContext abbContext, double b, double t, double r, double nu, out double kc) |
| Curves for finding 'kc' the compressive-buckling coefficient for curved sheet panel More... | |
| unsafe NXOpen.CAE.AeroStructures.Author.ABB.Status | CurvedMetallicPanelShearBucklingCoefficient (NXOpen.CAE.AeroStructures.Author.AbbContext abbContext, double a, double b, double t, double r, double nu, NXOpen.CAE.AeroStructures.Author.ABB.EdgeSupportType bc, out double ks) |
| Curves for finding 'ks' the shear-buckling coefficient for curved sheet panel More... | |
| unsafe NXOpen.CAE.AeroStructures.Author.ABB.Status | EquivalentSectionProperties (NXOpen.CAE.AeroStructures.Author.AbbContext abbContext, double[] iAi, double[] iYcog, double[] iEi, double[] iIxxi, out double[] a, out double[] oYcog, out double[] e, out double[] oIxx) |
| Compute equivalent section properties (area, center of gravity, Young's modulus and inertia) of a profile composed of different sub-sections. More... | |
| unsafe NXOpen.CAE.AeroStructures.Author.ABB.Status | ExtrudedMetallicSubSectionCripplingAllowable (NXOpen.CAE.AeroStructures.Author.AbbContext abbContext, double iFcy, double e, int fe, double b, double t, out double iFcc) |
| Compute Crippling stress allowable for a given segment More... | |
| unsafe NXOpen.CAE.AeroStructures.Author.ABB.Status | FlatMetallicPanelBendingBucklingCoefficient (NXOpen.CAE.AeroStructures.Author.AbbContext abbContext, double aOverB, double beta, out double kb) |
| Curves for finding the bending buckling stress coefficient for thin flat plates More... | |
| unsafe NXOpen.CAE.AeroStructures.Author.ABB.Status | FlatMetallicPanelCompressiveBucklingCoefficient (NXOpen.CAE.AeroStructures.Author.AbbContext abbContext, double a, double b, NXOpen.CAE.AeroStructures.Author.ABB.UnloadedEdgeSupportType bcUnloaded, NXOpen.CAE.AeroStructures.Author.ABB.EdgeSupportType bcLoaded, out double kc) |
| Curves for finding 'kc' the compressive-buckling coefficient for rectangular metallic flat plate More... | |
| unsafe NXOpen.CAE.AeroStructures.Author.ABB.Status | FlatMetallicPanelShearBucklingCoefficient (NXOpen.CAE.AeroStructures.Author.AbbContext abbContext, double a, double b, NXOpen.CAE.AeroStructures.Author.ABB.EdgeSupportType bc, out double ks) |
| Curves for finding 'ks' the shear-buckling coefficient for flat rectangular plate More... | |
| unsafe int | GetIntegerNa () |
| Integer NA value More... | |
| unsafe double | GetMsThreshold () |
| The MS (margin of safety) threshold More... | |
| unsafe double | GetPi () |
| PI number More... | |
| unsafe double | GetRealEpsilon () |
| Real epsilon More... | |
| unsafe double | GetRealMax () |
| Maximum real number More... | |
| unsafe double | GetRealNa () |
| Real NA More... | |
| unsafe double | GetRealNegativeInfinity () |
| The negative infinity value More... | |
| unsafe double | GetRealPositiveInfinity () |
| The positive infinity value More... | |
| unsafe double | GetUltimateLimitFactor () |
| Ultimate limit factor from the customer default More... | |
| unsafe bool | IsRealNa (double value) |
| Tests if a value is NA More... | |
| unsafe bool | IsRealNegativeInfinity (double value) |
| Tests if a value equals negative infinity More... | |
| unsafe bool | IsRealPositiveInfinity (double value) |
| Tests if a value equals positive infinity More... | |
| unsafe NXOpen.CAE.AeroStructures.Author.ABB.Status | LoadDistributionBoltsConcentricLoads (NXOpen.CAE.AeroStructures.Author.AbbContext abbContext, double[] p, double[] iPsn, out double[] oPn) |
| Computes bolt loads for multiple bolt fitting - Concentric load More... | |
| unsafe NXOpen.CAE.AeroStructures.Author.ABB.Status | MaterialFsyEstimation (NXOpen.CAE.AeroStructures.Author.AbbContext abbContext, double iFtyL, double iFtyLT, double iFcyL, double iFcyLT, double iFsu, double iFtuL, double iFtuLT, out double oFsy) |
| Estimation of shear yield stress (Fsy) More... | |
| unsafe NXOpen.CAE.AeroStructures.Author.ABB.Status | MetallicPanelCompressivePlasticityCurveBc1 (NXOpen.CAE.AeroStructures.Author.AbbContext abbContext, double x, double n, out double z) |
| Metallic panel compressive plasticity curve BC1 Curves for finding critical buckling stress / secant yield stress F0. More... | |
| unsafe NXOpen.CAE.AeroStructures.Author.ABB.Status | MetallicPanelCompressivePlasticityCurveBc2 (NXOpen.CAE.AeroStructures.Author.AbbContext abbContext, double x, double n, out double z) |
| Metallic panel compressive plasticity curve BC2 Curves for finding critical inter-rivet buckling stress (or critical wrinkling stress) / secant yield stress F0. More... | |
| unsafe NXOpen.CAE.AeroStructures.Author.ABB.Status | MetallicPanelCompressivePlasticityCurveBc3 (NXOpen.CAE.AeroStructures.Author.AbbContext abbContext, double x, double n, out double z) |
| Metallic panel compressive plasticity curve BC3 Curves for finding critical buckling stress / secant yield stress F0. More... | |
| unsafe NXOpen.CAE.AeroStructures.Author.ABB.Status | MsAllowable (NXOpen.CAE.AeroStructures.Author.AbbContext abbContext, double allowable, double[] value, out double[] ms) |
| MS allowable. More... | |
| unsafe NXOpen.CAE.AeroStructures.Author.ABB.Status | MsBearing (NXOpen.CAE.AeroStructures.Author.AbbContext abbContext, double d, double t, double iFbr, double f, double[] p, out double[] ms) |
| MS bearing Computes margin of bearing More... | |
| unsafe NXOpen.CAE.AeroStructures.Author.ABB.Status | MsBoltBending (NXOpen.CAE.AeroStructures.Author.AbbContext abbContext, double b, double iMba, double f, double[] p, out double[] ms) |
| MS bolt bending Computes margin of safety of a bolt under bending load More... | |
| unsafe NXOpen.CAE.AeroStructures.Author.ABB.Status | MsBoltCombinedShearTension (NXOpen.CAE.AeroStructures.Author.AbbContext abbContext, double iPtx, double iPss, double[] iPx, double f, double[] p, out double[] ms) |
| MS bolt combined shear tension Computes margin of safety of a bolt under shear load and tension load More... | |
| unsafe NXOpen.CAE.AeroStructures.Author.ABB.Status | MsBoltCombinedShearTensionBending (NXOpen.CAE.AeroStructures.Author.AbbContext abbContext, double b, double iMba, double iPtx, double iPss, double fb, double[] iPb, double[] iPx, double fs, double[] iPs, out double[] ms) |
| MS bolt combined shear tension bending Computes margin of safety of a bolt under shear, tension and bending load More... | |
| unsafe NXOpen.CAE.AeroStructures.Author.ABB.Status | MsBoltShear (NXOpen.CAE.AeroStructures.Author.AbbContext abbContext, double iPss, double f, double[] p, out double[] ms) |
| MS bolt shear Computes margin of safety of a bolt under shear load More... | |
| unsafe NXOpen.CAE.AeroStructures.Author.ABB.Status | MsColumnEccentricLoadSecantFormula (NXOpen.CAE.AeroStructures.Author.AbbContext abbContext, double a, double l, double e, double i, double sigmacr, double c, double ecc, double extrmfbrdist, double[] sigma, out double iPcr, out double[] ms) |
| MS Column Eccentric Load More... | |
| unsafe NXOpen.CAE.AeroStructures.Author.ABB.Status | MsColumnEngesser (NXOpen.CAE.AeroStructures.Author.AbbContext abbContext, double a, double l, double e, double i, double n, double iFy, double c, double[] sigma, out double sigmacr, out double[] ms) |
| MS Engesser More... | |
| unsafe NXOpen.CAE.AeroStructures.Author.ABB.Status | MsColumnEuler (NXOpen.CAE.AeroStructures.Author.AbbContext abbContext, double a, double l, double e, double i, double c, double[] sigma, out double sigmacr, out double[] ms) |
| MS Euler More... | |
| unsafe NXOpen.CAE.AeroStructures.Author.ABB.Status | MsColumnJohnsonEuler (NXOpen.CAE.AeroStructures.Author.AbbContext abbContext, double a, double l, double i, double e, double c, double sigma0, double[] sigma, out double sigmacr, out double[] ms) |
| MS Column Johnson-Euler More... | |
| unsafe NXOpen.CAE.AeroStructures.Author.ABB.Status | MsColumnTorsionalbuckling (NXOpen.CAE.AeroStructures.Author.AbbContext abbContext, double l, double e, double g, double j, double gamma, double r0, double c, double[] load, out double iPcr, out double[] ms) |
| MS Torsional Buckling More... | |
| unsafe NXOpen.CAE.AeroStructures.Author.ABB.Status | MsCompositePlateBucklingFlatCompressive (NXOpen.CAE.AeroStructures.Author.AbbContext abbContext, double b, double a, NXOpen.CAE.AeroStructures.Author.ABB.PlaneStressBoundaryConditions bc, NXOpen.CAE.AeroStructures.Laminate laminate, double[] sigma, out double[] ms, out double sigmaAllowable) |
| Computes margin of safety of a rectangular flat composite panel in buckling under compressive loads. More... | |
| unsafe NXOpen.CAE.AeroStructures.Author.ABB.Status | MsCompositePlateBucklingFlatLongitudinalShearCombined (NXOpen.CAE.AeroStructures.Author.AbbContext abbContext, double b, double a, NXOpen.CAE.AeroStructures.Author.ABB.PlaneStressBoundaryConditions bc, NXOpen.CAE.AeroStructures.Laminate laminate, double[] sigma, double[] tau, out double[] ms, out double sigmaAllowable, out double tauAllowable) |
| Computes margin of safety of a rectangular flat composite panel in buckling under combined shear and longitudinal loads. More... | |
| unsafe NXOpen.CAE.AeroStructures.Author.ABB.Status | MsCompositePlateBucklingFlatShear (NXOpen.CAE.AeroStructures.Author.AbbContext abbContext, double b, double a, NXOpen.CAE.AeroStructures.Author.ABB.PlaneStressBoundaryConditions bc, NXOpen.CAE.AeroStructures.Laminate laminate, double[] tau, out double[] ms, out double tauAllowable) |
| Computes margin of safety of a rectangular flat composite panel in buckling under shear loads. More... | |
| unsafe NXOpen.CAE.AeroStructures.Author.ABB.Status | MsInterrivetbucklingColumn (NXOpen.CAE.AeroStructures.Author.AbbContext abbContext, double t, double p, NXOpen.CAE.AeroStructures.Author.ABB.MaterialBehaviour behaviour, double e, double iFy, double n, double c, double[] sigma, out double[] ms) |
| MS Inter-rivet buckling (Column) More... | |
| unsafe NXOpen.CAE.AeroStructures.Author.ABB.Status | MsInterrivetbucklingWidecolumn (NXOpen.CAE.AeroStructures.Author.AbbContext abbContext, double t, double p, NXOpen.CAE.AeroStructures.Author.ABB.MaterialBehaviour behaviour, double e, double nu, double n, double iFy, double c, double[] sigma, out double[] ms) |
| MS Inter-rivet buckling (wide column) More... | |
| unsafe NXOpen.CAE.AeroStructures.Author.ABB.Status | MsNetSection (NXOpen.CAE.AeroStructures.Author.AbbContext abbContext, double d, double b, double t, double iFx, double f, double[] p, out double[] ms) |
| MS Net section Computes margin of net section (due to bolt hole) More... | |
| unsafe NXOpen.CAE.AeroStructures.Author.ABB.Status | MsPlateBuckling (NXOpen.CAE.AeroStructures.Author.AbbContext abbContext, double b, double t, double e, double nu, double eta, double k, double[] sigma, out double[] ms) |
| MS Plate Buckling Computes margin of safety of a metallic plate under buckling load (generic formula) More... | |
| unsafe NXOpen.CAE.AeroStructures.Author.ABB.Status | MsPlateBucklingCurvedCompressive (NXOpen.CAE.AeroStructures.Author.AbbContext abbContext, double b, double a, double t, double r, NXOpen.CAE.AeroStructures.Author.ABB.MaterialBehaviour behaviour, double e, double nu, double n, double iFy, double[] sigma, out double[] ms, out double sigmaAllowable) |
| MS Plate Buckling Curved Compressive Computes margin of safety of a curved metallic rectangular panel under compressive load More... | |
| unsafe NXOpen.CAE.AeroStructures.Author.ABB.Status | MsPlateBucklingCurvedLongitudinalShearCombined (NXOpen.CAE.AeroStructures.Author.AbbContext abbContext, double b, double a, NXOpen.CAE.AeroStructures.Author.ABB.EdgeSupportType bc, double t, double r, NXOpen.CAE.AeroStructures.Author.ABB.MaterialBehaviour behaviour, double e, double nu, double n, double iFy, double[] sigma, double[] tau, out double[] ms, out double sigmacr, out double taucr) |
| 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 More... | |
| unsafe NXOpen.CAE.AeroStructures.Author.ABB.Status | MsPlateBucklingCurvedShear (NXOpen.CAE.AeroStructures.Author.AbbContext abbContext, double b, double a, NXOpen.CAE.AeroStructures.Author.ABB.EdgeSupportType bc, double t, double r, NXOpen.CAE.AeroStructures.Author.ABB.MaterialBehaviour behaviour, double e, double nu, double n, double iFy, double[] tau, out double[] ms, out double tauAllowable) |
| MS Plate Buckling Curved Shear Computes margin of safety of a curved metallic rectangular panel under shear load More... | |
| unsafe NXOpen.CAE.AeroStructures.Author.ABB.Status | MsPlateBucklingFlatBending (NXOpen.CAE.AeroStructures.Author.AbbContext abbContext, double b, double a, double t, NXOpen.CAE.AeroStructures.Author.ABB.MaterialBehaviour behaviour, double e, double nu, double n, double iFy, double beta, double[] sigma1, double[] sigma2, out double[] ms, out double[] sigmaAllowable) |
| MS Plate Buckling Flat Bending Computes margin of safety of a flat metallic rectangular panel under bending load More... | |
| unsafe NXOpen.CAE.AeroStructures.Author.ABB.Status | MsPlateBucklingFlatCompressive (NXOpen.CAE.AeroStructures.Author.AbbContext abbContext, double b, NXOpen.CAE.AeroStructures.Author.ABB.EdgeSupportType bcLoaded, double a, NXOpen.CAE.AeroStructures.Author.ABB.UnloadedEdgeSupportType bcUnloaded, double t, NXOpen.CAE.AeroStructures.Author.ABB.MaterialBehaviour behaviour, double e, double nu, double n, double iFy, double[] sigma, out double[] ms, out double sigmaAllowable) |
| MS Plate Buckling Flat Compressive Computes margin of safety of a flat metallic rectangular panel under compressive load More... | |
| unsafe NXOpen.CAE.AeroStructures.Author.ABB.Status | MsPlateBucklingFlatLongitudinalBendingCombined (NXOpen.CAE.AeroStructures.Author.AbbContext abbContext, double b, NXOpen.CAE.AeroStructures.Author.ABB.EdgeSupportType bcLoaded, double a, NXOpen.CAE.AeroStructures.Author.ABB.UnloadedEdgeSupportType bcUnloaded, double t, NXOpen.CAE.AeroStructures.Author.ABB.MaterialBehaviour behaviour, double e, double nu, double n, double iFy, double[] sigma1, double[] sigma2, out double[] ms, out double sigmacr, out double sigmabcr) |
| 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 More... | |
| unsafe NXOpen.CAE.AeroStructures.Author.ABB.Status | MsPlateBucklingFlatLongitudinalShearCombined (NXOpen.CAE.AeroStructures.Author.AbbContext abbContext, double b, NXOpen.CAE.AeroStructures.Author.ABB.EdgeSupportType bcLoaded, double a, NXOpen.CAE.AeroStructures.Author.ABB.UnloadedEdgeSupportType bcUnloaded, double t, NXOpen.CAE.AeroStructures.Author.ABB.MaterialBehaviour behaviour, double e, double nu, double n, double iFy, double[] sigma, double[] tau, out double[] ms, out double sigmacr, out double taucr) |
| 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 More... | |
| unsafe NXOpen.CAE.AeroStructures.Author.ABB.Status | MsPlateBucklingFlatShear (NXOpen.CAE.AeroStructures.Author.AbbContext abbContext, double b, double a, NXOpen.CAE.AeroStructures.Author.ABB.EdgeSupportType bc, double t, NXOpen.CAE.AeroStructures.Author.ABB.MaterialBehaviour behaviour, double e, double nu, double n, double iFy, double[] tau, out double[] ms, out double tauAllowable) |
| MS Plate Buckling Flat Shear Computes margin of safety of a flat metallic rectangular panel under shear load More... | |
| unsafe NXOpen.CAE.AeroStructures.Author.ABB.Status | MsPlateBucklingFlatShearBendingCombined (NXOpen.CAE.AeroStructures.Author.AbbContext abbContext, double b, NXOpen.CAE.AeroStructures.Author.ABB.EdgeSupportType bcLoaded, double a, NXOpen.CAE.AeroStructures.Author.ABB.UnloadedEdgeSupportType bcUnloaded, double t, NXOpen.CAE.AeroStructures.Author.ABB.MaterialBehaviour behaviour, double e, double nu, double n, double iFy, double[] sigma1, double[] sigma2, double[] tau, out double[] ms, out double[] sigmabcr, out double taucr) |
| 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 More... | |
| unsafe NXOpen.CAE.AeroStructures.Author.ABB.Status | MsShearTearOut (NXOpen.CAE.AeroStructures.Author.AbbContext abbContext, double d, double b, double t, double iFs, double f, double[] p, out double[] ms) |
| MS Shear Tear Out Computes margin of shear tear out (due to bolt hole) More... | |
| unsafe NXOpen.CAE.AeroStructures.Author.ABB.Status | MsTrescaPlaneStress (NXOpen.CAE.AeroStructures.Author.AbbContext abbContext, double iSTresca, double[] iFx, double[] iFy, double[] iFxy, out double[] ms) |
| MS Tresca. More... | |
| unsafe NXOpen.CAE.AeroStructures.Author.ABB.Status | MsTsaiHillPlaneStress (NXOpen.CAE.AeroStructures.Author.AbbContext abbContext, double iXt, double iXc, double iYt, double iYc, double s, double[] sigma1, double[] sigma2, double[] tau, out double[] ms) |
| MS Tsai-Hill More... | |
| unsafe NXOpen.CAE.AeroStructures.Author.ABB.Status | SecantModulus (NXOpen.CAE.AeroStructures.Author.AbbContext abbContext, double e, double n, double fy, double sigma, out double iEs) |
| Secant modulus Computes the secant modulus from material properties and stress. More... | |
| unsafe NXOpen.CAE.AeroStructures.Author.ABB.Status | StressF07 (NXOpen.CAE.AeroStructures.Author.AbbContext abbContext, double iFy, double e, double n, out double f07) |
| Stress F0. More... | |
| unsafe NXOpen.CAE.AeroStructures.Author.ABB.Status | StressFromStrainInPlasticDomain (NXOpen.CAE.AeroStructures.Author.AbbContext abbContext, double strain, double e, double iF02ys, double n, out double sigma) |
| Compute stress from strain with the help of Ramberg-Osgood relationship More... | |
| unsafe NXOpen.CAE.AeroStructures.Author.ABB.Status | TangentModulus (NXOpen.CAE.AeroStructures.Author.AbbContext abbContext, double e, double n, double iFy, double sigma, out double oEt) |
| Computes the tangent modulus from material properties and stress. More... | |
 Public Member Functions inherited from NXOpen.Utilities.NXRemotableObject | |
| IMessageCtrl | AsyncProcessMessage (IMessage msg, IMessageSink replySink) |
| Asynchronously processes the given message. More... | |
| IMessage | SyncProcessMessage (IMessage msg) |
| Synchronously processes the given message. More... | |
Static Public Member Functions | |
| static ABB | GetABB (NXOpen.Session owner) |
| Returns the ABB object for the running session which serves as the 'gateway' class for the application API. More... | |
Properties | |
| Tag | Tag [get] |
| Returns the tag of this object. More... | |
| Properties inherited from NXOpen.Utilities.NXRemotableObject | |
| IMessageSink | NextSink [get] |
| Gets the next message sink in the sink chain. More... | |
Additional Inherited Members | |
| Protected Member Functions inherited from NXOpen.Utilities.NXRemotableObject | |
| void | initialize () |
| <exclude> More... | |
Represents a AeroStruct application building block (ABB)
To obtain an instance of this class, refer to NXOpen.Session
Created in NX12.0.0
Plane stress boundary conditions, the choices are: {SSSS, SCSC, CCCC, SFSS}
Support along unloaded edges, the choices are: {Clamped-Clamped, Simply Supported-Clamped, Simply Supported-Simply Supported, Free-Clamped, Free-Simply Supported}
|
inline |
Curves for finding 'kc' the compressive-buckling coefficient for curved sheet panel
This curve is extracted from Bruhn manual, figure C9.1 Used for finding 'kc' the compressive-buckling coefficient for curved sheet panel, with simply-supported edges.
Input b dimension in radial axis t thickness r radius nu Poisson's ratio Output kc compressive-buckling coefficient Returns Status of the calculation
Created in NX12.0.0
License requirements: sc_aero_environment ("Simcenter AeroStructures Environment"), sc_margin_safety ("Simcenter Margin Of Safety")
| abbContext | The ABB context |
| b | Dimension in radial axis |
| t | Panel thickness |
| r | Panel radius |
| nu | Material Poisson's ratio |
| kc | Compressive-buckling coefficient |
|
inline |
Curves for finding 'ks' the shear-buckling coefficient for curved sheet panel
These curves are extracted from Bruhn manual, figures C9.2 to C9.5 Used for finding 'ks' the shear-buckling coefficient for curved sheet panel, with simply-supported or clamped edges.
Input a Dimension in longitudinal axis b Dimension in radial axis t Thickness r Radius nu Poisson's ratio BC Support along the edges, the choice is between SimplySupported and Clamped Output ks Shear-buckling coefficient Returns False if input values are out of bounds
Created in NX12.0.0
License requirements: sc_aero_environment ("Simcenter AeroStructures Environment"), sc_margin_safety ("Simcenter Margin Of Safety")
| abbContext | The ABB context |
| a | Dimension in longitudinal axis |
| b | Dimension in radial axis |
| t | Thickness |
| r | Radius |
| nu | Poisson's ratio |
| bc | Support along the edges |
| ks | Compressive-buckling coefficient |
|
inline |
Compute equivalent section properties (area, center of gravity, Young's modulus and inertia) of a profile composed of different sub-sections.
Input n Number of sub-sections that compose the section Ai Areas of sub-sections Ei Young's modulus of sub-sections Ycogi Center of gravity of sub-sections in Y direction Ixxi Moments of inertia (Quadratic moments) of sub-sections around XX (expressed at the center of gravity of each sub-section) Output A Area of the equivalent section (sum of all sub-sections) E Young's modulus of the equivalent section Ycog Center of gravity of the equivalent section in Y direction Ixx Moment of inertia of the equivalent section around XX (expressed at the center of gravity of the equivalent section)
Created in NX12.0.0
License requirements: sc_aero_environment ("Simcenter AeroStructures Environment"), sc_margin_safety ("Simcenter Margin Of Safety")
| abbContext | The ABB context |
| iAi | Areas of sub-sections |
| iYcog | Center of gravity of sub-sections in Y direction |
| iEi | Young's modulus of sub-sections |
| iIxxi | Moments of inertia (Quadratic moments) of sub-sections around XX (expressed at the center of gravity of each sub-section) |
| a | Area of the equivalent section (sum of all sub-sections) |
| oYcog | Center of gravity of the equivalent section in Y direction |
| e | Young's modulus of the equivalent section |
| oIxx | Moment of inertia of the equivalent section around XX (expressed at the center of gravity of the equivalent section) |
|
inline |
Compute Crippling stress allowable for a given segment
Crippling curves for a sub-section (also called a segment) of extruded metallic profiles.
The computed value is 'Fcc'. 'Fcc' is thresholded by 'Fcy', to avoid plasticity of material. Segment's width ('b') is assumed to be greater than its thickness ('t').
Input Fcy Compressive yield allowable stress E Young's modulus FE Segment's number of free edges b Segment's width t Segment's thickness Output Fcc Equivalent stress allowable Returns Computation status
Created in NX12.0.0
License requirements: sc_aero_environment ("Simcenter AeroStructures Environment"), sc_margin_safety ("Simcenter Margin Of Safety")
| abbContext | The ABB context |
| iFcy | Compressive yield allowable stress |
| e | Young's modulus |
| fe | Segment's number of free edges |
| b | Segment's width |
| t | Segment's thickness |
| iFcc | Equivalent stress allowable |
|
inline |
Curves for finding the bending buckling stress coefficient for thin flat plates
Used for finding 'kb' the bending buckling stress coefficient as a function of: * 'a/b', the panel length ratio * 'a' is the unloaded edge length * 'b' is the loaded edge length * 'beta', is the factor which, divided to b, gives the edge length in compression (while the remaining edge length is in tension).
Input a_over_b Panel length ratio beta Loading length ratio Output kb Bending buckling stress coefficient Returns False if input values are out of bounds
Created in NX12.0.0
License requirements: sc_aero_environment ("Simcenter AeroStructures Environment"), sc_margin_safety ("Simcenter Margin Of Safety")
| abbContext | The ABB context |
| aOverB | Panel length ratio |
| beta | Loading length ratio |
| kb | Bending buckling stress coefficient |
|
inline |
Curves for finding 'kc' the compressive-buckling coefficient for rectangular metallic flat plate
Used for finding 'kc' the compressive-buckling coefficient for rectangular metallic flat plate, as a function of edge lengths and edge boundary conditions
Input a Unloaded edge length b Loaded edge length BC_Unloaded Support along unloaded edges {Clamped-Clamped, Simply Supported-Clamped, Simply Supported-Simply Supported, Free-Clamped, Free-Simply Supported} BC_Loaded Support along loaded edges {Clamped or Simply Supported} Output kc Compressive buckling coefficient Returns Computation status
Created in NX12.0.0
License requirements: sc_aero_environment ("Simcenter AeroStructures Environment"), sc_margin_safety ("Simcenter Margin Of Safety")
| abbContext | The ABB context |
| a | Unloaded edge length |
| b | Loaded edge length |
| bcUnloaded | Support along unloaded edges |
| bcLoaded | Support along loaded edges |
| kc | Compressive buckling coefficient |
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Curves for finding 'ks' the shear-buckling coefficient for flat rectangular plate
These curves are inspired by Bruhn manual. Used for finding 'ks' the shear-buckling coefficient for flat rectangular plate, as a function of edge lengths and boundary conditions
Input a Longer plate dimension b Shorter plate dimension BC Support along the edges {Simply Supported or Clamped} Output ks Shear-buckling coefficient Returns Computation status
Created in NX12.0.0
License requirements: sc_aero_environment ("Simcenter AeroStructures Environment"), sc_margin_safety ("Simcenter Margin Of Safety")
| abbContext | The ABB context |
| a | Longer plate dimension |
| b | Shorter plate dimension |
| bc | Support along the edges |
| ks | Shear-buckling coefficient |
|
inlinestatic |
Returns the ABB object for the running session which serves as the 'gateway' class for the application API.
References to all other objects in this API are obtained either directly or indirectly via methods and properties on this class. Platform Session should be initialized using 'GetSession' method from NXOpen API prior to this call.
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Integer NA value
Created in NX12.0.0
License requirements: sc_aero_environment ("Simcenter AeroStructures Environment"), sc_margin_safety ("Simcenter Margin Of Safety")
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The MS (margin of safety) threshold
Created in NX12.0.0
License requirements: sc_aero_environment ("Simcenter AeroStructures Environment"), sc_margin_safety ("Simcenter Margin Of Safety")
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PI number
Created in NX12.0.0
License requirements: sc_aero_environment ("Simcenter AeroStructures Environment"), sc_margin_safety ("Simcenter Margin Of Safety")
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Real epsilon
Created in NX12.0.0
License requirements: sc_aero_environment ("Simcenter AeroStructures Environment"), sc_margin_safety ("Simcenter Margin Of Safety")
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Maximum real number
Created in NX12.0.0
License requirements: sc_aero_environment ("Simcenter AeroStructures Environment"), sc_margin_safety ("Simcenter Margin Of Safety")
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Real NA
Created in NX12.0.0
License requirements: sc_aero_environment ("Simcenter AeroStructures Environment"), sc_margin_safety ("Simcenter Margin Of Safety")
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The negative infinity value
Created in NX12.0.0
License requirements: sc_aero_environment ("Simcenter AeroStructures Environment"), sc_margin_safety ("Simcenter Margin Of Safety")
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The positive infinity value
Created in NX12.0.0
License requirements: sc_aero_environment ("Simcenter AeroStructures Environment"), sc_margin_safety ("Simcenter Margin Of Safety")
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Ultimate limit factor from the customer default
Created in NX12.0.0
License requirements: sc_aero_environment ("Simcenter AeroStructures Environment"), sc_margin_safety ("Simcenter Margin Of Safety")
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Tests if a value is NA
Created in NX12.0.0
License requirements: sc_aero_environment ("Simcenter AeroStructures Environment"), sc_margin_safety ("Simcenter Margin Of Safety")
| value |
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Tests if a value equals negative infinity
Created in NX12.0.0
License requirements: sc_aero_environment ("Simcenter AeroStructures Environment"), sc_margin_safety ("Simcenter Margin Of Safety")
| value |
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Tests if a value equals positive infinity
Created in NX12.0.0
License requirements: sc_aero_environment ("Simcenter AeroStructures Environment"), sc_margin_safety ("Simcenter Margin Of Safety")
| value |
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Computes bolt loads for multiple bolt fitting - Concentric load
Formula Pn = P * (Psn / SUM(Psn)) where: * 'P' is the load acting on the fitting * 'Psn' is the allowable strength of bolt n * 'Pn' is the shear load on bolt n
Input nblc Number of load cases P Load acting on fitting (nblc) nbbolt Number of bolts Psn Allowable shear strength of bolt (nbbolt) Output Pn Shear load on bolt (nblc x nbbolt) Return Status of the calculation
Created in NX12.0.0
License requirements: sc_aero_environment ("Simcenter AeroStructures Environment"), sc_margin_safety ("Simcenter Margin Of Safety")
| abbContext | The ABB context |
| p | Load acting on fitting (nblc) |
| iPsn | Allowable shear strength of bolt (nbbolt) |
| oPn | Shear load on bolt (nblc x nbbolt) |
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Estimation of shear yield stress (Fsy)
Shear yield stress allowable ('Fsy') is estimated on the basis of the following formula: 'Fsy=( FtyL + FtyLT + FcyL + FcyLT ) / 4 * ( 2 * Fsu)/( FtuL + FtuLT )' where: * 'FtyL' is the tensile yield stress under longitudinal direction * 'FtyLT' is the tensile yield stress under long transverse direction * 'FcyL' is the compressive yield stress under longitudinal direction * 'FcyLT' is the compressive yield stress under long transverse direction * 'Fsu' is the shear ultimate stress * 'FtuL' is the tensile ultimate stress under longitudinal direction * 'FtuLT' is the tensile ultimate stress under long transverse direction
Input FtyL Tensile yield stress, longitudinal direction FtyLT Tensile yield stress, long transverse direction FcyL Compressive yield stress, longitudinal direction FcyLT Compressive yield stress, long transverse direction Fsu Shear ultimate stress FtuL Tensile ultimate stress, longitudinal direction FtuLT Tensile ultimate stress, long transverse direction Output Fsy Shear yield stress Return Status of the calculation
Created in NX12.0.0
License requirements: sc_aero_environment ("Simcenter AeroStructures Environment"), sc_margin_safety ("Simcenter Margin Of Safety")
| abbContext | The ABB context |
| iFtyL | Tensile yield stress, longitudinal direction |
| iFtyLT | Tensile yield stress, long transverse direction |
| iFcyL | Compressive yield stress, longitudinal direction |
| iFcyLT | Compressive yield stress, long transverse direction |
| iFsu | Shear ultimate stress |
| iFtuL | Tensile ultimate stress, longitudinal direction |
| iFtuLT | Tensile ultimate stress, long transverse direction |
| oFsy | Shear yield stress |
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Metallic panel compressive plasticity curve BC1 Curves for finding critical buckling stress / secant yield stress F0.
7
Used for finding 'sigma_cr' the inelastic buckling strength of metallic flat rectangular plate in compression. The Boundary Condition for the unloaded edges is Simply Supported-Free. It computes: * 'sigma_cr /sigma_0.7' as a function of '(kc * pi^2E) / (12 * (1-nu^2) * sigma_0.7)(t/b)^2' and 'n' where * 'sigma_cr' is the critical stress allowable * 'sigma_0.7' is the [stress for secant modulus equal to 70% of Young's modulus] * 'kc' is the buckling coefficient, computed in Figure FlatMetallicPanelCompressiveBucklingCoefficient * 'E' is the Young's modulus * 'nu' is the Poisson's ratio * 't' is the plate thickness * 'b' is the loaded edge length * 'n' is the Ramberg-Osgood parameter
Input X Critical buckling stress (elastic) / secant yield stress F0.7 n Ramberg-Osgood parameter Output Z Critical buckling stress (including plasticity) / secant yield stress F0.7 Returns Status of the computation
Created in NX12.0.0
License requirements: sc_aero_environment ("Simcenter AeroStructures Environment"), sc_margin_safety ("Simcenter Margin Of Safety")
| abbContext | The ABB context |
| x | Critical buckling stress (elastic) / secant yield stress F0.7 |
| n | Ramberg-Osgood parameter |
| z | Critical buckling stress (including plasticity) / secant yield stress F0.7 |
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Metallic panel compressive plasticity curve BC2 Curves for finding critical inter-rivet buckling stress (or critical wrinkling stress) / secant yield stress F0.
7
Used for finding 'Fir' or 'Fw'. It computes either: * 'Fir /F0.7' as a function of '(C * pi^2E)/(12 * (1-nu^2) * F0.7)(ts/p)^2' and 'n' where * 'Fir' is the Inter-Rivet Buckling stress allowable (with plasticity) * 'F0.7' is the [stress for secant modulus equal to 70% of Young's modulus] * 'C' is the end fixity coefficient * 'E' is the Young's modulus * 'nu' is the Poisson's ratio * 'ts' is the thickness of the sheet * 'p' is the rivet spacing * 'n' is the Ramberg-Osgood parameter
Or: * 'Fw /F0.7' as a function of '(kw * pi^2E)/(12 * (1-nu^2) * F0.7)(ts/bs)^2' and 'n' where * 'Fw' is the wrinkling stress allowable * 'kw' is the wrinkling failing stress coefficient * 'ts' is the thickness of the sheet * 'bs' is the stiffener spacing * 'n' is the Ramberg-Osgood parameter
Input X Critical buckling stress (elastic) / secant yield stress F0.7 n Ramberg-Osgood parameter Output Z Critical buckling/wrinkling stress (including plasticity) / secant yield stress F0.7 Returns Status of the computation
Created in NX12.0.0
License requirements: sc_aero_environment ("Simcenter AeroStructures Environment"), sc_margin_safety ("Simcenter Margin Of Safety")
| abbContext | The ABB context |
| x | Critical buckling stress (elastic) / secant yield stress F0.7 |
| n | Ramberg-Osgood parameter |
| z | Critical buckling/wrinkling stress (including plasticity) / secant yield stress F0.7 |
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Metallic panel compressive plasticity curve BC3 Curves for finding critical buckling stress / secant yield stress F0.
7
Used for finding 'sigma_cr' the inelastic buckling strength of metallic cylinder in compression.
It computes: * 'sigma_cr /sigma_0.7' as a function of '(kc * pi^2E)/(12 * (1-nu^2) * sigma_0.7)(t/b)^2' and 'n' where * 'sigma_cr' is the critical stress allowable * 'sigma_0.7' is the [stress for secant modulus equal to 70% of Young's modulus] * 'kc' is the buckling coefficient, computed in Figure FlatMetallicPanelCompressiveBucklingCoefficient * 'E' is the Young's modulus * 'nu' is the Poisson's ratio * 't' is the plate thickness * 'b' is the loaded edge length * 'n' is the Ramberg-Osgood parameter
Input X Critical buckling stress (elastic) / secant yield stress F0.7 n Ramberg-Osgood parameter Output Z Critical buckling stress (including plasticity) / secant yield stress F0.7 Returns Status of the computation
Created in NX12.0.0
License requirements: sc_aero_environment ("Simcenter AeroStructures Environment"), sc_margin_safety ("Simcenter Margin Of Safety")
| abbContext | The ABB context |
| x | Critical buckling stress (elastic) / secant yield stress F0.7 |
| n | Ramberg-Osgood parameter |
| z | Critical buckling stress (including plasticity) / secant yield stress F0.7 |
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MS allowable.
Computes margin of safety based on an allowable
The formula is MS = Allowable / Value - 1
where: * 'Allowable' is the manual input * 'Value' is the value coming from load extractor * 'MS' is the margin of safety
Input Allowable Manual input Value(nblc) Value coming from load extractor Output MS(nblc) Margin of safety Return Status of the calculation
Created in NX12.0.0
License requirements: sc_aero_environment ("Simcenter AeroStructures Environment"), sc_margin_safety ("Simcenter Margin Of Safety")
| abbContext | The ABB context |
| allowable | Manual input |
| value | Value coming from load extractor |
| ms | Margin of safety |
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MS bearing Computes margin of bearing
The formula is 'MS = PBearingAllowable / P - 1'
where * 'PBearingAllowable' is the bearing load allowable ('PBearingAllowable = Fbr * D * t') 'Fbr' is the bearing stress allowable 'D' is the diameter 't' is the thickness * 'P' is the bearing load (P = FactorLoad * PExtracted) 'FactorLoad' is the ratio of load between extracted load 'PExtracted' and 'P' 'PExtracted' is the extracted load ('PExtracted = sqrt( Py ^ 2 + Pz ^ 2 )') 'Py' is the shear load in Y direction 'Pz' is the shear load in Z direction
Input D Diameter t Thickness Fbr Bearing stress allowable f Load factor Py Shear load Y direction Pz Shear load Z direction Output MS Margin of safety Return Status of the calculation
Created in NX12.0.0
License requirements: sc_aero_environment ("Simcenter AeroStructures Environment"), sc_margin_safety ("Simcenter Margin Of Safety")
| abbContext | The ABB context |
| d | Diameter |
| t | Thickness |
| iFbr | Bearing stress allowable |
| f | Load factor |
| p | Shear load |
| ms | Margin of safety |
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MS bolt bending Computes margin of safety of a bolt under bending load
The formula is 'MS = MBendingAllowable / M - 1'
where * 'MBendingAllowable' is the bending moment allowable of the bolt. * 'M' is the bending moment applied to the bolt. ('M = b * P') where: 'b' is the arm 'P' is the load ('P = FactorLoad * PExtracted') 'FactorLoad' is the ratio of load between extracted load 'PExtracted' and 'P' 'PExtracted' is the extracted load ('PExtracted = sqrt(Py^2 + Pz^2)') 'Py' is the shear load in Y direction 'Pz' is the shear load in Z direction
Input b Arm Mba Bending moment allowable of bolt f Load factor P Shear load Output MS Margin of safety Return Status of the calculation
Created in NX12.0.0
License requirements: sc_aero_environment ("Simcenter AeroStructures Environment"), sc_margin_safety ("Simcenter Margin Of Safety")
| abbContext | The ABB context |
| b | Arm |
| iMba | Bending moment allowable of bolt |
| f | Load factor |
| p | Shear load |
| ms | Margin of safety |
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MS bolt combined shear tension Computes margin of safety of a bolt under shear load and tension load
The formula is 'MS = 1 / sqrt( Rt ^ 2 + Rs ^ 3 ) - 1' where * Rt = PTensileX/PTensileAllowable * Rs = PShear/PShearAllowable *'PTensileAllowable' is the tensile load allowable of the bolt * 'PTensileX' is the tensile load applied on the fastener * 'PShearAllowable' is the single shear load allowable of the bolt * 'Pshear' is the shearing load applied through the shear area. PShear = FactorLoad * PExtracted * 'FactorLoad' is the ratio of load between extracted load PExtracted and PShear * 'PExtracted' is the extracted load ('PExtracted = sqrt(Py^2 + Pz^2)') * 'Py' is the shear load in Y direction * 'Pz' is the shear load in Z direction
Input nblc Number of loadcases Ptx Tensile load allowable Pss Single shear load allowable Px(nblc) Tensile load f Load factor P(nblc) Shear load Output MS Margin of safety Return Status of the calculation
Created in NX12.0.0
License requirements: sc_aero_environment ("Simcenter AeroStructures Environment"), sc_margin_safety ("Simcenter Margin Of Safety")
| abbContext | The ABB context |
| iPtx | Tensile load allowable |
| iPss | Single shear load allowable |
| iPx | Tensile load |
| f | Load factor |
| p | Shear load |
| ms | Margin of safety |
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MS bolt combined shear tension bending Computes margin of safety of a bolt under shear, tension and bending load
The formula is MS = 1 / sqrt ( ( Rt + Rb ) ^ 2 + Rs ^ 3 ) - 1 where * Rt = PTensileX / PTensileAllowable * Rb = M / MAllowable * Rs = PShear / PShearAllowable
Tensile data * 'PTensileAllowable' is the tensile load allowable of the bolt * 'PTensileX' is the tensile load applied on the fastener
Bending data * 'MAllowable' is the bending moment allowable of the bolt * 'M' is the bending moment applied to the bolt. M = b * PBend PBend = FactorLoadBend * sqrt(PyBend^2 + PzBend^2) * 'b' is the arm * 'FactorLoadBend' is the load factor for bending * 'PyBend' is the bending load in Y direction * 'PzBend' is the shear load in Z direction
Shear data * 'PShearAllowable' is the single shear load allowable of the bolt * 'PShear' is the shearing load applied through the shear area. PShear = FactorLoadShear * sqrt(PyShear^2 + PzShear^2) * 'FactorLoadShear' is the load factor for shearing * 'PyShear' is the shear load in Y direction * 'PzShear' is the shear load in Z direction
Input nblc Number of loadcases b Arm Mba Bending moment allowable of bolt Ptx Tensile load allowable Pss Single shear load allowable fb Load factor for bending Pb(nblc) Bending load Px(nblc) Tensile load fs Load factor for shear Ps(nblc) Shear load Output MS Margin of safety Return Status of the calculation
Created in NX12.0.0
License requirements: sc_aero_environment ("Simcenter AeroStructures Environment"), sc_margin_safety ("Simcenter Margin Of Safety")
| abbContext | The ABB context |
| b | Arm |
| iMba | Bending moment allowable of bolt |
| iPtx | Tensile load allowable |
| iPss | Single shear load allowable |
| fb | Bending load factor |
| iPb | Bending load |
| iPx | Tensile load |
| fs | Shear load factor |
| iPs | Shear load |
| ms | Margin of safety |
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MS bolt shear Computes margin of safety of a bolt under shear load
The formula is MS = PShearAllowable / P - 1 where * 'PShearAllowable' is the single shear load allowable of the bolt * 'P' is the shearing load applied through the shear area. P = FactorLoad * PExtracted * 'FactorLoad' is the ratio of load between extracted load 'PExtracted' and 'P' * 'PExtracted' is the extracted load ('PExtracted = sqrt(Py^2 + Pz^2)') * 'Py' is the shear load in Y direction * 'Pz' is the shear load in Z direction
Input NbLC Number of loadcases Pss Single shear load allowable f Load factor P(NbLC) Shear load Output MS Margin of safety Return Status of the calculation
Created in NX12.0.0
License requirements: sc_aero_environment ("Simcenter AeroStructures Environment"), sc_margin_safety ("Simcenter Margin Of Safety")
| abbContext | The ABB context |
| iPss | Single shear load allowable |
| f | Shear load factor |
| p | Shear load |
| ms | Margin of safety |
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MS Column Eccentric Load
Computes margin of safety of column under eccentric axial compressive load (secant formula theory)
When the axial compressive load is not applied on the centroid of the column cross section eccentricity has to be taken into account.
MS = Pcr / (abs(P)) - 1
where: * Pcr is the compressive load allowable * P is the axial compressive load (MS is not calculated in case of tensile stress)
Pcr = (sigmacr*A)/(1 + (ecc*c)/rho^2 sec (1/2 sqrt(Pcr)/(EA)(L')/rho))
where: * sigmacr is the material stress allowable * A the area of the cross section * I is the bending inertia of the column * ecc the eccentricity of the load (distance between the line of action of P and the axis of the column) * c the distance of extreme fiber to neutral axis * rho is the radius of gyration of cross-section given by rho=sqrt(I/A) * E the material Young modulus * L' is the column effective length given by L'=L/sqrt(C) * L the column length * C the end fixity coefficient depending on the Boundary Condition given at both extremities. Please find some values: * Pinned-Pinned: C=1 * Fixed-Fixed: C=4 * Fixed-Pinned: C=2.05 * Fixed-Free: C=0.25
Remark: Pcr is declared in each side of the formula. As consequence an iterative process is used to evaluate it.
Input A Area of the cross section L Column length E Young's modulus I Bending inertia of the column sigmacr Material stress allowable C End fixity coefficient depending on the Boundary Condition given at both extremities ecc Eccentricity of the load nblc Number of load cases sigma Stress Output iPcr Compressive load allowable MS Margin of safety Return Status of the calculation
Created in NX12.0.0
License requirements: sc_aero_environment ("Simcenter AeroStructures Environment"), sc_margin_safety ("Simcenter Margin Of Safety")
| abbContext | The ABB context |
| a | Area of the cross section |
| l | Column length |
| e | Young's modulus |
| i | Bending inertia of the column |
| sigmacr | Material stress allowable |
| c | End fixity coefficient depending on the Boundary Condition given at both extremities |
| ecc | Eccentricity of the load |
| extrmfbrdist | Distance from neutral axis to extreme fiber |
| sigma | Applied stress |
| iPcr | Compressive load allowable |
| ms | Margin of safety |
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MS Engesser
Computes margin of safety on the basis of Engesser column buckling theory (also called tangent-modulus theory)
MS = sigmacr / (abs(sigma)) - 1
where: * sigmacr is the Engesser buckling stress allowable * sigma is the axial compressive stress (MS is not calculated in case of tensile stress)
sigmacr = (pi^2 Et)/((L') /rho)^2
where: * Et is the tangent Young modulus of the column material given by Et=sigma/((sigma/E)+0.002*n*(sigma/fy)^n)) with * sigma is the stress * fy is the yield stress * E is the Young's modulus * n is the Ramberg-Osgood parameter * L' is the column effective length given by L'=L/sqrt(C) with * L the column length * C the end fixity coefficient depending on the Boundary Condition given at both extremities. Please find some values: * Pinned-Pinned: C=1 * Fixed-Fixed: C=4 * Fixed-Pinned: C=2.05 * Fixed-Free: C=0.25 * rho is the radius of gyration of cross-section given by rho=sqrt(I/A) with * I is the bending inertia of the column * A is the column cross section area
Input A Area of the cross section L Column length E Young's modulus I Bending inertia of the column n Ramberg-Ossgood coefficient iFy Yield stress allowable C End fixity coefficient depending on the Boundary Condition given at both extremities nblc Number of load cases sigma Stress Output sigmacr Engesser buckling stress allowable MS Margin of safety Return Status of the calculation
Created in NX12.0.0
License requirements: nx_masterfem ("Finite Element Modeling"), sc_aero_environment ("Simcenter AeroStructures Environment")
| abbContext | The ABB context |
| a | Area of the cross section |
| l | Column length |
| e | Young's modulus |
| i | Bending inertia of the column |
| n | Ramberg-Ossgood coefficient |
| iFy | Yield stress allowable |
| c | End fixity coefficient depending on the Boundary Condition given at both extremities |
| sigma | Stress |
| sigmacr | Engesser buckling stress allowable |
| ms | Margin of safety |
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MS Euler
Computes margin of safety on the basis of Euler column buckling theory
MS = sigmacr / (abs(sigma)) - 1
where: * sigmacr is the Euler buckling stress allowable * sigma is the axial compressive stress (MS is not calculated in case of tensile stress)
sigmacr = (pi^2 E)/((L') /rho)^2
where: * E is the Young modulus of the column material * L' is the column effective length given by L'=L/sqrt(C) with * L the column length * C the end fixity coefficient depending on the Boundary Condition given at both extremities. Please find some values: * Pinned-Pinned: C=1 * Fixed-Fixed: C=4 * Fixed-Pinned: C=2.05 * Fixed-Free: C=0.25 * rho is the radius of gyration of cross-section given by rho=sqrt(I/A) with * I is the bending inertia of the column * A is the column cross section area
Input A Area of the cross section L Column length E Young's modulus I Bending inertia of the column C End fixity coefficient depending on the Boundary Condition given at both extremities nblc Number of load cases sigma Axial compressive stress Output sigmacr Euler buckling stress allowable MS Margin of safety Return Status of the calculation
Created in NX12.0.0
License requirements: sc_aero_environment ("Simcenter AeroStructures Environment"), sc_margin_safety ("Simcenter Margin Of Safety")
| abbContext | The ABB context |
| a | Area of the cross section |
| l | Column length |
| e | Young's modulus |
| i | Bending inertia of the column |
| c | End fixity coefficient depending on the Boundary Condition given at both extremities |
| sigma | Axial compressive stress |
| sigmacr | Euler buckling stress allowable |
| ms | Margin of safety |
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MS Column Johnson-Euler
Computes margin of safety on the basis of Johnson-Euler column theory
MS = sigmacr / (abs(sigma)) - 1
where: * sigmacr is the Johnson-Euler stress allowable * sigma is the axial compressive stress (MS is not calculated in case of tensile stress)
To find the column failing stress under axial compressive load (sigmacr)) Euler or Johnson-Euler equations are used (choice is done depending L'/rho): * The Euler equation is sigmacr = (pi^2E)/(L'/rho)^2 (use in case L'/rho greater than sigma0/2) * The Johnson-Euler equation is sigmacr = sigma0-sigma0^2/(4*pi^2*E)(L'/rho)^2 (use in case L'/rho smaller than sigma0/2) where: * sigma0 is the column stress allowable for a column slenderness equals to 0. It is the minimal value between crippling stress and yield allowable in compression of column. * E is the Young modulus of the column material * L' is the column effective length given by L'=L/sqrt(C) * L the column length * C the end fixity coefficient depending on the Boundary Condition (BC) given at both extremities. Please find some values: * Pinned-Pinned: C=1 * Fixed-Fixed: C=4 * Fixed-Pinned: C=2.05 * Fixed-Free: C=0.25 * rho is the radius of gyration of cross-section given by rho=sqrt(I/A) * I is the bending inertia of the column * A is the column cross section area
Input A Column cross section area L Column length I Bending inertia of the column E Young's modulus C End fixity coefficient depending on the Boundary Condition given at both extremities sigma0 Column stress allowable for a column slenderness equals to 0 nblc Number of load cases sigma Axial compressive stress Output sigmacr Johnson-Euler Stress Allowable MS Margin of safety Return Status of the calculation
Created in NX12.0.0
License requirements: sc_aero_environment ("Simcenter AeroStructures Environment"), sc_margin_safety ("Simcenter Margin Of Safety")
| abbContext | The ABB context |
| a | Column cross section area |
| l | Column length |
| i | Bending inertia of the column |
| e | Young's modulus |
| c | End fixity coefficient depending on the Boundary Condition given at both extremities |
| sigma0 | Column stress allowable for a column slenderness equals to 0 |
| sigma | Axial compressive stress |
| sigmacr | Johnson-Euler Stress Allowable |
| ms | Margin of safety |
|
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MS Torsional Buckling
Computes margin of safety of torsional buckling of a column
MS = iPcr / (abs(load)) - 1
where: * iPcr is the torsional buckling load allowable * load is the axial compressive load (MS is not calculated in case of tensile load)
Hypotheses: Column cross section has two axes of symetry or is point symmetric and the shear center and centroid is coinciding.
iPcr = 1/r0^2(G*J+(E*gamma*pi^2)/(L')^2)
where: * E is the Young modulus of the column material * G is the shear modulus of elasticity * L' is the column effective length L'=L/sqrt(C) with: * L the column length * C the end fixity coefficient depending on the Boundary Condition given at both extremities. * r0 is the polar radius of gyration of the section about its shear center * J is the torsion constant of the section * gamma is the warping constant of the section
Input L Column effective length E Young's modulus G Shear modulus of elasticity J Torsion constant of the section gamma Warping constant of the section r0 Polar radius of gyration of the section about its shear center C End fixity coefficient depending on the Boundary Condition given at both extremities nblc Number of load cases load Axial compressive load Output iPcr Torsional buckling load allowable MS Margin of safety Return Status of the calculation
Created in NX12.0.0
License requirements: sc_aero_environment ("Simcenter AeroStructures Environment"), sc_margin_safety ("Simcenter Margin Of Safety")
| abbContext | The ABB context |
| l | Column effective length |
| e | Young's modulus |
| g | Shear modulus of elasticity |
| j | Torsion constant of the section |
| gamma | Warping constant of the section |
| r0 | Polar radius of gyration of the section about its shear center |
| c | End fixity coefficient depending on the Boundary Condition given at both extremities |
| load | Axial compressive load |
| iPcr | Torsional buckling load allowable |
| ms | Margin of safety |
|
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Computes margin of safety of a rectangular flat composite panel in buckling under compressive loads.
sigma_allowable is the allowable compressive stress computed as: 'sigma_allowable = N_xcr/t' where: * 'N_xcr' is the allowable compressive load in longitudinal direction and * 't' is the total thickness of the laminate
A margin of safety can be derived from this formulation: 'MS=sigma_allowable/(abs(sigma))-1 (Compression; sigma less than 0)' 'MS=NaN (Tension; sigma greater or equal than 0)' Where: * 'sigma' is the measured compressive stress
the allowable compressive load depends on the boundary conditions: * SSSS (loaded edges: simply supported, unloaded edges: simply supported - simply supported) N_xcr = pi^2*(D_11*m^4 + 2*(D_12+2*D_66)*m^2*AR^2 + D_22*AR^4)/(a^2*m^2)
* CSCS (loaded edges: clamped, unloaded edges: simply supported - simply supported) 'N_xcr = pi^2/b^2 * sqrt(D_11*D22)*K_min' 'K(m) = 4/lambda^2 + 2*(D_12+2*D_66)/sqrt(D_11*D_22) + 3/4*lambda^2, for lambda between 0 and 1.662' 'K(m) = (m^4+8*m^2+1)/(lambda^2*(m^2+1)) + 2*(D_12+2*D_66)/sqrt(D_11*D_22) + lambda^2/(m^2+1), for lambda larger than 1.662'
* SCSC (loaded edges: simply supported, unloaded edges: clamped - clamped) 'N_xcr = pi^2/b^2*sqrt(D_11*D_22)*K_min' 'K = m^2/lambda^2 + 2*(D_12+2*D_66)/sqrt(D_11*D_22) + 16/3*lambda^2/m^2'
* CCCC (loaded edges: clamped, unloaded edges: clamped - clamped) 'N_xcr = pi^2/b^2*sqrt(D_11*D22)*K_min' 'K(m) = 4/lambda^2 + (8*(D_12+2*D_66))/(3*sqrt(D_11*D_22 )) + 4*lambda^2, for lambda between 0 and 1.094' 'K(m) = (m^4+8*m^2+1)/(lambda^2*(m^2+1)) + (2*(D_12+2*D_66))/sqrt(D_11*D_22) + lambda^2/(m^2+1), for lambda larger than 1.094'
* SFSS (loaded edges: simply supported, unloaded edges: free - simply supported) 'N_xcr = pi^2/b^2*sqrt(D_11*D22)*K_min' 'K(m) = 12/pi^2*D_66/sqrt(D_11*D22) + 1/lambda^2'
Where: * 'a' is the unloaded edge length * 'b' is the loaded edge length * 'AR =a/b' is the length to width ratio * 'D_ij' are the equivalent flexural stiffenesses of the laminate * 'lambda' is obtained from 'lambda = AR*(D_22/D_11)^(1/4)' * 'K = K(m) is the buckling coefficient * 'm' is the longitudinal half-waves number (buckling mode) * 'Kmin' is the minimum value of K(m) for m integer.
Input b Loaded edge length a Unloaded edge length bc Edges boundary conditions {SSSS; CSCS; SCSC; CCCC; SFSS} laminate Laminate sigma Compressive Stress Output MS Margin of safety sigmaAllowable Allowable compressive stress indexed by failure mode Return Status of the calculation
Created in NX1847.0.0
License requirements: sc_aero_environment ("Simcenter AeroStructures Environment"), sc_margin_safety ("Simcenter Margin Of Safety")
| abbContext | The ABB context |
| b | Loaded edge length |
| a | Unloaded edge length |
| bc | Edges Boundary Conditions |
| laminate | Laminate |
| sigma | Compressive stresses |
| ms | Margin of safety |
| sigmaAllowable | Compressive stress allowable |
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Computes margin of safety of a rectangular flat composite panel in buckling under combined shear and longitudinal loads.
Under longitudinal and shear loads, the interaction equation is: 'R_L + R_S^(1.9+0.1*beta) = 1'
Where: * 'R_L = sigma/sigma_cr' is the stress ratio due to longitudinal stress * 'sigma' is the given longitudinal stress * 'sigma_cr' is the compression stress allowable for buckling, as computed by method MS_Composite_PlateBuckling_FlatCompressive * 'R_S = tau/tau_cr' is the critical ratio of buckling coefficients due to shear stress * 'tau' the given shear stress * 'tau_cr' the shear stress allowable for buckling as computed by method MS_Composite_PlateBuckling_FlatShear * 'beta = (D_12+2*D_66)/sqrt(D_11*D_22)' is a non-dimensional orthotropic material parameter defined by the interaction equation * 'D_ij' are the equivalent flexural stiffenesses of the laminate
The following boundary conditions are supported: * SSSS (loaded edges: simply supported, unloaded edges: simply supported - simply supported) * CSCS (loaded edges: clamped, unloaded edges: simply supported - simply supported) * CCCC (loaded edges: clamped, unloaded edges: clamped - clamped)
Input b Loaded edge length a Unloaded edge length bc Edges boundary conditions {SSSS; CSCS; CCCC} laminate Laminate sigma Compressive Stress tau Shear Stress Output sigmaAllowable Allowable compressive stress tauAllowable Allowable shear stress MS Margin of safety Return Status of the calculation
Created in NX1847.0.0
License requirements: sc_aero_environment ("Simcenter AeroStructures Environment"), sc_margin_safety ("Simcenter Margin Of Safety")
| abbContext | The ABB context |
| b | Loaded edge length |
| a | Unloaded edge length |
| bc | Edges Boundary Conditions |
| laminate | Laminate |
| sigma | Compressive stresses |
| tau | Shear stresses |
| ms | Margin of safety |
| sigmaAllowable | Compressive stress allowable |
| tauAllowable | Shear stress allowable |
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Computes margin of safety of a rectangular flat composite panel in buckling under shear loads.
The MS is calculated by the formula: 'MS = sigma_Allowable/(abs(tau)) - 1'
Where: * 'tau_allowable=N_xycr/t' is the allowable shear stress * 'tau' is the shear stress * 'N_xycr = (k_s*pi^2)/b^2*(D_11*D_22^3)^(1/4)' is the allowable shear load * 't' is the total thickness of the laminate * 'a' is the longer edge length * 'b' is the shorter edge length * 'D_ij' are the equivalent flexural stiffenesses of the laminate * 'theta=sqrt(D_11*D_22)/(D_12+2*D_66)' * 'B = b/a*(D_11/D_22)^(1/4)'
The shear buckling coefficient k_s is expressed in terms of two non-dimensional parameters theta and B as a function of the aspect ratio and the orthotropic bending stiffnesses. The value depends on the boundary conditions:
* SSSS (loaded edges: simply supported, unloaded edges: simply supported - simply supported) 'k_s = 3.32 + 2.17/theta - 0.163/theta^2 + B^2*(1.54+2.36/theta+0.1/theta^2)'
* CSCS (loaded edges: clamped, unloaded edges: simply supported - simply supported) 'k_s(theta,B)' is interpolated from a 2D table of values
* CCCC (loaded edges: clamped, unloaded edges: clamped - clamped) 'k_s(theta,B)' is interpolated from a 2D table of values
Input b Shorter edge length a Longer edge length bc Edges boundary conditions {SSSS; CSCS; CCCC} laminate Laminate sigma Compressive Stress Output MS Margin of safety tauAllowable Allowable shear stress indexed by failure mode Return Status of the calculation
Created in NX1847.0.0
License requirements: sc_aero_environment ("Simcenter AeroStructures Environment"), sc_margin_safety ("Simcenter Margin Of Safety")
| abbContext | The ABB context |
| b | Shorter edge length |
| a | Longer edge length |
| bc | Edges Boundary Conditions |
| laminate | Laminate |
| tau | Shear stresses |
| ms | Margin of safety |
| tauAllowable | Shear stress allowable |
|
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MS Inter-rivet buckling (Column)
Computes margin of safety of inter-rivet buckling (theory coming from Euler column theory)
MS = sigmacr / (abs(sigma)) - 1
where: * sigmacr is the inter-rivet buckling stress allowable * sigma is the axial compressive stress (MS is not calculated in case of tensile stress)
Inter-rivet buckling stress allowable (sigmacr) assumes that sheet between adjacent rivets acts as a **column**.
The formula (derived from Euler theory) is: * sigmacr=(Pi^2E)/(p/sqrt(C)/0.29t)^2 if material is considered as elastic (Material behaviour = Elastic) * sigmacr=(Pi^2Et)/(p/sqrt(C)/0.29t)^2 if material is considered as elastic-plastic (Material behaviour = Elastic-Plastic). This formulation is a derivation of tangent modulus therory (Engesser).
where: * Et is the tangent modulus given by Et=sigma/((sigma/E)+0.002*n*(sigma/fy)^n)) with * sigma is the stress * fy is the yield stress * E is the Young's modulus * n is the Ramberg-Osgood parameter * E is the Young's modulus * p is the the rivet spacing * t is the thickness of sheet * C is the end fixity coefficient * Universal head (or flat head) - C = 4 * Brazier head - C = 3 * Countersunk rivet - C = 1 * Spotwelds - C = 3.5
Input t Sheet thickness p Rivet spacing behaviour Material behaviour E Young's Modulus iFy Compressive yield stress n Ramberg-Osgood coefficient C End fixity coefficient nblc Number of load cases sigma Stress Output MS Margin of safety Return Status of the calculation
Created in NX12.0.1
License requirements: nx_masterfem ("Finite Element Modeling")
| abbContext | The ABB context |
| t | Sheet thickness |
| p | Rivet spacing |
| behaviour | Material behaviour |
| e | Young's Modulus |
| iFy | Compressive yield stress |
| n | Ramberg-Osgood coefficient |
| c | End fixity coefficient |
| sigma | Stress |
| ms | Margin of safety |
|
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MS Inter-rivet buckling (wide column)
Computes margin of safety of inter-rivet buckling (theory based on plate buckling - wide column assumption)
MS = sigmacr / abs(sigma) - 1
where:
* sigmacr is the inter-rivet buckling stress allowable * sigma is the axial compressive stress (MS is not calculated in case of tensile stress)
Inter-rivet buckling stress allowable (sigmacr) assumes that the sheet acts as a **wide column** at its ends and whose length is equal to the rivet spacing.
The formula (derived from buckling plate theory) is: sigmacr=(C pi^2eta E)/(12 (1-nu^2))(t/p)^2
where: * E is the young's modulus * eta is the clad correction factor (supposed to be equal to 1) * nu is the Poisson coefficient * t is the thickness of the sheet * p is the the rivet spacing * C is the end fixity coefficient * Universal head (or flat head) - `C` = 4 * Brazier head - `C` = 3 * Countersunk rivet - `C` = 1 * Spotwelds - `C` = 3.5 * eta is the plasticity reduction factor: sigmacr(Plastic)=eta.sigmacr(Elastic) * eta = 1 if material is considered as elastic (Material behaviour = Elastic) * eta is obtain from following charts sigmacr(Plastic))/sigma(0.7)=f(sigmacr(Elastic)/sigma(0.7)) if material is considered as elastic-plastic (Material behaviour = Elastic-Plastic): with: sigma(0.7) is the stress for secant modulus equal to 70% of Young modulus
Input t Sheet thickness p Rivet pitch behaviour Material behaviour E Young's Modulus nu Elastic Poisson's ratio n Ramberg-Osgood coefficient iFy Yield Stress Allowable C End fixity coefficient nblc Number of load cases sigma Stress Output MS Margin of safety Return Status of the calculation
Created in NX12.0.1
License requirements: nx_masterfem ("Finite Element Modeling")
| abbContext | The ABB context |
| t | Sheet thickness |
| p | Rivet pitch |
| behaviour | Material behaviour |
| e | Young's Modulus |
| nu | Elastic Poisson's ratio |
| n | Ramberg-Osgood coefficient |
| iFy | Yield stress Allowable |
| c | End fixity coefficient |
| sigma | Stress |
| ms | Margin of safety |
|
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MS Net section Computes margin of net section (due to bolt hole)
The formula is MS = PNetSectionAllowable / P - 1
where: * 'PNetSectionAllowable' is the net section load allowable. PNetSectionAllowable = SigmaAllowable * t * ( b - D ) * 'SigmaAllowable' is the material stress allowable. For instance, it could be Ftu * 'D' is the hole diameter * 't' is the thickness * 'b' is the width of the net section
* 'P' is the load. P = FactorLoad * PExtracted * 'FactorLoad' is the ratio of load between extracted load 'PExtracted' and 'P' * 'PExtracted' is the extracted load
* 'MS' is the margin of safety
Input D Diameter b Width t Thickness Fx Material stress allowable f Load factor P(nblc) Axial load Output MS Margin of safety Return Status of the calculation
Created in NX12.0.0
License requirements: sc_aero_environment ("Simcenter AeroStructures Environment"), sc_margin_safety ("Simcenter Margin Of Safety")
| abbContext | The ABB context |
| d | Diameter |
| b | Width |
| t | Thickness |
| iFx | Material stress allowable |
| f | Load factor |
| p | Axial load |
| ms | Margin of safety |
|
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MS Plate Buckling Computes margin of safety of a metallic plate under buckling load (generic formula)
The formula is MS = Allowable / Stress - 1
where: * 'Allowable' is the compressive buckling stress allowable * 'Stress' is the stress * 'MS' is the margin of safety
Allowable = eta * PI^2*k*E/(12*(1-nu^2)) * (t/b)^2 where * 'k' is the buckling coefficient * 'E' is the Young's modulus * 'nu' is the elastic Poisson's ratio * 't' is the panel thickness * 'b' is the panel dimension * 'eta' is the plasticity reduction factor: SigmaAllowablePlastic = eta*SigmaAllowableElastic
Input b Panel's dimension t Panel's thickness E Young's modulus nu Elastic Poisson's ratio eta Plasticity reduction factor k Buckling coefficient nblc Number of load cases sigma Compressive stress Output MS Margin of safety Return Status of the calculation
Created in NX12.0.0
License requirements: sc_aero_environment ("Simcenter AeroStructures Environment"), sc_margin_safety ("Simcenter Margin Of Safety")
| abbContext | The ABB context |
| b | Panel dimension |
| t | Panel thickness |
| e | Young's modulus |
| nu | Elastic Poisson's ratio |
| eta | Plasticity reduction factor |
| k | Buckling coefficient |
| sigma | Compressive stress |
| ms | Margin of safety |
|
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MS Plate Buckling Curved Compressive Computes margin of safety of a curved metallic rectangular panel under compressive load
The formula is MS = Allowable / |Stress| - 1
where: * 'Allowable' is the compressive buckling stress allowable * 'Stress' is the compressive stress (MS is not calculated in case of tensile stress), * 'MS' is the margin of safety
Allowable = eta * PI^2*kc*E/(12*(1-nu^2)) * (t/c)^2 where * 'kc' is the buckling coefficient * 'E' is the Young's modulus * 'nu' is the elastic Poisson's ratio * 't' is the panel thickness * 'c' is the shorter panel dimension c = min(a,b) * 'eta' is the plasticity reduction factor: SigmaAllowablePlastic = eta*SigmaAllowableElastic * eta = 1 if material is considered as elastic (Material behaviour = Elastic) * eta is obtain from following charts if material is considered as elastic-plastic (Material behaviour = Elastic-Plastic):
SigmaAllowablePlastic/F0.7 = f(SigmaAllowableElastic/F0.7)
MetallicPanelCompressivePlasticityCurveBC3 with F0.7 is the stress for secant modulus equal to 70% of Young's modulus
Input b Loaded edge length a Unloaded edge length t Panel thickness r Panel radius of curvature behaviour Material behaviour E Young's modulus nu Elastic Poisson's ratio n Ramberg-Osgood parameter iFy Yield stress Allowable nblc Number of load cases sigma Compressive stress Output sigmaAllowable Stress allowable MS Margin of safety Return Status of the calculation
Created in NX12.0.0
License requirements: sc_aero_environment ("Simcenter AeroStructures Environment"), sc_margin_safety ("Simcenter Margin Of Safety")
| abbContext | The ABB context |
| b | Loaded edge length |
| a | Unloaded edge length |
| t | Panel's thickness |
| r | Panel's curvature radius |
| behaviour | Material behaviour |
| e | Young's modulus |
| nu | Elastic Poisson's ratio |
| n | Ramberg-Osgood parameter |
| iFy | Yield stress Allowable |
| sigma | Compressive stress |
| ms | Margin of safety |
| sigmaAllowable | Stress allowable |
|
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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. Plasticity is not taken into account.
Input b Loaded edge length a Unloaded edge length BC Support along edges ('Clamped' or 'Simply Supported') t Panel thickness r Panel radius of curvature behaviour Material behaviour ('Elastic' or 'Elastic-Plastic') E Young's modulus nu Elastic Poisson's ratio n Ramberg-Osgood parameter iFy Yield Stress Allowable nblc Number of load cases sigma Compressive stress tau Shear stress Output MS Margin of safety sigmacr Compressive stress allowable taucr Shear stress allowable
Return Status of the calculation
Created in NX12.0.0
License requirements: sc_aero_environment ("Simcenter AeroStructures Environment"), sc_margin_safety ("Simcenter Margin Of Safety")
| abbContext | The ABB context |
| b | Loaded edge length |
| a | Unloaded edge length |
| bc | Support along the edges |
| t | Panel thickness |
| r | Panel's curvature radius |
| behaviour | Material behaviour |
| e | Young's modulus |
| nu | Elastic Poisson's ratio |
| n | Ramberg-Osgood parameter |
| iFy | Yield stress Allowable |
| sigma | Compressive stress |
| tau | Shear stress |
| ms | Margin of safety |
| sigmacr | Compressive stress allowable |
| taucr | Shear stress allowable |
|
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MS Plate Buckling Curved Shear Computes margin of safety of a curved metallic rectangular panel under shear load
The formula is MS = Allowable / |Stress| - 1
where: * 'Allowable' is the compressive buckling stress allowable * 'Stress' is the compressive stress (MS is not calculated in case of tensile stress), * 'MS' is the margin of safety
Allowable = eta * PI^2*ks*E/(12*(1-nu^2)) * (t/c)^2 where * 'ks' is the buckling coefficient * 'E' is the Young's modulus * 'nu' is the elastic Poisson's ratio * 't' is the panel thickness * 'c' is the shorter panel dimension c = min(a,b) * 'eta' is the plasticity reduction factor: TauAllowablePlastic = eta*TauAllowableElastic * eta = 1 if material is considered as elastic (Material behaviour = Elastic) * eta is obtained from the MetallicPanelCompressivePlasticityCurveBC1 charts if material is considered as elastic-plastic (Material behaviour = Elastic-Plastic): * TauAllowablePlastic/F0.7 = f(TauAllowableElastic/F0.7) * F0.7 is the stress for secant modulus equal to 70% of Young's modulus
Input b Shorter edge length a Longer edge length BC Support along edges t Panel thickness r Panel radius of curvature behaviour Material behaviour E Young's modulus nu Elastic Poisson's ratio n Ramberg-Osgood parameter iFy Yield Stress Allowable nblc Number of load cases tau Shear stress Output tauAllowable Stress allowable MS Margin of safety Return Status of the calculation
Created in NX12.0.0
License requirements: sc_aero_environment ("Simcenter AeroStructures Environment"), sc_margin_safety ("Simcenter Margin Of Safety")
| abbContext | The ABB context |
| b | Shorter edge length |
| a | Longer edge length |
| bc | Support along the edges |
| t | Panel's thickness |
| r | Panel's curvature radius |
| behaviour | Material behaviour |
| e | Young's modulus |
| nu | Elastic Poisson's ratio |
| n | Ramberg-Osgood parameter |
| iFy | Yield stress Allowable |
| tau | Shear stress |
| ms | Margin of safety |
| tauAllowable | Stress allowable |
|
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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's ratio * '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). * 'beta' is calculated on the basis of sigma1 and sigma2 with an hypothesis of linear behaviour with the formula: * beta = (fc - ft) / fc where fc = min(sigma1, sigma2) and ft = max(sigma1, sigma2) ) * 'eta' is the plasticity reduction factor: SigmaAllowablePlastic = eta*SigmaAllowableElastic * eta = 1 if material is considered as elastic (Material behaviour = Elastic) * eta is obtain from following charts if material is considered as elastic-plastic (Material behaviour = Elastic-Plastic):
SigmaAllowablePlastic/F0.7 = f(SigmaAllowableElastic/F0.7)
MetallicPanelCompressivePlasticityCurveBC2 with F0.7 is the stress for secant modulus equal to 70% of Young's modulus Input b Loaded edge length a Unloaded edge length t Panel thickness behaviour Material behaviour E Young's modulus nu Elastic Poisson's ratio n Ramberg-Osgood parameter iFy Yield Stress Allowable beta Loading length ratio. If not specified (beta = NA), beta is computed nblc Number of load cases sigma1 Compressive stress, side 1 sigma2 Compressive stress, side 2 Output MS Margin of safety sigmaAllowable Stress allowable Return Status of the calculation
Created in NX12.0.0
License requirements: sc_aero_environment ("Simcenter AeroStructures Environment"), sc_margin_safety ("Simcenter Margin Of Safety")
| abbContext | The ABB context |
| b | Loaded edge length |
| a | Unloaded edge length |
| t | Panel thickness |
| behaviour | Material behaviour |
| e | Young's modulus |
| nu | Elastic Poisson's ratio |
| n | Ramberg-Osgood parameter |
| iFy | Yield stress Allowable |
| beta | Loading length ratio |
| sigma1 | Compressive stress, side 1 |
| sigma2 | Compressive stress, side 2 |
| ms | Margin of safety |
| sigmaAllowable | Stress allowables |
|
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MS Plate Buckling Flat Compressive Computes margin of safety of a flat metallic rectangular panel under compressive load
The formula is MS = sigmaAllowable / abs(sigma) - 1
where: * 'sigmaAllowable' is the compressive buckling stress allowable, * 'sigma' is the compressive stress (MS is not calculated in case of tensile stress), * 'MS' is the margin of safety
Allowable = eta * PI^2*kc*E/(12*(1-nu^2)) * (t/b)^2 where * 'kc' is the bending buckling stress coefficient * 'E' is the Young's modulus * 'nu' is the elastic Poisson's ratio * 't' is the panel thickness * 'a' is the unloaded edge length * 'b' is the loaded edge length * 'eta' is the plasticity reduction factor: SigmaAllowablePlastic = eta*SigmaAllowableElastic * eta = 1 if material is considered as elastic (Material behaviour = Elastic) * eta is obtain from following charts if material is considered as elastic-plastic (Material behaviour = Elastic-Plastic):
SigmaAllowablePlastic/F0.7 = f(SigmaAllowableElastic/F0.7) MetallicPanelCompressivePlasticityCurveBC1 if the Boundary Condition for the unloaded edges is Simply Supported-Free, MetallicPanelCompressivePlasticityCurveBC2 if the boundary condition for the unloaded edges is different of Simply Supported-Free
Input b Loaded edge length BC_Loaded Support along loaded edges {'Clamped';'Simply Supported'} a Unloaded edge length BC_Unloaded Support along unloaded edges {'Clamped-Clamped';'Simply Supported-Clamped';'Simply Supported-Simply Supported';'Free-Clamped';'Free-Simply Supported'} t Panel thickness behaviour Material behaviour E Young's modulus nu Elastic Poisson's ratio n Ramberg-Osgood parameter iFy Yield Stress Allowable nblc Number of load cases sigma Compressive stress Output sigmaAllowable Stress allowable MS Margin of safety Return Status of the calculation
Created in NX12.0.0
License requirements: sc_aero_environment ("Simcenter AeroStructures Environment"), sc_margin_safety ("Simcenter Margin Of Safety")
| abbContext | The ABB context |
| b | Loaded edge length |
| bcLoaded | Support along loaded edges |
| a | Unloaded edge length |
| bcUnloaded | Support along unloaded edges |
| t | Panel thickness |
| behaviour | Material behaviour |
| e | Young's modulus |
| nu | Elastic Poisson's ratio |
| n | Ramberg-Osgood parameter |
| iFy | Yield stress Allowable |
| sigma | Compressive stress |
| ms | Margin of safety |
| sigmaAllowable | Stress allowable |
|
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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 b Loaded edge length BC_Loaded Support along loaded edges {'Clamped';'Simply Supported'} a Unloaded edge length BC_Unloaded Support along unloaded edges {'Clamped-Clamped';'Simply Supported-Clamped';'Simply Supported-Simply Supported';'Free-Clamped';'Free-Simply Supported'} t Panel thickness behaviour Material behaviour E Young's modulus nu Elastic Poisson's ratio n Ramberg-Osgood parameter iFy Yield Stress Allowable beta Loading length ratio nblc Number of load cases sigma1 Compressive stress, side 1 sigma2 Compressive stress, side 2 Output sigmacr Compressive stress allowable sigmabcr Bending stress allowable MS Margin of safety Return Status of the calculation
Created in NX12.0.0
License requirements: sc_aero_environment ("Simcenter AeroStructures Environment"), sc_margin_safety ("Simcenter Margin Of Safety")
| abbContext | The ABB context |
| b | Loaded edge length |
| bcLoaded | Support along loaded edges |
| a | Unloaded edge length |
| bcUnloaded | Support along unloaded edges |
| t | Panel thickness |
| behaviour | Material behaviour |
| e | Young's modulus |
| nu | Elastic Poisson's ratio |
| n | Ramberg-Osgood parameter |
| iFy | Yield stress Allowable |
| sigma1 | Compressive stress, side 1 |
| sigma2 | Compressive stress, side 2 |
| ms | Margin of safety |
| sigmacr | Compressive stress allowable |
| sigmabcr | Bending stress allowable |
|
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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.
Input b Loaded edge length BC_Loaded Support along loaded edges {'Clamped';'Simply Supported'} a Unloaded edge length BC_Unloaded Support along unloaded edges {'Clamped-Clamped';'Simply Supported-Clamped';'Simply Supported-Simply Supported';'Free-Clamped';'Free-Simply Supported'} t Panel thickness behaviour Material behaviour {'Elastic'; 'Elastic-Plastic'} E Young's modulus nu Elastic Poisson's ratio n Ramberg-Osgood parameter iFy Yield Stress Allowable nblc Number of load cases sigma Compressive stress tau Shear stress Output sigmacr Compressive stress allowable taucr Shear stress allowable MS Margin of safety Return Status of the calculation
Created in NX12.0.0
License requirements: sc_aero_environment ("Simcenter AeroStructures Environment"), sc_margin_safety ("Simcenter Margin Of Safety")
| abbContext | The ABB context |
| b | Loaded edge length |
| bcLoaded | Support along loaded edges |
| a | Unloaded edge length |
| bcUnloaded | Support along unloaded edges |
| t | Panel thickness |
| behaviour | Material behaviour |
| e | Young's modulus |
| nu | Elastic Poisson's ratio |
| n | Ramberg-Osgood parameter |
| iFy | Yield stress Allowable |
| sigma | Compressive stress |
| tau | Shear stress |
| ms | Margin of safety |
| sigmacr | Compressive stress allowable |
| taucr | Shear stress allowable |
|
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MS Plate Buckling Flat Shear Computes margin of safety of a flat metallic rectangular panel under shear load
The formula is MS = tauAllowable / abs(tau) - 1
where: * 'tauAllowable' is the shear buckling stress allowable, * 'tau' is the compressive stress (MS is not calculated in case of tensile stress), * 'MS' is the margin of safety
Allowable = eta * PI^2*ks*E/(12*(1-nu^2)) * (t/b)^2 where * 'ks' is the bending buckling stress coefficient * 'E' is the Young's modulus * 'nu' is the elastic Poisson's ratio * 't' is the panel thickness * 'a' is the panel's longer edge length * 'b' is panel's shorter edge length * 'eta' is the plasticity reduction factor: SigmaAllowablePlastic = eta*SigmaAllowableElastic * eta = 1 if material is considered as elastic (Material behaviour = Elastic) * eta is obtain from following charts if material is considered as elastic-plastic (Material behaviour = Elastic-Plastic):
TauAllowablePlastic/F0.7 = f(TauAllowableElastic/F0.7) MetallicPanelCompressivePlasticityCurveBC1, Warning: in fact graph is fig C5.13 but it is C5.7 graph divided by 2
Input b Shorter edge length a Longer edge length BC Support along the edges {'Clamped';'Simply Supported'} t Panel thickness behaviour Material behaviour E Young's modulus nu Elastic Poisson's ratio n Ramberg-Osgood parameter iFy Yield Stress Allowable nblc Number of load cases tau Shear stress Output tauAllowable Stress allowable MS Margin of safety Return Status of the calculation
Created in NX12.0.0
License requirements: sc_aero_environment ("Simcenter AeroStructures Environment"), sc_margin_safety ("Simcenter Margin Of Safety")
| abbContext | The ABB context |
| b | Shorter edge length |
| a | Longer edge length |
| bc | Support along the edges |
| t | Panel thickness |
| behaviour | Material behaviour |
| e | Young's modulus |
| nu | Elastic Poisson's ratio |
| n | Ramberg-Osgood parameter |
| iFy | Yield stress Allowable |
| tau | Shear stress |
| ms | Margin of safety |
| tauAllowable | Stress allowable |
|
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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 b Loaded edge length BC_Loaded Support along loaded edges {'Clamped';'Simply Supported'} a Unloaded edge length BC_Unloaded Support along unloaded edges {'Clamped-Clamped';'Simply Supported-Clamped';'Simply Supported-Simply Supported';'Free-Clamped';'Free-Simply Supported'} t Panel thickness behaviour Material behaviour {'Elastic'; 'Elastic-Plastic'} E Young's modulus nu Elastic Poisson's ratio n Ramberg-Osgood parameter iFy Yield Stress Allowable nblc Number of load cases sigma1 Compressive stress, side 1 sigma2 Compressive stress, side 2 tau Shear stress 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
Created in NX12.0.0
License requirements: sc_aero_environment ("Simcenter AeroStructures Environment"), sc_margin_safety ("Simcenter Margin Of Safety")
| abbContext | The ABB context |
| b | Loaded edge length |
| bcLoaded | Support along loaded edges |
| a | Unloaded edge length |
| bcUnloaded | Support along unloaded edges |
| t | Panel thickness |
| behaviour | Material behaviour |
| e | Young's modulus |
| nu | Elastic Poisson's ratio |
| n | Ramberg-Osgood parameter |
| iFy | Yield stress Allowable |
| sigma1 | Compressive stress, side 1 |
| sigma2 | Compressive stress, side 2 |
| tau | Shear stress |
| ms | Margin of safety |
| sigmabcr | Bending stress allowable |
| taucr | Shear stress allowable |
|
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MS Shear Tear Out Computes margin of shear tear out (due to bolt hole)
The formula is MS = PShearTearOutAllowable / P - 1 * 'PShearTearOutAllowable' is the shear tear out load allowable. PShearTearOutAllowable = tauAllowable * 2 * t * ( b - D / 2 ) * 'tauAllowable' is the material shear stress allowable. For instance, it could be Fsu. * 'D' is the hole diameter * 't' is the thickness * 'b' is the distance from hole center to edge of the plate * 'P' is the axial load. P = FactorLoad * PExtracted * FactorLoad is the ratio of load between extracted load 'PExtracted' and 'P' * PExtracted is the extracted load.
Input nblc Number of loadcases D Diameter b Edge distance t Thickness Fs Material shear stress allowable f Load factor P(nblc) Axial load Output MS Margin of safety Return Status of the calculation
Created in NX12.0.0
License requirements: sc_aero_environment ("Simcenter AeroStructures Environment"), sc_margin_safety ("Simcenter Margin Of Safety")
| abbContext | The ABB context |
| d | Diameter |
| b | Edge distance |
| t | Thickness |
| iFs | Material shear stress allowable |
| f | Load factor |
| p | Axial load |
| ms | Margin of safety |
|
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MS Tresca.
Computes margin of safety based on Tresca yield criterion under plane stress condition
The yield criteria of isotropic materials limit the elastic domain during loading. According to the Tresca criterion, yield failure is expected when the greatest shear stress reaches the shear strength of the material. Thus, the maximum shear stress yield criterion can be specified as 'max((|S1-S2|)/2 , (|S1-S3|)/2, (|S2-S3|)/2) <= (STresca)/2' where * 'S1', 'S2' and 'S3' are the principal stresses. * 'STresca' is the Tresca equivalent stress allowable
A margin of safety can be derived from this formulation: 'MS = (STresca) / (max(|S1-S2| , |S1-S3|, |S2-S3|)) - 1' that must be greater than 0.
In a plane stress configuration, principal stresses are computed as 'S1 = (FX + FY)/2 + sqrt(((FX-FY)/2)^2 + FXY^2)' 'S2 = (FX + FY)/2 - sqrt(((FX-FY)/2)^2 + FXY^2)' where * 'FX' the normal stress in the X direction * 'FY' the normal stress in the Y direction * 'FXY' the shearing stress
Input iSTresca Tresca equivalent stress allowable nblc Number of load cases Fx Normal stress in the X direction iFy Normal stress in the Y direction Fxy Shear stress Output MS Margin of safety Return Status of the calculation
Created in NX12.0.0
License requirements: sc_aero_environment ("Simcenter AeroStructures Environment"), sc_margin_safety ("Simcenter Margin Of Safety")
| abbContext | The ABB context |
| iSTresca | Tresca equivalent stress allowable |
| iFx | Normal stress, X direction |
| iFy | Normal stress, Y direction |
| iFxy | Shear stress |
| ms | Margin of safety |
|
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MS Tsai-Hill
Computes margin of safety on the basis of Tsai-Hill failure theory (plane stress hypothesis)
For plane stress, this criterion can be written as: sigma1^2/X^2 - (sigma1 * sigma2)/X^2 + sigma2^2/Y^2 + tau^2/S^2 > 1
where:
* sigma1, sigma2 and tau are the components of the symmetric plane stress tensor in the material direction, * X is the longitudinal tensile (Xt; if sigma1 is in tension, e.g., sigma1 greater than 0) or compressive (Xc; if sigma1 is in compression, e.g., sigma1 less than 0) stress, * Y is the transverse tensile (Yt; if sigma2 is in tension, e.g., sigma2 greater than 0) or compressive (Yc; if sigma2 is in compression, e.g., sigma2 less than 0) stress, and * S is the in-plane shear stress.
Note: This equation is specialized for plane stress with the longitudinal strength X in the 1-direction.
The Margin of Safety, MS, is deduced from the criterion: MS = 1 / sqrt(sigma1^2/X^2 - (sigma1 * sigma2)/X^2 + sigma2^2/Y^2 + tau^2/S^2) - 1
Input Xt Longitudinal Tensile Strength Xc Longitudinal Compressive Strength Yt Transverse Tensile Strength Yc Transverse Compressive Strength S In-plane Shear Strength sigma1 Longitudinal Stresses sigma2 Transverse Stresses tau Shear Stresses Output MS Margin of safety Return Status of the calculation
Created in NX1899.0.0
License requirements: sc_aero_environment ("Simcenter AeroStructures Environment"), sc_margin_safety ("Simcenter Margin Of Safety")
| abbContext | The ABB context |
| iXt | Longitudinal Tensile Strength |
| iXc | Longitudinal Compressive Strength |
| iYt | Transverse Tensile Strength |
| iYc | Transverse Compressive Strength |
| s | In-plane Shear Strength |
| sigma1 | Longitudinal stresses |
| sigma2 | Transverse stresses |
| tau | Shear stresses |
| ms | Margin of Safety |
|
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Secant modulus Computes the secant modulus from material properties and stress.
The secant modulus ('Es') is defined as the stress('f') to strain ('epsilon') ratio at each value of stress.
The formula is 'Es = f / ( f / E + 0.002 * ( f / fy ) ^ n )' where: * 'f' is the stress * 'fy' is the yield stress * 'E' is the Young's modulus * 'n' is the Ramberg-Osgood parameter
The formula can be applied in compression and is 'Es = f / ( f / Ec + 0.002 * ( f / Fcy ) ^ nc)' where: * 'Fcy' is the compressive yield stress * 'Ec' is the compressive Young's modulus * 'nc' is the compressive Ramberg-Osgood parameter
Input E Young's modulus n Ramberg-Osgood parameter fy Yield stress sigma Stress Output Es Secant modulus Return Status of the computation
Created in NX12.0.0
License requirements: sc_aero_environment ("Simcenter AeroStructures Environment"), sc_margin_safety ("Simcenter Margin Of Safety")
| abbContext | The ABB context |
| e | Young's modulus |
| n | Ramberg-Osgood parameter |
| fy | Yield stress |
| sigma | Stress |
| iEs | Secant modulus |
|
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Stress F0.
7 Computes the stress for secant modulus equal to 70% of Young's modulus.
The calculation is based upon the material properties. 'F0.7' is defined by: 'F0.7/epsilon=0.7E', where 'epsilon' is the strain, and 'E' is the Young's modulus. The formula can be applied for tensile and compressive stress, hence: 'F0.7 = ( (1/0.7 - 1) / 0.002 * Fty ^ n / E ) ^ ( 1 / ( n - 1 ) )' for tension, and 'F0.7c = ( ( 1 / 0.7 - 1 ) / 0.002 * Fcy ^ nc / Ec ) ^ ( 1 / ( nc - 1 ) )' for compression.
where: * 'Fcy' is the compressive yield stress allowable * 'Fty' the tensile yield stress allowable * 'n' the Ramberg-Osgood parameter * 'Ec' the compressive Young's modulus * 'nc' the compressive Ramberg-Osgood parameter
Input iFy Yield stress allowable E Young's modulus n Ramberg-Osgood parameter Output F07 Secant yield stress F0.7
Created in NX12.0.0
License requirements: sc_aero_environment ("Simcenter AeroStructures Environment"), sc_margin_safety ("Simcenter Margin Of Safety")
| abbContext | The ABB context |
| iFy | Yield stress allowable |
| e | Young's modulus |
| n | Ramberg-Osgood's parameter |
| f07 | Secant yield stress F0.7 |
|
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Compute stress from strain with the help of Ramberg-Osgood relationship
The Ramberg-Osgood relationship allows to describe stress-strain curve with the help of a dedicated material parameter ('n'). 'e = f / E + 0.002 * ( f / f0.2ys ) ^ n' where: * 'e' is the total strain that takes into account elastic and plastic strains. * 'f' is the stress * 'E' is the material Young's modulus * 'f0.2ys' is the material yield allowable (Fcy or Fty depending load type). * 'n' is the Ramberg-Osgood parameter (in case of compressive load, it is common to call it 'nc').
The Ramberg-Osgood equation can not be inverted. As a consequence, stress is determined by numerical iterative calculation.
Input strain Total strain E Young's modulus F02ys Yield allowable (typically Fcy) n Ramberg-Osgood's parameter Output sigma Stress
Created in NX12.0.0
License requirements: sc_aero_environment ("Simcenter AeroStructures Environment"), sc_margin_safety ("Simcenter Margin Of Safety")
| abbContext | The ABB context |
| strain | Total strain |
| e | Young's modulus |
| iF02ys | Yield allowable (typically Fcy) |
| n | Ramberg-Osgood's parameter |
| sigma | Stress |
|
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Computes the tangent modulus from material properties and stress.
The tangent modulus ('Et') is defined as the slope of the stress('f')-strain('epsilon') curve at each value of stress.
The formula is 'Et = f / ( f / E + 0.002 * n * ( f / FY ) ^ n )' where: * 'f' is the stress * 'FY' is the yield stress * 'E' is the Young's modulus * 'n' is the Ramberg-Osgood parameter
The formula can be applied in compression and is 'Et=f/(f/Ec+0.002nc(f/(Fcy))^(nc))' where: * 'Fcy' is the compressive yield stress * 'Ec' is the compressive Young's modulus * 'nc' is the compressive Ramberg-Osgood parameter
Input E Young's modulus n Ramberg-Osgood parameter iFy Yield stress Allowable sigma Stress Output Et Tangent modulus
Created in NX12.0.0
License requirements: sc_aero_environment ("Simcenter AeroStructures Environment"), sc_margin_safety ("Simcenter Margin Of Safety")
| abbContext | The ABB context |
| e | Young's modulus |
| n | Ramberg-Osgood parameter |
| iFy | Yield stress Allowable |
| sigma | Stress |
| oEt | Tangent modulus |
|
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Returns the tag of this object.
