NXOpen::CAE::AeroStructures::Author::ABB Class Reference

Represents a AeroStruct application building block (ABB)
To obtain an instance of this class, refer to NXOpen::Session

Created in NX12.0.0. More...

Public Types
enum	EdgeSupportType { EdgeSupportTypeSimplySupported, EdgeSupportTypeClamped }
	Support along the edges, the choice is between SimplySupported and Clamped. More...
enum	MaterialBehaviour { MaterialBehaviourElastic, MaterialBehaviourElasticPlastic }
	Material behaivour type, the choices are: {Elastic, Elastic-plastic}. More...
enum	PlaneStressBoundaryConditions {   PlaneStressBoundaryConditionsSsss, PlaneStressBoundaryConditionsCscs, PlaneStressBoundaryConditionsScsc, PlaneStressBoundaryConditionsCccc,   PlaneStressBoundaryConditionsSfss }
	Plane stress boundary conditions, the choices are: {SSSS, SCSC, CCCC, SFSS}. More...
enum	Status { StatusSuccess, StatusFailed }
	ABB return status. More...
enum	UnloadedEdgeSupportType {   UnloadedEdgeSupportTypeClampedClamped, UnloadedEdgeSupportTypeSimplySupportedClamped, UnloadedEdgeSupportTypeSimplySupportedSimplySupported, UnloadedEdgeSupportTypeFreeClamped,   UnloadedEdgeSupportTypeFreeSimplySupported }
	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
NXOpen::CAE::AeroStructures::Author::ABB::Status	CurvedMetallicPanelCompressiveBucklingCoefficient (NXOpen::CAE::AeroStructures::Author::AbbContext *abbContext, double b, double t, double r, double nu, double *kc)
	Curves for finding 'kc' the compressive-buckling coefficient for curved sheet panel. More...
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, double *ks)
	Curves for finding 'ks' the shear-buckling coefficient for curved sheet panel. More...
NXOpen::CAE::AeroStructures::Author::ABB::Status	EquivalentSectionProperties (NXOpen::CAE::AeroStructures::Author::AbbContext *abbContext, const std::vector< double > &iAi, const std::vector< double > &iYcog, const std::vector< double > &iEi, const std::vector< double > &iIxxi, std::vector< double > &a, std::vector< double > &oYcog, std::vector< double > &e, std::vector< double > &oIxx)
	Compute equivalent section properties (area, center of gravity, Young's modulus and inertia) of a profile composed of different sub-sections. More...
NXOpen::CAE::AeroStructures::Author::ABB::Status	ExtrudedMetallicSubSectionCripplingAllowable (NXOpen::CAE::AeroStructures::Author::AbbContext *abbContext, double iFcy, double e, int fe, double b, double t, double *iFcc)
	Compute Crippling stress allowable for a given segment. More...
NXOpen::CAE::AeroStructures::Author::ABB::Status	FlatMetallicPanelBendingBucklingCoefficient (NXOpen::CAE::AeroStructures::Author::AbbContext *abbContext, double aOverB, double beta, double *kb)
	Curves for finding the bending buckling stress coefficient for thin flat plates. More...
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, double *kc)
	Curves for finding 'kc' the compressive-buckling coefficient for rectangular metallic flat plate. More...
NXOpen::CAE::AeroStructures::Author::ABB::Status	FlatMetallicPanelShearBucklingCoefficient (NXOpen::CAE::AeroStructures::Author::AbbContext *abbContext, double a, double b, NXOpen::CAE::AeroStructures::Author::ABB::EdgeSupportType bc, double *ks)
	Curves for finding 'ks' the shear-buckling coefficient for flat rectangular plate. More...
int	GetIntegerNa ()
	Integer NA value. More...
double	GetMsThreshold ()
	The MS (margin of safety) threshold. More...
double	GetPi ()
	PI number. More...
double	GetRealEpsilon ()
	Real epsilon. More...
double	GetRealMax ()
	Maximum real number. More...
double	GetRealNa ()
	Real NA. More...
double	GetRealNegativeInfinity ()
	The negative infinity value. More...
double	GetRealPositiveInfinity ()
	The positive infinity value. More...
double	GetUltimateLimitFactor ()
	Ultimate limit factor from the customer default. More...
bool	IsRealNa (double value)
	Tests if a value is NA. More...
bool	IsRealNegativeInfinity (double value)
	Tests if a value equals negative infinity. More...
bool	IsRealPositiveInfinity (double value)
	Tests if a value equals positive infinity. More...
NXOpen::CAE::AeroStructures::Author::ABB::Status	LoadDistributionBoltsConcentricLoads (NXOpen::CAE::AeroStructures::Author::AbbContext *abbContext, const std::vector< double > &p, const std::vector< double > &iPsn, std::vector< double > &oPn)
	Computes bolt loads for multiple bolt fitting - Concentric load. More...
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, double *oFsy)
	Estimation of shear yield stress (Fsy) More...
NXOpen::CAE::AeroStructures::Author::ABB::Status	MetallicPanelCompressivePlasticityCurveBc1 (NXOpen::CAE::AeroStructures::Author::AbbContext *abbContext, double x, double n, double *z)
	Metallic panel compressive plasticity curve BC1 Curves for finding critical buckling stress / secant yield stress F0.7. More...
NXOpen::CAE::AeroStructures::Author::ABB::Status	MetallicPanelCompressivePlasticityCurveBc2 (NXOpen::CAE::AeroStructures::Author::AbbContext *abbContext, double x, double n, double *z)
	Metallic panel compressive plasticity curve BC2 Curves for finding critical inter-rivet buckling stress (or critical wrinkling stress) / secant yield stress F0.7. More...
NXOpen::CAE::AeroStructures::Author::ABB::Status	MetallicPanelCompressivePlasticityCurveBc3 (NXOpen::CAE::AeroStructures::Author::AbbContext *abbContext, double x, double n, double *z)
	Metallic panel compressive plasticity curve BC3 Curves for finding critical buckling stress / secant yield stress F0.7. More...
NXOpen::CAE::AeroStructures::Author::ABB::Status	MsAllowable (NXOpen::CAE::AeroStructures::Author::AbbContext *abbContext, double allowable, const std::vector< double > &value, std::vector< double > &ms)
	MS allowable. More...
NXOpen::CAE::AeroStructures::Author::ABB::Status	MsBearing (NXOpen::CAE::AeroStructures::Author::AbbContext *abbContext, double d, double t, double iFbr, double f, const std::vector< double > &p, std::vector< double > &ms)
	MS bearing Computes margin of bearing. More...
NXOpen::CAE::AeroStructures::Author::ABB::Status	MsBoltBending (NXOpen::CAE::AeroStructures::Author::AbbContext *abbContext, double b, double iMba, double f, const std::vector< double > &p, std::vector< double > &ms)
	MS bolt bending Computes margin of safety of a bolt under bending load. More...
NXOpen::CAE::AeroStructures::Author::ABB::Status	MsBoltCombinedShearTension (NXOpen::CAE::AeroStructures::Author::AbbContext *abbContext, double iPtx, double iPss, const std::vector< double > &iPx, double f, const std::vector< double > &p, std::vector< double > &ms)
	MS bolt combined shear tension Computes margin of safety of a bolt under shear load and tension load. More...
NXOpen::CAE::AeroStructures::Author::ABB::Status	MsBoltCombinedShearTensionBending (NXOpen::CAE::AeroStructures::Author::AbbContext *abbContext, double b, double iMba, double iPtx, double iPss, double fb, const std::vector< double > &iPb, const std::vector< double > &iPx, double fs, const std::vector< double > &iPs, std::vector< double > &ms)
	MS bolt combined shear tension bending Computes margin of safety of a bolt under shear, tension and bending load. More...
NXOpen::CAE::AeroStructures::Author::ABB::Status	MsBoltShear (NXOpen::CAE::AeroStructures::Author::AbbContext *abbContext, double iPss, double f, const std::vector< double > &p, std::vector< double > &ms)
	MS bolt shear Computes margin of safety of a bolt under shear load. More...
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, const std::vector< double > &sigma, double *iPcr, std::vector< double > &ms)
	MS Column Eccentric Load. More...
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, const std::vector< double > &sigma, double *sigmacr, std::vector< double > &ms)
	MS Engesser. More...
NXOpen::CAE::AeroStructures::Author::ABB::Status	MsColumnEuler (NXOpen::CAE::AeroStructures::Author::AbbContext *abbContext, double a, double l, double e, double i, double c, const std::vector< double > &sigma, double *sigmacr, std::vector< double > &ms)
	MS Euler. More...
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, const std::vector< double > &sigma, double *sigmacr, std::vector< double > &ms)
	MS Column Johnson-Euler. More...
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, const std::vector< double > &load, double *iPcr, std::vector< double > &ms)
	MS Torsional Buckling. More...
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, const std::vector< double > &sigma, std::vector< double > &ms, double *sigmaAllowable)
	Computes margin of safety of a rectangular flat composite panel in buckling under compressive loads. More...
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, const std::vector< double > &sigma, const std::vector< double > &tau, std::vector< double > &ms, double *sigmaAllowable, double *tauAllowable)
	Computes margin of safety of a rectangular flat composite panel in buckling under combined shear and longitudinal loads. More...
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, const std::vector< double > &tau, std::vector< double > &ms, double *tauAllowable)
	Computes margin of safety of a rectangular flat composite panel in buckling under shear loads. More...
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, const std::vector< double > &sigma, std::vector< double > &ms)
	MS Inter-rivet buckling (Column) More...
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, const std::vector< double > &sigma, std::vector< double > &ms)
	MS Inter-rivet buckling (wide column) More...
NXOpen::CAE::AeroStructures::Author::ABB::Status	MsNetSection (NXOpen::CAE::AeroStructures::Author::AbbContext *abbContext, double d, double b, double t, double iFx, double f, const std::vector< double > &p, std::vector< double > &ms)
	MS Net section Computes margin of net section (due to bolt hole) More...
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, const std::vector< double > &sigma, std::vector< double > &ms)
	MS Plate Buckling Computes margin of safety of a metallic plate under buckling load (generic formula) More...
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, const std::vector< double > &sigma, std::vector< double > &ms, double *sigmaAllowable)
	MS Plate Buckling Curved Compressive Computes margin of safety of a curved metallic rectangular panel under compressive load. More...
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, const std::vector< double > &sigma, const std::vector< double > &tau, std::vector< double > &ms, double *sigmacr, 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...
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, const std::vector< double > &sigma, std::vector< double > &ms, double *sigmaAllowable)
	MS Plate Buckling Curved Shear Computes margin of safety of a curved metallic rectangular panel under shear load. More...
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, const std::vector< double > &sigma1, const std::vector< double > &sigma2, std::vector< double > &ms, std::vector< double > &sigmaAllowable)
	MS Plate Buckling Flat Bending Computes margin of safety of a flat metallic rectangular panel under bending load. More...
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, const std::vector< double > &sigma, std::vector< double > &ms, double *sigmaAllowable)
	MS Plate Buckling Flat Compressive Computes margin of safety of a flat metallic rectangular panel under compressive load. More...
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, const std::vector< double > &sigma1, const std::vector< double > &sigma2, std::vector< double > &ms, double *sigmacr, 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...
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, const std::vector< double > &sigma, const std::vector< double > &tau, std::vector< double > &ms, double *sigmacr, 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...
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, const std::vector< double > &sigma, std::vector< double > &ms, double *sigmaAllowable)
	MS Plate Buckling Flat Shear Computes margin of safety of a flat metallic rectangular panel under shear load. More...
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, const std::vector< double > &sigma1, const std::vector< double > &sigma2, const std::vector< double > &tau, std::vector< double > &ms, std::vector< double > &sigmabcr, 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...
NXOpen::CAE::AeroStructures::Author::ABB::Status	MsShearTearOut (NXOpen::CAE::AeroStructures::Author::AbbContext *abbContext, double d, double b, double t, double iFs, double f, const std::vector< double > &p, std::vector< double > &ms)
	MS Shear Tear Out Computes margin of shear tear out (due to bolt hole) More...
NXOpen::CAE::AeroStructures::Author::ABB::Status	MsTrescaPlaneStress (NXOpen::CAE::AeroStructures::Author::AbbContext *abbContext, double iSTresca, const std::vector< double > &iFx, const std::vector< double > &iFy, const std::vector< double > &iFxy, std::vector< double > &ms)
	MS Tresca. More...
NXOpen::CAE::AeroStructures::Author::ABB::Status	SecantModulus (NXOpen::CAE::AeroStructures::Author::AbbContext *abbContext, double e, double n, double fy, double sigma, double *iEs)
	Secant modulus Computes the secant modulus from material properties and stress. More...
NXOpen::CAE::AeroStructures::Author::ABB::Status	StressF07 (NXOpen::CAE::AeroStructures::Author::AbbContext *abbContext, double iFy, double e, double n, double *f07)
	Stress F0.7 Computes the stress for secant modulus equal to 70% of Young's modulus. More...
NXOpen::CAE::AeroStructures::Author::ABB::Status	StressFromStrainInPlasticDomain (NXOpen::CAE::AeroStructures::Author::AbbContext *abbContext, double strain, double e, double iF02ys, double n, double *sigma)
	Compute stress from strain with the help of Ramberg-Osgood relationship. More...
tag_t	Tag () const
	Returns the tag of this object. More...
NXOpen::CAE::AeroStructures::Author::ABB::Status	TangentModulus (NXOpen::CAE::AeroStructures::Author::AbbContext *abbContext, double e, double n, double iFy, double sigma, double *oEt)
	Computes the tangent modulus from material properties and stress. 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...

Detailed Description

Represents a AeroStruct application building block (ABB)
To obtain an instance of this class, refer to NXOpen::Session

Created in NX12.0.0.

Member Enumeration Documentation

enum NXOpen::CAE::AeroStructures::Author::ABB::EdgeSupportType

Support along the edges, the choice is between SimplySupported and Clamped.

Enumerator
EdgeSupportTypeSimplySupported	Simply Supported.
EdgeSupportTypeClamped	Clamped.

enum NXOpen::CAE::AeroStructures::Author::ABB::MaterialBehaviour

Material behaivour type, the choices are: {Elastic, Elastic-plastic}.

Enumerator
MaterialBehaviourElastic	Elastic behaviour.
MaterialBehaviourElasticPlastic	Elastic-plastic behaviour.

enum NXOpen::CAE::AeroStructures::Author::ABB::PlaneStressBoundaryConditions

Plane stress boundary conditions, the choices are: {SSSS, SCSC, CCCC, SFSS}.

Enumerator
PlaneStressBoundaryConditionsSsss	loaded edges: simply supported, unloaded edges: simply supported - simply supported
PlaneStressBoundaryConditionsCscs	loaded edges: clamped, unloaded edges: simply supported - simply supported
PlaneStressBoundaryConditionsScsc	loaded edges: simply supported, unloaded edges: clamped - clamped
PlaneStressBoundaryConditionsCccc	loaded edges: clamped, unloaded edges: clamped - clamped
PlaneStressBoundaryConditionsSfss	loaded edges: simply supported, unloaded edges: free - simply supported

enum NXOpen::CAE::AeroStructures::Author::ABB::Status

ABB return status.

Enumerator
StatusSuccess	ABB computation success.
StatusFailed	ABB computation failed.

enum NXOpen::CAE::AeroStructures::Author::ABB::UnloadedEdgeSupportType

Support along unloaded edges, the choices are: {Clamped-Clamped, Simply Supported-Clamped, Simply Supported-Simply Supported, Free-Clamped, Free-Simply Supported}.

Enumerator
UnloadedEdgeSupportTypeClampedClamped	Clamped-Clamped.
UnloadedEdgeSupportTypeSimplySupportedClamped	Simply Supported-Clamped.
UnloadedEdgeSupportTypeSimplySupportedSimplySupported	Simply Supported-Simply Supported.
UnloadedEdgeSupportTypeFreeClamped	Free-Clamped.
UnloadedEdgeSupportTypeFreeSimplySupported	Free-Simply Supported.

Member Function Documentation

NXOpen::CAE::AeroStructures::Author::ABB::Status NXOpen::CAE::AeroStructures::Author::ABB::CurvedMetallicPanelCompressiveBucklingCoefficient	(	NXOpen::CAE::AeroStructures::Author::AbbContext *	abbContext,
		double	b,
		double	t,
		double	r,
		double	nu,
		double *	kc
	)

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")

Parameters

abbContext	The ABB context
b	Dimension in radial axis
t	Panel thickness
r	Panel radius
nu	Material Poisson's ratio
kc	Compressive-buckling coefficient

NXOpen::CAE::AeroStructures::Author::ABB::Status NXOpen::CAE::AeroStructures::Author::ABB::CurvedMetallicPanelShearBucklingCoefficient	(	NXOpen::CAE::AeroStructures::Author::AbbContext *	abbContext,
		double	a,
		double	b,
		double	t,
		double	r,
		double	nu,
		NXOpen::CAE::AeroStructures::Author::ABB::EdgeSupportType	bc,
		double *	ks
	)

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")

Parameters

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

NXOpen::CAE::AeroStructures::Author::ABB::Status NXOpen::CAE::AeroStructures::Author::ABB::EquivalentSectionProperties	(	NXOpen::CAE::AeroStructures::Author::AbbContext *	abbContext,
		const std::vector< double > &	iAi,
		const std::vector< double > &	iYcog,
		const std::vector< double > &	iEi,
		const std::vector< double > &	iIxxi,
		std::vector< double > &	a,
		std::vector< double > &	oYcog,
		std::vector< double > &	e,
		std::vector< double > &	oIxx
	)

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")

Parameters

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)

NXOpen::CAE::AeroStructures::Author::ABB::Status NXOpen::CAE::AeroStructures::Author::ABB::ExtrudedMetallicSubSectionCripplingAllowable	(	NXOpen::CAE::AeroStructures::Author::AbbContext *	abbContext,
		double	iFcy,
		double	e,
		int	fe,
		double	b,
		double	t,
		double *	iFcc
	)

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")

Parameters

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

NXOpen::CAE::AeroStructures::Author::ABB::Status NXOpen::CAE::AeroStructures::Author::ABB::FlatMetallicPanelBendingBucklingCoefficient	(	NXOpen::CAE::AeroStructures::Author::AbbContext *	abbContext,
		double	aOverB,
		double	beta,
		double *	kb
	)

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")

Parameters

abbContext	The ABB context
aOverB	Panel length ratio
beta	Loading length ratio
kb	Bending buckling stress coefficient

NXOpen::CAE::AeroStructures::Author::ABB::Status NXOpen::CAE::AeroStructures::Author::ABB::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,
		double *	kc
	)

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")

Parameters

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

NXOpen::CAE::AeroStructures::Author::ABB::Status NXOpen::CAE::AeroStructures::Author::ABB::FlatMetallicPanelShearBucklingCoefficient	(	NXOpen::CAE::AeroStructures::Author::AbbContext *	abbContext,
		double	a,
		double	b,
		NXOpen::CAE::AeroStructures::Author::ABB::EdgeSupportType	bc,
		double *	ks
	)

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")

Parameters

abbContext	The ABB context
a	Longer plate dimension
b	Shorter plate dimension
bc	Support along the edges
ks	Shear-buckling coefficient

static ABB* NXOpen::CAE::AeroStructures::Author::ABB::GetABB ( NXOpen::Session *  owner )

static

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.

int NXOpen::CAE::AeroStructures::Author::ABB::GetIntegerNa

(

)

Integer NA value.

Created in NX12.0.0.

License requirements : sc_aero_environment ("Simcenter AeroStructures Environment"), sc_margin_safety ("Simcenter Margin Of Safety")

double NXOpen::CAE::AeroStructures::Author::ABB::GetMsThreshold

(

)

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")

double NXOpen::CAE::AeroStructures::Author::ABB::GetPi

(

)

PI number.

Created in NX12.0.0.

License requirements : sc_aero_environment ("Simcenter AeroStructures Environment"), sc_margin_safety ("Simcenter Margin Of Safety")

double NXOpen::CAE::AeroStructures::Author::ABB::GetRealEpsilon

(

)

Real epsilon.

Created in NX12.0.0.

License requirements : sc_aero_environment ("Simcenter AeroStructures Environment"), sc_margin_safety ("Simcenter Margin Of Safety")

double NXOpen::CAE::AeroStructures::Author::ABB::GetRealMax

(

)

Maximum real number.

Created in NX12.0.0.

License requirements : sc_aero_environment ("Simcenter AeroStructures Environment"), sc_margin_safety ("Simcenter Margin Of Safety")

double NXOpen::CAE::AeroStructures::Author::ABB::GetRealNa

(

)

Real NA.

Created in NX12.0.0.

License requirements : sc_aero_environment ("Simcenter AeroStructures Environment"), sc_margin_safety ("Simcenter Margin Of Safety")

double NXOpen::CAE::AeroStructures::Author::ABB::GetRealNegativeInfinity

(

)

The negative infinity value.

Created in NX12.0.0.

License requirements : sc_aero_environment ("Simcenter AeroStructures Environment"), sc_margin_safety ("Simcenter Margin Of Safety")

double NXOpen::CAE::AeroStructures::Author::ABB::GetRealPositiveInfinity

(

)

The positive infinity value.

Created in NX12.0.0.

License requirements : sc_aero_environment ("Simcenter AeroStructures Environment"), sc_margin_safety ("Simcenter Margin Of Safety")

double NXOpen::CAE::AeroStructures::Author::ABB::GetUltimateLimitFactor

(

)

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")

bool NXOpen::CAE::AeroStructures::Author::ABB::IsRealNa

(

double

value

)

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")

Parameters

value

value

bool NXOpen::CAE::AeroStructures::Author::ABB::IsRealNegativeInfinity

(

double

value

)

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")

Parameters

value

value

bool NXOpen::CAE::AeroStructures::Author::ABB::IsRealPositiveInfinity

(

double

value

)

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")

Parameters

value

value

NXOpen::CAE::AeroStructures::Author::ABB::Status NXOpen::CAE::AeroStructures::Author::ABB::LoadDistributionBoltsConcentricLoads	(	NXOpen::CAE::AeroStructures::Author::AbbContext *	abbContext,
		const std::vector< double > &	p,
		const std::vector< double > &	iPsn,
		std::vector< double > &	oPn
	)

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")

Parameters

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)

NXOpen::CAE::AeroStructures::Author::ABB::Status NXOpen::CAE::AeroStructures::Author::ABB::MaterialFsyEstimation	(	NXOpen::CAE::AeroStructures::Author::AbbContext *	abbContext,
		double	iFtyL,
		double	iFtyLT,
		double	iFcyL,
		double	iFcyLT,
		double	iFsu,
		double	iFtuL,
		double	iFtuLT,
		double *	oFsy
	)

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")

Parameters

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

NXOpen::CAE::AeroStructures::Author::ABB::Status NXOpen::CAE::AeroStructures::Author::ABB::MetallicPanelCompressivePlasticityCurveBc1	(	NXOpen::CAE::AeroStructures::Author::AbbContext *	abbContext,
		double	x,
		double	n,
		double *	z
	)

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")

Parameters

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

NXOpen::CAE::AeroStructures::Author::ABB::Status NXOpen::CAE::AeroStructures::Author::ABB::MetallicPanelCompressivePlasticityCurveBc2	(	NXOpen::CAE::AeroStructures::Author::AbbContext *	abbContext,
		double	x,
		double	n,
		double *	z
	)

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")

Parameters

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

NXOpen::CAE::AeroStructures::Author::ABB::Status NXOpen::CAE::AeroStructures::Author::ABB::MetallicPanelCompressivePlasticityCurveBc3	(	NXOpen::CAE::AeroStructures::Author::AbbContext *	abbContext,
		double	x,
		double	n,
		double *	z
	)

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")

Parameters

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

NXOpen::CAE::AeroStructures::Author::ABB::Status NXOpen::CAE::AeroStructures::Author::ABB::MsAllowable	(	NXOpen::CAE::AeroStructures::Author::AbbContext *	abbContext,
		double	allowable,
		const std::vector< double > &	value,
		std::vector< double > &	ms
	)

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")

Parameters

abbContext	The ABB context
allowable	Manual input
value	Value coming from load extractor
ms	Margin of safety

NXOpen::CAE::AeroStructures::Author::ABB::Status NXOpen::CAE::AeroStructures::Author::ABB::MsBearing	(	NXOpen::CAE::AeroStructures::Author::AbbContext *	abbContext,
		double	d,
		double	t,
		double	iFbr,
		double	f,
		const std::vector< double > &	p,
		std::vector< double > &	ms
	)

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")

Parameters

abbContext	The ABB context
d	Diameter
t	Thickness
iFbr	Bearing stress allowable
f	Load factor
p	Shear load
ms	Margin of safety

NXOpen::CAE::AeroStructures::Author::ABB::Status NXOpen::CAE::AeroStructures::Author::ABB::MsBoltBending	(	NXOpen::CAE::AeroStructures::Author::AbbContext *	abbContext,
		double	b,
		double	iMba,
		double	f,
		const std::vector< double > &	p,
		std::vector< double > &	ms
	)

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")

Parameters

abbContext	The ABB context
b	Arm
iMba	Bending moment allowable of bolt
f	Load factor
p	Shear load
ms	Margin of safety

NXOpen::CAE::AeroStructures::Author::ABB::Status NXOpen::CAE::AeroStructures::Author::ABB::MsBoltCombinedShearTension	(	NXOpen::CAE::AeroStructures::Author::AbbContext *	abbContext,
		double	iPtx,
		double	iPss,
		const std::vector< double > &	iPx,
		double	f,
		const std::vector< double > &	p,
		std::vector< double > &	ms
	)

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")

Parameters

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

NXOpen::CAE::AeroStructures::Author::ABB::Status NXOpen::CAE::AeroStructures::Author::ABB::MsBoltCombinedShearTensionBending	(	NXOpen::CAE::AeroStructures::Author::AbbContext *	abbContext,
		double	b,
		double	iMba,
		double	iPtx,
		double	iPss,
		double	fb,
		const std::vector< double > &	iPb,
		const std::vector< double > &	iPx,
		double	fs,
		const std::vector< double > &	iPs,
		std::vector< double > &	ms
	)

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")

Parameters

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

NXOpen::CAE::AeroStructures::Author::ABB::Status NXOpen::CAE::AeroStructures::Author::ABB::MsBoltShear	(	NXOpen::CAE::AeroStructures::Author::AbbContext *	abbContext,
		double	iPss,
		double	f,
		const std::vector< double > &	p,
		std::vector< double > &	ms
	)

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")

Parameters

abbContext	The ABB context
iPss	Single shear load allowable
f	Shear load factor
p	Shear load
ms	Margin of safety

NXOpen::CAE::AeroStructures::Author::ABB::Status NXOpen::CAE::AeroStructures::Author::ABB::MsColumnEccentricLoadSecantFormula	(	NXOpen::CAE::AeroStructures::Author::AbbContext *	abbContext,
		double	a,
		double	l,
		double	e,
		double	i,
		double	sigmacr,
		double	c,
		double	ecc,
		double	extrmfbrdist,
		const std::vector< double > &	sigma,
		double *	iPcr,
		std::vector< double > &	ms
	)

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")

Parameters

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

NXOpen::CAE::AeroStructures::Author::ABB::Status NXOpen::CAE::AeroStructures::Author::ABB::MsColumnEngesser	(	NXOpen::CAE::AeroStructures::Author::AbbContext *	abbContext,
		double	a,
		double	l,
		double	e,
		double	i,
		double	n,
		double	iFy,
		double	c,
		const std::vector< double > &	sigma,
		double *	sigmacr,
		std::vector< double > &	ms
	)

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")

Parameters

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

NXOpen::CAE::AeroStructures::Author::ABB::Status NXOpen::CAE::AeroStructures::Author::ABB::MsColumnEuler	(	NXOpen::CAE::AeroStructures::Author::AbbContext *	abbContext,
		double	a,
		double	l,
		double	e,
		double	i,
		double	c,
		const std::vector< double > &	sigma,
		double *	sigmacr,
		std::vector< double > &	ms
	)

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")

Parameters

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

NXOpen::CAE::AeroStructures::Author::ABB::Status NXOpen::CAE::AeroStructures::Author::ABB::MsColumnJohnsonEuler	(	NXOpen::CAE::AeroStructures::Author::AbbContext *	abbContext,
		double	a,
		double	l,
		double	i,
		double	e,
		double	c,
		double	sigma0,
		const std::vector< double > &	sigma,
		double *	sigmacr,
		std::vector< double > &	ms
	)

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")

Parameters

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

NXOpen::CAE::AeroStructures::Author::ABB::Status NXOpen::CAE::AeroStructures::Author::ABB::MsColumnTorsionalbuckling	(	NXOpen::CAE::AeroStructures::Author::AbbContext *	abbContext,
		double	l,
		double	e,
		double	g,
		double	j,
		double	gamma,
		double	r0,
		double	c,
		const std::vector< double > &	load,
		double *	iPcr,
		std::vector< double > &	ms
	)

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")

Parameters

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

NXOpen::CAE::AeroStructures::Author::ABB::Status NXOpen::CAE::AeroStructures::Author::ABB::MsCompositePlateBucklingFlatCompressive	(	NXOpen::CAE::AeroStructures::Author::AbbContext *	abbContext,
		double	b,
		double	a,
		NXOpen::CAE::AeroStructures::Author::ABB::PlaneStressBoundaryConditions	bc,
		NXOpen::CAE::AeroStructures::Laminate *	laminate,
		const std::vector< double > &	sigma,
		std::vector< double > &	ms,
		double *	sigmaAllowable
	)

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")

Parameters

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

NXOpen::CAE::AeroStructures::Author::ABB::Status NXOpen::CAE::AeroStructures::Author::ABB::MsCompositePlateBucklingFlatLongitudinalShearCombined	(	NXOpen::CAE::AeroStructures::Author::AbbContext *	abbContext,
		double	b,
		double	a,
		NXOpen::CAE::AeroStructures::Author::ABB::PlaneStressBoundaryConditions	bc,
		NXOpen::CAE::AeroStructures::Laminate *	laminate,
		const std::vector< double > &	sigma,
		const std::vector< double > &	tau,
		std::vector< double > &	ms,
		double *	sigmaAllowable,
		double *	tauAllowable
	)

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")

Parameters

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

NXOpen::CAE::AeroStructures::Author::ABB::Status NXOpen::CAE::AeroStructures::Author::ABB::MsCompositePlateBucklingFlatShear	(	NXOpen::CAE::AeroStructures::Author::AbbContext *	abbContext,
		double	b,
		double	a,
		NXOpen::CAE::AeroStructures::Author::ABB::PlaneStressBoundaryConditions	bc,
		NXOpen::CAE::AeroStructures::Laminate *	laminate,
		const std::vector< double > &	tau,
		std::vector< double > &	ms,
		double *	tauAllowable
	)

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 unloaded edge length 'b' is the loaded 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 Loaded edge length a Unloaded 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")

Parameters

abbContext	The ABB context
b	Loaded edge length
a	Unloaded edge length
bc	Edges Boundary Conditions
laminate	Laminate
tau	Shear stresses
ms	Margin of safety
tauAllowable	Shear stress allowable

NXOpen::CAE::AeroStructures::Author::ABB::Status NXOpen::CAE::AeroStructures::Author::ABB::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,
		const std::vector< double > &	sigma,
		std::vector< double > &	ms
	)

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")

Parameters

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

NXOpen::CAE::AeroStructures::Author::ABB::Status NXOpen::CAE::AeroStructures::Author::ABB::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,
		const std::vector< double > &	sigma,
		std::vector< double > &	ms
	)

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")

Parameters

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

NXOpen::CAE::AeroStructures::Author::ABB::Status NXOpen::CAE::AeroStructures::Author::ABB::MsNetSection	(	NXOpen::CAE::AeroStructures::Author::AbbContext *	abbContext,
		double	d,
		double	b,
		double	t,
		double	iFx,
		double	f,
		const std::vector< double > &	p,
		std::vector< double > &	ms
	)

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")

Parameters

abbContext	The ABB context
d	Diameter
b	Width
t	Thickness
iFx	Material stress allowable
f	Load factor
p	Axial load
ms	Margin of safety

NXOpen::CAE::AeroStructures::Author::ABB::Status NXOpen::CAE::AeroStructures::Author::ABB::MsPlateBuckling	(	NXOpen::CAE::AeroStructures::Author::AbbContext *	abbContext,
		double	b,
		double	t,
		double	e,
		double	nu,
		double	eta,
		double	k,
		const std::vector< double > &	sigma,
		std::vector< double > &	ms
	)

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")

Parameters

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

NXOpen::CAE::AeroStructures::Author::ABB::Status NXOpen::CAE::AeroStructures::Author::ABB::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,
		const std::vector< double > &	sigma,
		std::vector< double > &	ms,
		double *	sigmaAllowable
	)

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/Sigma0.7 = f(SigmaAllowableElastic/Sigma0.7)

MetallicPanelCompressivePlasticityCurveBC3 with Sigma0.7 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")

Parameters

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

NXOpen::CAE::AeroStructures::Author::ABB::Status NXOpen::CAE::AeroStructures::Author::ABB::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,
		const std::vector< double > &	sigma,
		const std::vector< double > &	tau,
		std::vector< double > &	ms,
		double *	sigmacr,
		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.

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")

Parameters

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

NXOpen::CAE::AeroStructures::Author::ABB::Status NXOpen::CAE::AeroStructures::Author::ABB::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,
		const std::vector< double > &	sigma,
		std::vector< double > &	ms,
		double *	sigmaAllowable
	)

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: SigmaAllowablePlastic = eta*SigmaAllowableElastic 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): SigmaAllowablePlastic/Sigma0.7 = f(SigmaAllowableElastic/Sigma0.7) Sigma0.7 is the stress for secant modulus equal to 70% of Young's modulus

Input b Loaded edge length a Unloaded 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 sigma Shear 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")

Parameters

abbContext	The ABB context
b	Longest edge length
a	Shortest 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
sigma	Shear stress
ms	Margin of safety
sigmaAllowable	Stress allowable

NXOpen::CAE::AeroStructures::Author::ABB::Status NXOpen::CAE::AeroStructures::Author::ABB::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,
		const std::vector< double > &	sigma1,
		const std::vector< double > &	sigma2,
		std::vector< double > &	ms,
		std::vector< double > &	sigmaAllowable
	)

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/Sigma0.7 = f(SigmaAllowableElastic/Sigma0.7)

MetallicPanelCompressivePlasticityCurveBC2 with Sigma0.7 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")

Parameters

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

NXOpen::CAE::AeroStructures::Author::ABB::Status NXOpen::CAE::AeroStructures::Author::ABB::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,
		const std::vector< double > &	sigma,
		std::vector< double > &	ms,
		double *	sigmaAllowable
	)

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/Sigma0.7 = f(SigmaAllowableElastic/Sigma0.7) 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")

Parameters

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

NXOpen::CAE::AeroStructures::Author::ABB::Status NXOpen::CAE::AeroStructures::Author::ABB::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,
		const std::vector< double > &	sigma1,
		const std::vector< double > &	sigma2,
		std::vector< double > &	ms,
		double *	sigmacr,
		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.

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")

Parameters

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

NXOpen::CAE::AeroStructures::Author::ABB::Status NXOpen::CAE::AeroStructures::Author::ABB::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,
		const std::vector< double > &	sigma,
		const std::vector< double > &	tau,
		std::vector< double > &	ms,
		double *	sigmacr,
		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.

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")

Parameters

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

NXOpen::CAE::AeroStructures::Author::ABB::Status NXOpen::CAE::AeroStructures::Author::ABB::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,
		const std::vector< double > &	sigma,
		std::vector< double > &	ms,
		double *	sigmaAllowable
	)

MS Plate Buckling Flat Shear Computes margin of safety of a flat metallic rectangular panel under shear load.

The formula is MS = sigmaAllowable / abs(sigma) - 1

where: 'sigmaAllowable' is the shear 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*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 loaded edge length 'b' is panel's unloaded 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/Sigma0.7 = f(SigmaAllowableElastic/Sigma0.7) MetallicPanelCompressivePlasticityCurveBC1, Warning: in fact graph is fig C5.13 but it is C5.7 graph divided by 2

Input b Loaded edge length a Unloaded 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 sigma Shear 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")

Parameters

abbContext	The ABB context
b	Loaded edge length
a	Unloaded 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
sigma	Shear stress
ms	Margin of safety
sigmaAllowable	Stress allowable

NXOpen::CAE::AeroStructures::Author::ABB::Status NXOpen::CAE::AeroStructures::Author::ABB::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,
		const std::vector< double > &	sigma1,
		const std::vector< double > &	sigma2,
		const std::vector< double > &	tau,
		std::vector< double > &	ms,
		std::vector< double > &	sigmabcr,
		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.

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")

Parameters

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

NXOpen::CAE::AeroStructures::Author::ABB::Status NXOpen::CAE::AeroStructures::Author::ABB::MsShearTearOut	(	NXOpen::CAE::AeroStructures::Author::AbbContext *	abbContext,
		double	d,
		double	b,
		double	t,
		double	iFs,
		double	f,
		const std::vector< double > &	p,
		std::vector< double > &	ms
	)

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")

Parameters

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

NXOpen::CAE::AeroStructures::Author::ABB::Status NXOpen::CAE::AeroStructures::Author::ABB::MsTrescaPlaneStress	(	NXOpen::CAE::AeroStructures::Author::AbbContext *	abbContext,
		double	iSTresca,
		const std::vector< double > &	iFx,
		const std::vector< double > &	iFy,
		const std::vector< double > &	iFxy,
		std::vector< double > &	ms
	)

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")

Parameters

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

NXOpen::CAE::AeroStructures::Author::ABB::Status NXOpen::CAE::AeroStructures::Author::ABB::SecantModulus	(	NXOpen::CAE::AeroStructures::Author::AbbContext *	abbContext,
		double	e,
		double	n,
		double	fy,
		double	sigma,
		double *	iEs
	)

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")

Parameters

abbContext	The ABB context
e	Young's modulus
n	Ramberg-Osgood parameter
fy	Yield stress
sigma	Stress
iEs	Secant modulus

NXOpen::CAE::AeroStructures::Author::ABB::Status NXOpen::CAE::AeroStructures::Author::ABB::StressF07	(	NXOpen::CAE::AeroStructures::Author::AbbContext *	abbContext,
		double	iFy,
		double	e,
		double	n,
		double *	f07
	)

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")

Parameters

abbContext	The ABB context
iFy	Yield stress allowable
e	Young's modulus
n	Ramberg-Osgood's parameter
f07	Secant yield stress F0.7

NXOpen::CAE::AeroStructures::Author::ABB::Status NXOpen::CAE::AeroStructures::Author::ABB::StressFromStrainInPlasticDomain	(	NXOpen::CAE::AeroStructures::Author::AbbContext *	abbContext,
		double	strain,
		double	e,
		double	iF02ys,
		double	n,
		double *	sigma
	)

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")

Parameters

abbContext	The ABB context
strain	Total strain
e	Young's modulus
iF02ys	Yield allowable (typically Fcy)
n	Ramberg-Osgood's parameter
sigma	Stress

tag_t NXOpen::CAE::AeroStructures::Author::ABB::Tag

(

)

const

Returns the tag of this object.

NXOpen::CAE::AeroStructures::Author::ABB::Status NXOpen::CAE::AeroStructures::Author::ABB::TangentModulus	(	NXOpen::CAE::AeroStructures::Author::AbbContext *	abbContext,
		double	e,
		double	n,
		double	iFy,
		double	sigma,
		double *	oEt
	)

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")

Parameters

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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The documentation for this class was generated from the following file:

• CAE_AeroStructures_Author_ABB.hxx