Represents a AeroStruct application building block (ABB) More...

Inheritance diagram for NXOpen.CAE.AeroStructures.Author.ABB:

Public Types
enum	Status { Success, Failed }
	ABB return status More...

enum	EdgeSupportType { SimplySupported, Clamped }
	Type of support along the edges, the choice is between SimplySupported and Clamped More...

enum	UnloadedEdgeSupportType { ClampedClamped, SimplySupportedClamped, SimplySupportedSimplySupported, FreeClamped, FreeSimplySupported }
	Type of support along unloaded edges, the choices are: {Clamped-Clamped, Simply Supported-Clamped, Simply Supported-Simply Supported, Free-Clamped, Free-Simply Supported} More...

enum	MaterialBehaviour { Elastic, ElasticPlastic }
	Material behaivour type, the choices are: {Elastic, Elastic-plastic} More...

Public Member Functions
unsafe double	GetUltimateLimitFactor ()
	Ultimate limit factor from the customer default More...

unsafe double	GetIntegerNa ()
	Integer NA value More...

unsafe double	GetPi ()
	PI number More...

unsafe double	GetRealMax ()
	Maximum real number More...

unsafe double	GetRealEpsilon ()
	Real epsilon More...

unsafe double	GetRealNa ()
	Real NA More...

unsafe bool	IsRealNa (double value)
	Tests if a value is NA More...

unsafe double	GetRealPositiveInfinity ()
	The positive infinity value More...

unsafe bool	IsRealPositiveInfinity (double value)
	Tests if a value equals positive infinity More...

unsafe double	GetRealNegativeInfinity ()
	The negative infinity value More...

unsafe bool	IsRealNegativeInfinity (double value)
	Tests if a value equals negative infinity More...

unsafe double	GetMsThreshold ()
	The MS (margin of safety) threshold More...

unsafe NXOpen.CAE.AeroStructures.Author.ABB.Status	CurvedMetallicPanelCompressiveBucklingCoefficient (double b, double t, double r, double nu, out double kc)
	Curves for finding 'kc' the compressive-buckling coefficient for curved sheet panel More...

unsafe NXOpen.CAE.AeroStructures.Author.ABB.Status	CurvedMetallicPanelShearBucklingCoefficient (double a, double b, double t, double r, double nu, NXOpen.CAE.AeroStructures.Author.ABB.EdgeSupportType bc, out double ks)
	Curves for finding 'ks' the shear-buckling coefficient for curved sheet panel More...

unsafe NXOpen.CAE.AeroStructures.Author.ABB.Status	EquivalentSectionProperties (double[] n, double[] iAi, double[] iEi, double[] iIxxi, out double[] a, out double[] e, out double[] oYcog, out double[] oIxx)
	Compute equivalent section properties (area, center of gravity, Young's modulus and inertia) of a profile composed of different sub-sections. More...

unsafe NXOpen.CAE.AeroStructures.Author.ABB.Status	ExtrudedMetallicSubSectionCripplingAllowable (double iFcy, double e, int fe, double b, double t, out double iFcc)
	Compute Crippling stress allowable for a given segment More...

unsafe NXOpen.CAE.AeroStructures.Author.ABB.Status	FlatMetallicPanelBendingBucklingCoefficient (double aOverB, double beta, out double kb)
	Curves for finding the bending buckling stress coefficient for thin flat plates More...

unsafe NXOpen.CAE.AeroStructures.Author.ABB.Status	FlatMetallicPanelCompressiveBucklingCoefficient (double a, double b, NXOpen.CAE.AeroStructures.Author.ABB.UnloadedEdgeSupportType bcUnloaded, NXOpen.CAE.AeroStructures.Author.ABB.EdgeSupportType bcLoaded, out double kc)
	Curves for finding 'kc' the compressive-buckling coefficient for rectangular metallic flat plate More...

unsafe NXOpen.CAE.AeroStructures.Author.ABB.Status	FlatMetallicPanelShearBucklingCoefficient (double a, double b, NXOpen.CAE.AeroStructures.Author.ABB.EdgeSupportType bc, out double ks)
	Curves for finding 'ks' the shear-buckling coefficient for flat rectangular plate More...

unsafe NXOpen.CAE.AeroStructures.Author.ABB.Status	LoadDistributionBoltsConcentricLoads (double[] p, double[] iPsn, int nblcXnbbolt, out double[] oPn)
	Computes bolt loads for multiple bolt fitting - Concentric load More...

unsafe NXOpen.CAE.AeroStructures.Author.ABB.Status	MaterialFsyEstimation (double iFtyL, double iFtyLT, double iFcyL, double iFcyLT, double iFsu, double iFtuL, double iFtuLT, out double oFsy)
	Estimation of shear yield stress (Fsy) More...

unsafe NXOpen.CAE.AeroStructures.Author.ABB.Status	MetallicPanelCompressivePlasticityCurveBc1 (double x, double n, out double z)
	Metallic panel compressive plasticity curve BC1 Curves for finding critical buckling stress / secant yield stress F0. More...

unsafe NXOpen.CAE.AeroStructures.Author.ABB.Status	MetallicPanelCompressivePlasticityCurveBc2 (double x, double n, out double z)
	Metallic panel compressive plasticity curve BC2 Curves for finding critical inter-rivet buckling stress (or critical wrinkling stress) / secant yield stress F0. More...

unsafe NXOpen.CAE.AeroStructures.Author.ABB.Status	MetallicPanelCompressivePlasticityCurveBc3 (double x, double n, out double z)
	Metallic panel compressive plasticity curve BC3 Curves for finding critical buckling stress / secant yield stress F0. More...

unsafe NXOpen.CAE.AeroStructures.Author.ABB.Status	SecantModulus (double e, double n, double fy, double sigma, out double iEs)
	Secant modulus Computes the secant modulus from material properties and stress. More...

unsafe NXOpen.CAE.AeroStructures.Author.ABB.Status	StressFromStrainInPlasticDomain (double strain, double e, double iF02ys, double n, out double sigma)
	Compute stress from strain with the help of Ramberg-Osgood relationship More...

unsafe NXOpen.CAE.AeroStructures.Author.ABB.Status	StressF07 (double iFy, double e, double n, out double f07)
	Stress F0. More...

unsafe NXOpen.CAE.AeroStructures.Author.ABB.Status	TangentModulus (double e, double n, double iFy, double sigma, out double oEt)
	Computes the tangent modulus from material properties and stress. More...

unsafe NXOpen.CAE.AeroStructures.Author.ABB.Status	MsAllowable (double allowable, double[] value, out double[] ms)
	MS allowable. More...

unsafe NXOpen.CAE.AeroStructures.Author.ABB.Status	MsBearing (double iFbr, double d, double t, double factor, double[] iPy, double[] iPz, out double[] ms)
	MS bearing Computes margin of bearing More...

unsafe NXOpen.CAE.AeroStructures.Author.ABB.Status	MsBoltBending (double iMba, double b, double factor, double[] iPy, double[] iPz, out double[] ms)
	MS bolt bending Computes margin of safety of a bolt under bending load More...

unsafe NXOpen.CAE.AeroStructures.Author.ABB.Status	MsBoltCombinedShearTension (double iPTensileAllowable, double[] iPTensileX, double iPShearAllowable, double factor, double[] iPy, double[] iPz, out double[] ms)
	MS bolt combined shear tension Computes margin of safety of a bolt under shear load and tension load More...

unsafe NXOpen.CAE.AeroStructures.Author.ABB.Status	MsBoltCombinedShearTensionBending (double iPTensileAllowable, double[] iPTensileX, double iMAllowable, double b, double factorBend, double[] iPyBend, double[] iPzBend, double iPShearAllowable, double factorShear, double[] iPyShear, double[] iPzShear, out double[] ms)
	MS bolt combined shear tension bending Computes margin of safety of a bolt under shear, tension and bending load More...

unsafe NXOpen.CAE.AeroStructures.Author.ABB.Status	MsBoltShear (double iPShearAllowable, double factor, double[] iPy, double[] iPz, out double[] ms)
	MS bolt shear Computes margin of safety of a bolt under shear load More...

unsafe NXOpen.CAE.AeroStructures.Author.ABB.Status	MsNetSection (double sigmaAllowable, double d, double t, double b, double factor, double[] iPExtracted, out double[] ms)
	MS Net section Computes margin of net section (due to bolt hole) More...

unsafe NXOpen.CAE.AeroStructures.Author.ABB.Status	MsShearTearOut (double tauAllowable, double d, double t, double b, double factor, double[] iPExtracted, out double[] ms)
	MS Shear Tear Out Computes margin of shear tear out (due to bolt hole) More...

unsafe NXOpen.CAE.AeroStructures.Author.ABB.Status	MsTsaiHillPlaneStress (double matFcL, double matFcLT, double matFtL, double matFtLT, double matFS, double[] fl, double[] flt, double[] fs, out double[] ms)
	MS Tsai-Hill Computes margin of safety on the basis of Tsai-Hill failure theory (plane stresses hypothesis) More...

unsafe NXOpen.CAE.AeroStructures.Author.ABB.Status	MsTrescaPlaneStress (double fs, double[] fx, double[] fy, double[] fxy, out double[] ms)
	MS Tresca. More...

unsafe NXOpen.CAE.AeroStructures.Author.ABB.Status	MsMaterialStressAllowable (double allowable, double[] sigma, out double[] ms)
	MS material stress allowable. More...

unsafe NXOpen.CAE.AeroStructures.Author.ABB.Status	MsPlateBuckling (double e, double nu, double b, double t, double k, double eta, double[] sigma, out double[] ms)
	MS Plate Buckling Computes margin of safety of a metallic plate under buckling load (generic formula) More...

unsafe NXOpen.CAE.AeroStructures.Author.ABB.Status	MsPlateBucklingCurvedCompressive (double e, double nu, double n, double a, double b, double t, double r, NXOpen.CAE.AeroStructures.Author.ABB.MaterialBehaviour behaviour, double[] sigma, out double[] ms, out double sigmaAllowable)
	MS Plate Buckling Curved Compressive Computes margin of safety of a curved metallic rectangular panel under compressive load More...

unsafe NXOpen.CAE.AeroStructures.Author.ABB.Status	MsPlateBucklingCurvedShear (double e, double nu, double n, double a, double b, double t, NXOpen.CAE.AeroStructures.Author.ABB.EdgeSupportType bc, double r, NXOpen.CAE.AeroStructures.Author.ABB.MaterialBehaviour behaviour, double[] sigma, out double[] ms, out double sigmaAllowable)
	MS Plate Buckling Curved Shear Computes margin of safety of a curved metallic rectangular panel under shear load More...

unsafe NXOpen.CAE.AeroStructures.Author.ABB.Status	MsPlateBucklingCurvedLongitudinalShearCombined (double e, double nu, double n, double a, double b, double t, NXOpen.CAE.AeroStructures.Author.ABB.EdgeSupportType bc, double r, NXOpen.CAE.AeroStructures.Author.ABB.MaterialBehaviour behaviour, double[] sigma, double[] tau, out double[] ms, out double sigmacr, out double taucr)
	MS Plate Buckling Curved Longitudinal Shear Combined Computes margin of safety of a rectangular curved metallic panel in buckling under combined shear and longitudinal loads More...

unsafe NXOpen.CAE.AeroStructures.Author.ABB.Status	MsPlateBucklingFlatBending (double e, double nu, double n, double a, double b, double beta, double t, NXOpen.CAE.AeroStructures.Author.ABB.MaterialBehaviour behaviour, double[] sigma1, double[] sigma2, out double[] ms, out double[] sigmaAllowable)
	MS Plate Buckling Flat Bending Computes margin of safety of a flat metallic rectangular panel under bending load More...

unsafe NXOpen.CAE.AeroStructures.Author.ABB.Status	MsPlateBucklingFlatCompressive (double e, double nu, double n, double a, double b, double t, NXOpen.CAE.AeroStructures.Author.ABB.UnloadedEdgeSupportType bcUnloaded, NXOpen.CAE.AeroStructures.Author.ABB.EdgeSupportType bcLoaded, NXOpen.CAE.AeroStructures.Author.ABB.MaterialBehaviour behaviour, double[] sigma, out double[] ms, out double sigmaAllowable)
	MS Plate Buckling Flat Compressive Computes margin of safety of a flat metallic rectangular panel under compressive load More...

unsafe NXOpen.CAE.AeroStructures.Author.ABB.Status	MsPlateBucklingFlatShear (double e, double nu, double n, double a, double b, double t, NXOpen.CAE.AeroStructures.Author.ABB.EdgeSupportType bc, NXOpen.CAE.AeroStructures.Author.ABB.MaterialBehaviour behaviour, double[] sigma, out double[] ms, out double sigmaAllowable)
	MS Plate Buckling Flat Shear Computes margin of safety of a flat metallic rectangular panel under shear load More...

unsafe NXOpen.CAE.AeroStructures.Author.ABB.Status	MsPlateBucklingFlatLongitudinalBendingCombined (double e, double nu, double n, double a, double b, double t, NXOpen.CAE.AeroStructures.Author.ABB.UnloadedEdgeSupportType bcUnloaded, NXOpen.CAE.AeroStructures.Author.ABB.EdgeSupportType bcLoaded, NXOpen.CAE.AeroStructures.Author.ABB.MaterialBehaviour behaviour, double[] sigma1, double[] sigma2, out double[] ms, out double sigmacr, out double sigmabcr)
	MS Plate Buckling Flat Longitudinal Bending Combined Computes margin of safety of a rectangular flat metallic panel in buckling under combined bending and longitudinal loads More...

unsafe NXOpen.CAE.AeroStructures.Author.ABB.Status	MsPlateBucklingFlatLongitudinalShearCombined (double e, double nu, double n, double a, double b, double t, NXOpen.CAE.AeroStructures.Author.ABB.UnloadedEdgeSupportType bcUnloaded, NXOpen.CAE.AeroStructures.Author.ABB.EdgeSupportType bcLoaded, NXOpen.CAE.AeroStructures.Author.ABB.MaterialBehaviour behaviour, double[] sigma, double[] tau, out double[] ms, out double sigmacr, out double taucr)
	MS Plate Buckling Flat Longitudinal Shear Combined Computes margin of safety of a rectangular flat metallic panel in buckling under combined shear and longitudinal loads More...

unsafe NXOpen.CAE.AeroStructures.Author.ABB.Status	MsPlateBucklingFlatShearBendingCombined (double e, double nu, double n, double a, double b, double t, NXOpen.CAE.AeroStructures.Author.ABB.UnloadedEdgeSupportType bcUnloaded, NXOpen.CAE.AeroStructures.Author.ABB.EdgeSupportType bcLoaded, NXOpen.CAE.AeroStructures.Author.ABB.MaterialBehaviour behaviour, double[] sigma1, double[] sigma2, double[] tau, out double[] ms, out double sigmabcr, out double taucr)
	MS Plate Buckling Flat Shear Bending Combined Computes margin of safety of a rectangular flat metallic panel in buckling under combined bending and shear loads More...

Static Public Member Functions
static ABB	GetABB (NXOpen.Session owner)
	Returns the ABB object for the running session which serves as the 'gateway' class for the application API. More...

Properties
Tag	Tag `[get]`
	Returns the tag of this object. More...

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

Type of support along the edges, the choice is between SimplySupported and Clamped

Enumerator
SimplySupported	Simply supported
Clamped	Clamped

enum NXOpen.CAE.AeroStructures.Author.ABB.MaterialBehaviour

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

Enumerator
Elastic	Elastic behaviour
ElasticPlastic	Elastic-plastic behaviour

enum NXOpen.CAE.AeroStructures.Author.ABB.Status

ABB return status

Enumerator
Success	ABB computation success
Failed	ABB computation failed

enum NXOpen.CAE.AeroStructures.Author.ABB.UnloadedEdgeSupportType

Type of support along unloaded edges, the choices are: {Clamped-Clamped, Simply Supported-Clamped, Simply Supported-Simply Supported, Free-Clamped, Free-Simply Supported}

Enumerator
ClampedClamped	Clamped-Clamped
SimplySupportedClamped	Simply Supported-Clamped
SimplySupportedSimplySupported	Simply Supported-Simply Supported
FreeClamped	Free-Clamped
FreeSimplySupported	Free-Simply Supported

Member Function Documentation

unsafe NXOpen.CAE.AeroStructures.Author.ABB.Status NXOpen.CAE.AeroStructures.Author.ABB.CurvedMetallicPanelCompressiveBucklingCoefficient	(	double	b,
		double	t,
		double	r,
		double	nu,
		out 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 coefficient Output kc compressive-buckling coefficient Returns Status of the calculation

Created in NX12.0.0

License requirements: nx_masterfem ("Finite Element Modeling")

Parameters

b	Dimension in radial axis
t	Panel thickness
r	Panel radius
nu	Material Poisson coefficient
kc	Compressive-buckling coefficient

Returns

unsafe NXOpen.CAE.AeroStructures.Author.ABB.Status NXOpen.CAE.AeroStructures.Author.ABB.CurvedMetallicPanelShearBucklingCoefficient	(	double	a,
		double	b,
		double	t,
		double	r,
		double	nu,
		NXOpen.CAE.AeroStructures.Author.ABB.EdgeSupportType	bc,
		out double	ks
	)

Curves for finding 'ks' the shear-buckling coefficient for curved sheet panel

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 coefficient BC Type of 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: nx_masterfem ("Finite Element Modeling")

Parameters

a	Dimension in longitudinal axis
b	Dimension in radial axis
t	Thickness
r	Radius
nu	Poisson coefficient
bc	Type of support along the edges
ks	Compressive-buckling coefficient

Returns

unsafe NXOpen.CAE.AeroStructures.Author.ABB.Status NXOpen.CAE.AeroStructures.Author.ABB.EquivalentSectionProperties	(	double[]	n,
		double[]	iAi,
		double[]	iEi,
		double[]	iIxxi,
		out double[]	a,
		out double[]	e,
		out double[]	oYcog,
		out 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 Ycogi Center of gravity of sub-sections in Y direction Ei Young's modulus of sub-sections 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: nx_masterfem ("Finite Element Modeling")

Parameters

n	Number of sub-sections that compose the section
iAi	Areas of sub-sections
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)
e	Young's modulus of the equivalent section
oYcog	Center of gravity of the equivalent section in Y direction
oIxx	Moment of inertia of the equivalent section around XX (expressed at the center of gravity of the equivalent section)

Returns

unsafe NXOpen.CAE.AeroStructures.Author.ABB.Status NXOpen.CAE.AeroStructures.Author.ABB.ExtrudedMetallicSubSectionCripplingAllowable	(	double	iFcy,
		double	e,
		int	fe,
		double	b,
		double	t,
		out 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: nx_masterfem ("Finite Element Modeling")

Parameters

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

Returns

unsafe NXOpen.CAE.AeroStructures.Author.ABB.Status NXOpen.CAE.AeroStructures.Author.ABB.FlatMetallicPanelBendingBucklingCoefficient	(	double	aOverB,
		double	beta,
		out 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: nx_masterfem ("Finite Element Modeling")

Parameters

aOverB	Panel length ratio
beta	Loading length ratio
kb	Bending buckling stress coefficient

Returns

unsafe NXOpen.CAE.AeroStructures.Author.ABB.Status NXOpen.CAE.AeroStructures.Author.ABB.FlatMetallicPanelCompressiveBucklingCoefficient	(	double	a,
		double	b,
		NXOpen.CAE.AeroStructures.Author.ABB.UnloadedEdgeSupportType	bcUnloaded,
		NXOpen.CAE.AeroStructures.Author.ABB.EdgeSupportType	bcLoaded,
		out double	kc
	)

Curves for finding 'kc' the compressive-buckling coefficient for rectangular metallic flat plate

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 Type of support along unloaded edges {Clamped-Clamped, Simply Supported-Clamped, Simply Supported-Simply Supported, Free-Clamped, Free-Simply Supported} BC_Loaded Type of support along loaded edges {Clamped or Simply Supported} Output kc Compressive buckling coefficient Returns Computation status

Created in NX12.0.0

License requirements: nx_masterfem ("Finite Element Modeling")

Parameters

a	Unloaded edge length
b	Loaded edge length
bcUnloaded	Type of support along unloaded edges
bcLoaded	Type of support along loaded edges
kc	Compressive buckling coefficient

Returns

unsafe NXOpen.CAE.AeroStructures.Author.ABB.Status NXOpen.CAE.AeroStructures.Author.ABB.FlatMetallicPanelShearBucklingCoefficient	(	double	a,
		double	b,
		NXOpen.CAE.AeroStructures.Author.ABB.EdgeSupportType	bc,
		out double	ks
	)

Curves for finding 'ks' the shear-buckling coefficient for flat rectangular plate

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 Type of support along the edges {Simply Supported or Clamped} Output ks Shear-buckling coefficient Returns Computation status

Created in NX12.0.0

License requirements: nx_masterfem ("Finite Element Modeling")

Parameters

a	Longer plate dimension
b	Shorter plate dimension
bc	Type of support along the edges
ks	Shear-buckling coefficient

Returns

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.

unsafe double NXOpen.CAE.AeroStructures.Author.ABB.GetIntegerNa ( )

Integer NA value

Created in NX12.0.0

License requirements: nx_masterfem ("Finite Element Modeling")

Returns

unsafe double NXOpen.CAE.AeroStructures.Author.ABB.GetMsThreshold ( )

The MS (margin of safety) threshold

Created in NX12.0.0

License requirements: nx_masterfem ("Finite Element Modeling")

Returns

unsafe double NXOpen.CAE.AeroStructures.Author.ABB.GetPi ( )

PI number

Created in NX12.0.0

License requirements: nx_masterfem ("Finite Element Modeling")

Returns

unsafe double NXOpen.CAE.AeroStructures.Author.ABB.GetRealEpsilon ( )

Real epsilon

Created in NX12.0.0

License requirements: nx_masterfem ("Finite Element Modeling")

Returns

unsafe double NXOpen.CAE.AeroStructures.Author.ABB.GetRealMax ( )

Maximum real number

Created in NX12.0.0

License requirements: nx_masterfem ("Finite Element Modeling")

Returns

unsafe double NXOpen.CAE.AeroStructures.Author.ABB.GetRealNa ( )

Real NA

Created in NX12.0.0

License requirements: nx_masterfem ("Finite Element Modeling")

Returns

unsafe double NXOpen.CAE.AeroStructures.Author.ABB.GetRealNegativeInfinity ( )

The negative infinity value

Created in NX12.0.0

License requirements: nx_masterfem ("Finite Element Modeling")

Returns

unsafe double NXOpen.CAE.AeroStructures.Author.ABB.GetRealPositiveInfinity ( )

The positive infinity value

Created in NX12.0.0

License requirements: nx_masterfem ("Finite Element Modeling")

Returns

unsafe double NXOpen.CAE.AeroStructures.Author.ABB.GetUltimateLimitFactor ( )

Ultimate limit factor from the customer default

Created in NX12.0.0

License requirements: nx_masterfem ("Finite Element Modeling")

Returns

unsafe bool NXOpen.CAE.AeroStructures.Author.ABB.IsRealNa ( double value )

Tests if a value is NA

Created in NX12.0.0

License requirements: nx_masterfem ("Finite Element Modeling")

Parameters

value

Returns

unsafe bool NXOpen.CAE.AeroStructures.Author.ABB.IsRealNegativeInfinity ( double value )

Tests if a value equals negative infinity

Created in NX12.0.0

License requirements: nx_masterfem ("Finite Element Modeling")

Parameters

value

Returns

unsafe bool NXOpen.CAE.AeroStructures.Author.ABB.IsRealPositiveInfinity ( double value )

Tests if a value equals positive infinity

Created in NX12.0.0

License requirements: nx_masterfem ("Finite Element Modeling")

Parameters

value

Returns

unsafe NXOpen.CAE.AeroStructures.Author.ABB.Status NXOpen.CAE.AeroStructures.Author.ABB.LoadDistributionBoltsConcentricLoads	(	double[]	p,
		double[]	iPsn,
		int	nblcXnbbolt,
		out 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: nx_masterfem ("Finite Element Modeling")

Parameters

p	Load acting on fitting (nblc)
iPsn	Allowable shear strength of bolt (nbbolt)
nblcXnbbolt
oPn	Shear load on bolt (nblc x nbbolt)

Returns

unsafe NXOpen.CAE.AeroStructures.Author.ABB.Status NXOpen.CAE.AeroStructures.Author.ABB.MaterialFsyEstimation	(	double	iFtyL,
		double	iFtyLT,
		double	iFcyL,
		double	iFcyLT,
		double	iFsu,
		double	iFtuL,
		double	iFtuLT,
		out 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: nx_masterfem ("Finite Element Modeling")

Parameters

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

Returns

unsafe NXOpen.CAE.AeroStructures.Author.ABB.Status NXOpen.CAE.AeroStructures.Author.ABB.MetallicPanelCompressivePlasticityCurveBc1	(	double	x,
		double	n,
		out 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 modulus] * 'kc' is the buckling coefficient, computed in Figure FlatMetallicPanelCompressiveBucklingCoefficient * 'E' is the Young's modulus * 'nu' is the Poisson coefficient * '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: nx_masterfem ("Finite Element Modeling")

Parameters

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

Returns

unsafe NXOpen.CAE.AeroStructures.Author.ABB.Status NXOpen.CAE.AeroStructures.Author.ABB.MetallicPanelCompressivePlasticityCurveBc2	(	double	x,
		double	n,
		out double	z
	)

Metallic panel compressive plasticity curve BC2 Curves for finding critical inter-rivet buckling stress (or critical wrinkling stress) / secant yield stress F0.

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 modulus] * 'C' is the end fixity coefficient * 'E' is the Young's modulus * 'nu' is the Poisson coefficient * '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: nx_masterfem ("Finite Element Modeling")

Parameters

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

Returns

unsafe NXOpen.CAE.AeroStructures.Author.ABB.Status NXOpen.CAE.AeroStructures.Author.ABB.MetallicPanelCompressivePlasticityCurveBc3	(	double	x,
		double	n,
		out 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 coefficient * '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: nx_masterfem ("Finite Element Modeling")

Parameters

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

Returns

unsafe NXOpen.CAE.AeroStructures.Author.ABB.Status NXOpen.CAE.AeroStructures.Author.ABB.MsAllowable	(	double	allowable,
		double[]	value,
		out 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: nx_masterfem ("Finite Element Modeling")

Parameters

allowable	Manual input
value	Value coming from load extractor
ms	Margin of safety

Returns

unsafe NXOpen.CAE.AeroStructures.Author.ABB.Status NXOpen.CAE.AeroStructures.Author.ABB.MsBearing	(	double	iFbr,
		double	d,
		double	t,
		double	factor,
		double[]	iPy,
		double[]	iPz,
		out 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 d iameter '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 Fbr Bearing stress allowable D Diameter t Thickness Factor 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: nx_masterfem ("Finite Element Modeling")

Parameters

iFbr	Bearing stress allowable
d	Diameter
t	Thickness
factor	Load factor
iPy	Shear load Y direction
iPz	Shear load Z direction
ms	Margin of safety

Returns

unsafe NXOpen.CAE.AeroStructures.Author.ABB.Status NXOpen.CAE.AeroStructures.Author.ABB.MsBoltBending	(	double	iMba,
		double	b,
		double	factor,
		double[]	iPy,
		double[]	iPz,
		out 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 Mba Bending moment allowable of bolt b Arm Factor 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: nx_masterfem ("Finite Element Modeling")

Parameters

iMba	Bending moment allowable of bolt
b	Arm
factor	Load factor
iPy	Shear load Y direction
iPz	Shear load Z direction
ms	Margin of safety

Returns

unsafe NXOpen.CAE.AeroStructures.Author.ABB.Status NXOpen.CAE.AeroStructures.Author.ABB.MsBoltCombinedShearTension	(	double	iPTensileAllowable,
		double[]	iPTensileX,
		double	iPShearAllowable,
		double	factor,
		double[]	iPy,
		double[]	iPz,
		out 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 PTensileAllowable Tensile load allowable PTensileX(nblc) Tensile load PShearAllowable Single shear load allowable Factor Load factor Py(nblc) Shear load Y direction Pz(nblc) Shear load Z direction Output MS Margin of safety Return Status of the calculation

Created in NX12.0.0

License requirements: nx_masterfem ("Finite Element Modeling")

Parameters

iPTensileAllowable	Tensile load allowable
iPTensileX	Tensile load
iPShearAllowable	Single shear load allowable
factor	Load factor
iPy	Shear load Y direction
iPz	Shear load Z direction
ms	Margin of safety

Returns

unsafe NXOpen.CAE.AeroStructures.Author.ABB.Status NXOpen.CAE.AeroStructures.Author.ABB.MsBoltCombinedShearTensionBending	(	double	iPTensileAllowable,
		double[]	iPTensileX,
		double	iMAllowable,
		double	b,
		double	factorBend,
		double[]	iPyBend,
		double[]	iPzBend,
		double	iPShearAllowable,
		double	factorShear,
		double[]	iPyShear,
		double[]	iPzShear,
		out 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 PTensileAllowable Tensile load allowable PTensileX(nblc) Tensile load

MAllowable Bending moment allowable of bolt b Arm FactorBend Load factor for bending PyBend(nblc) Bending load Y direction PzBend(nblc) Bending load Z direction

PShearAllowable Single shear load allowable FactorShear Load factor for shear PyShear(nblc) Shear load Y direction PzShear(nblc) Shear load Z direction Output MS Margin of safety Return Status of the calculation

Created in NX12.0.0

License requirements: nx_masterfem ("Finite Element Modeling")

Parameters

iPTensileAllowable	Tensile load allowable
iPTensileX	Tensile load
iMAllowable	Bending moment allowable of bolt
b	Arm
factorBend	Bending load factor
iPyBend	Bending load Y direction
iPzBend	Bending load Z direction
iPShearAllowable	Single shear load allowable
factorShear	Shear load factor
iPyShear	Shear load Y direction
iPzShear	Shear load Z direction
ms	Margin of safety

Returns

unsafe NXOpen.CAE.AeroStructures.Author.ABB.Status NXOpen.CAE.AeroStructures.Author.ABB.MsBoltShear	(	double	iPShearAllowable,
		double	factor,
		double[]	iPy,
		double[]	iPz,
		out 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 PShearAllowable Single shear load allowable Factor Load factor Py(nblc) Shear load Y direction Pz(nblc) Shear load Z direction Output MS Margin of safety Return Status of the calculation

Created in NX12.0.0

License requirements: nx_masterfem ("Finite Element Modeling")

Parameters

iPShearAllowable	Single shear load allowable
factor	Shear load factor
iPy	Shear load Y direction
iPz	Shear load Z direction
ms	Margin of safety

Returns

unsafe NXOpen.CAE.AeroStructures.Author.ABB.Status NXOpen.CAE.AeroStructures.Author.ABB.MsMaterialStressAllowable	(	double	allowable,
		double[]	sigma,
		out double[]	ms
	)

MS material stress allowable.

Computes margin of safety based on a material allowable

The formula is MS = StressAllowable / Stress - 1

where: * 'Allowable' is the material stress allowable * 'Stress' is the stress * 'MS' is the margin of safety

Input Allowable Material stress allowable sigma(nblc) Stress Output MS Margin of safety Return Status of the calculation

Created in NX12.0.0

License requirements: nx_masterfem ("Finite Element Modeling")

Parameters

allowable	Material stress allowable
sigma	Stress
ms	Margin of safety

Returns

unsafe NXOpen.CAE.AeroStructures.Author.ABB.Status NXOpen.CAE.AeroStructures.Author.ABB.MsNetSection	(	double	sigmaAllowable,
		double	d,
		double	t,
		double	b,
		double	factor,
		double[]	iPExtracted,
		out 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 SigmaAllowable Material stress allowable D Diameter t Thickness b Width Factor Load factor PExtracted(nblc) Axial load (extracted) Output MS Margin of safety Return Status of the calculation

Created in NX12.0.0

License requirements: nx_masterfem ("Finite Element Modeling")

Parameters

sigmaAllowable	Material stress allowable
d	Diameter
t	Thickness
b	Width
factor	Load factor
iPExtracted	Axial load (extracted)
ms	Margin of safety

Returns

unsafe NXOpen.CAE.AeroStructures.Author.ABB.Status NXOpen.CAE.AeroStructures.Author.ABB.MsPlateBuckling	(	double	e,
		double	nu,
		double	b,
		double	t,
		double	k,
		double	eta,
		double[]	sigma,
		out 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 modulus * 'nu' is the elastic Poisson coefficient * 't' is the panel thickness * 'b' is the panel dimension * 'eta' is the plasticity reduction factor: SigmaAllowablePlastic = eta*SigmaAllowableElastic

Input E Young modulus nu Elastic Poisson coefficient b Panel dimension t Panel thickness k Buckling coefficient eta Plasticity reduction factor nblc Number of load cases sigma Stress coming from load extraction Output MS Margin of safety Return Status of the calculation

Created in NX12.0.0

License requirements: nx_masterfem ("Finite Element Modeling")

Parameters

e	Young's modulus
nu	Elastic Poisson coefficient
b	Panel dimension
t	Panel thickness
k	Buckling coefficient
eta	Plasticity reduction factor
sigma	Stress coming from load extraction
ms	Margin of safety

Returns

unsafe NXOpen.CAE.AeroStructures.Author.ABB.Status NXOpen.CAE.AeroStructures.Author.ABB.MsPlateBucklingCurvedCompressive	(	double	e,
		double	nu,
		double	n,
		double	a,
		double	b,
		double	t,
		double	r,
		NXOpen.CAE.AeroStructures.Author.ABB.MaterialBehaviour	behaviour,
		double[]	sigma,
		out double[]	ms,
		out double	sigmaAllowable
	)

MS Plate Buckling Curved Compressive Computes margin of safety of a curved metallic rectangular panel under compressive load

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 modulus * 'nu' is the elastic Poisson coefficient * '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 modulus Input E Young modulus nu Elastic Poisson coefficient n Ramberg-Osgood parameter a Unloaded edge length b Loaded edge length t Panel thickness r Panel radius of curvature behaviour Material behaviour nblc Number of load cases sigma Stress coming from load extraction Output sigmaAllowable Stress allowable MS Margin of safety Return Status of the calculation

Created in NX12.0.0

License requirements: nx_masterfem ("Finite Element Modeling")

Parameters

e	Young's modulus
nu	Elastic Poisson coefficient
n	Ramberg-Osgood parameter
a	Unloaded edge length
b	Loaded edge length
t	Panel thickness
r	Panel radius of curvature
behaviour	Material behaviour
sigma	Stress coming from load extraction
ms	Margin of safety
sigmaAllowable	Stress allowable

Returns

unsafe NXOpen.CAE.AeroStructures.Author.ABB.Status NXOpen.CAE.AeroStructures.Author.ABB.MsPlateBucklingCurvedLongitudinalShearCombined	(	double	e,
		double	nu,
		double	n,
		double	a,
		double	b,
		double	t,
		NXOpen.CAE.AeroStructures.Author.ABB.EdgeSupportType	bc,
		double	r,
		NXOpen.CAE.AeroStructures.Author.ABB.MaterialBehaviour	behaviour,
		double[]	sigma,
		double[]	tau,
		out double[]	ms,
		out double	sigmacr,
		out double	taucr
	)

MS Plate Buckling Curved Longitudinal Shear Combined Computes margin of safety of a rectangular curved metallic panel in buckling under combined shear and longitudinal loads

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 E Young modulus nu Elastic Poisson coefficient n Ramberg-Osgood parameter a Unloaded edge length b Loaded edge length t Panel thickness BC Type of support along edges ('Clamped' or 'Simply Supported') r Panel radius of curvature behaviour Material behaviour ('Elastic' or 'Elastic-Plastic') nblc Number of load cases sigma Stress XX coming from load extraction tau Stress YY coming from load extraction 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: nx_masterfem ("Finite Element Modeling")

Parameters

e	Young's modulus
nu	Elastic Poisson coefficient
n	Ramberg-Osgood parameter
a	Unloaded edge length
b	Loaded edge length
t	Panel thickness
bc	Type of support along the edges
r	Panel radius of curvature
behaviour	Material behaviour
sigma	Stress XX coming from load extraction
tau	Stress YY coming from load extraction
ms	Margin of safety
sigmacr	Compressive stress allowable
taucr	Shear stress allowable

Returns

unsafe NXOpen.CAE.AeroStructures.Author.ABB.Status NXOpen.CAE.AeroStructures.Author.ABB.MsPlateBucklingCurvedShear	(	double	e,
		double	nu,
		double	n,
		double	a,
		double	b,
		double	t,
		NXOpen.CAE.AeroStructures.Author.ABB.EdgeSupportType	bc,
		double	r,
		NXOpen.CAE.AeroStructures.Author.ABB.MaterialBehaviour	behaviour,
		double[]	sigma,
		out double[]	ms,
		out 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 modulus * 'nu' is the elastic Poisson coefficient * '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 modulus

Input E Young modulus nu Elastic Poisson coefficient n Ramberg-Osgood parameter a Longer panel dimension b Shorter panel dimension t Panel thickness BC Type of support along edges r Panel radius of curvature behaviour Material behaviour nblc Number of load cases sigma Stress coming from load extraction Output sigmaAllowable Stress allowable MS Margin of safety Return Status of the calculation

Created in NX12.0.0

License requirements: nx_masterfem ("Finite Element Modeling")

Parameters

e	Young's modulus
nu	Elastic Poisson coefficient
n	Ramberg-Osgood parameter
a	Longer panel dimension
b	Shorter panel dimension
t	Panel thickness
bc	Type of support along the edges
r	Panel radius of curvature
behaviour	Material behaviour
sigma	Stress coming from load extraction
ms	Margin of safety
sigmaAllowable	Stress allowable

Returns

unsafe NXOpen.CAE.AeroStructures.Author.ABB.Status NXOpen.CAE.AeroStructures.Author.ABB.MsPlateBucklingFlatBending	(	double	e,
		double	nu,
		double	n,
		double	a,
		double	b,
		double	beta,
		double	t,
		NXOpen.CAE.AeroStructures.Author.ABB.MaterialBehaviour	behaviour,
		double[]	sigma1,
		double[]	sigma2,
		out double[]	ms,
		out double[]	sigmaAllowable
	)

MS Plate Buckling Flat Bending Computes margin of safety of a flat metallic rectangular panel under bending load

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 coefficient * '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 modulus Input E Young's modulus nu Elastic Poisson coefficient n Ramberg-Osgood parameter a Unloaded edge length b Loaded edge length beta Loading length ratio. If not specified (beta = NA), beta is computed t Panel thickness behaviour Material behaviour nblc Number of load cases sigma1 Stress XX Side1 sigma2 Stress XX Side2 Output sigmaAllowable Stress allowable MS Margin of safety Return Status of the calculation

Created in NX12.0.0

License requirements: nx_masterfem ("Finite Element Modeling")

Parameters

e	Young's modulus
nu	Elastic Poisson coefficient
n	Ramberg-Osgood parameter
a	Unloaded edge length
b	Loaded edge length
beta	Loading length ratio
t	Panel thickness
behaviour	Material behaviour
sigma1	Stress XX Side1
sigma2	Stress XX Side2
ms	Margin of safety
sigmaAllowable	Stress allowables

Returns

unsafe NXOpen.CAE.AeroStructures.Author.ABB.Status NXOpen.CAE.AeroStructures.Author.ABB.MsPlateBucklingFlatCompressive	(	double	e,
		double	nu,
		double	n,
		double	a,
		double	b,
		double	t,
		NXOpen.CAE.AeroStructures.Author.ABB.UnloadedEdgeSupportType	bcUnloaded,
		NXOpen.CAE.AeroStructures.Author.ABB.EdgeSupportType	bcLoaded,
		NXOpen.CAE.AeroStructures.Author.ABB.MaterialBehaviour	behaviour,
		double[]	sigma,
		out double[]	ms,
		out double	sigmaAllowable
	)

MS Plate Buckling Flat Compressive Computes margin of safety of a flat metallic rectangular panel under compressive load

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 coefficient * '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 E Young's modulus nu Elastic Poisson coefficient n Ramberg-Osgood parameter a Unloaded edge length b Loaded edge length t Panel thickness BC_Unloaded Type of support along unloaded edges {'Clamped-Clamped';'Simply Supported-Clamped';'Simply Supported-Simply Supported';'Free-Clamped';'Free-Simply Supported'} BC_Loaded Type of support along loaded edges {'Clamped';'Simply Supported'} behaviour Material behaviour nblc Number of load cases sigma Stress coming from load extractor Output sigmaAllowable Stress allowable MS Margin of safety Return Status of the calculation

Created in NX12.0.0

License requirements: nx_masterfem ("Finite Element Modeling")

Parameters

e	Young's modulus
nu	Elastic Poisson coefficient
n	Ramberg-Osgood parameter
a	Unloaded edge length
b	Loaded edge length
t	Panel thickness
bcUnloaded	Type of support along unloaded edges
bcLoaded	Type of support along loaded edges
behaviour	Material behaviour
sigma	Stress coming from load extractor
ms	Margin of safety
sigmaAllowable	Stress allowable

Returns

unsafe NXOpen.CAE.AeroStructures.Author.ABB.Status NXOpen.CAE.AeroStructures.Author.ABB.MsPlateBucklingFlatLongitudinalBendingCombined	(	double	e,
		double	nu,
		double	n,
		double	a,
		double	b,
		double	t,
		NXOpen.CAE.AeroStructures.Author.ABB.UnloadedEdgeSupportType	bcUnloaded,
		NXOpen.CAE.AeroStructures.Author.ABB.EdgeSupportType	bcLoaded,
		NXOpen.CAE.AeroStructures.Author.ABB.MaterialBehaviour	behaviour,
		double[]	sigma1,
		double[]	sigma2,
		out double[]	ms,
		out double	sigmacr,
		out double	sigmabcr
	)

MS Plate Buckling Flat Longitudinal Bending Combined Computes margin of safety of a rectangular flat metallic panel in buckling under combined bending and longitudinal loads

This formula is derived from the interaction equation Rb ^ 1.75 + Rc = 1.0

where: * Rc = sigmac / sigmacr is the stress ratio due to compression stress, with: * sigmac is the given longitudinal stress * sigmacr is the compression stress allowable for buckling

* Rb = sigmab / sigmabcr is the stress ratio due to bending stress with * sigmab is the given compressive stress due to bending * sigmabcr is the bending stress allowable for buckling

Input E Young's modulus nu Elastic Poisson coefficient n Ramberg-Osgood parameter a Unloaded edge length b Loaded edge length beta Loading length ratio t Panel thickness BC_Unloaded Type of support along unloaded edges {'Clamped-Clamped';'Simply Supported-Clamped';'Simply Supported-Simply Supported';'Free-Clamped';'Free-Simply Supported'} BC_Loaded Type of support along loaded edges {'Clamped';'Simply Supported'} behaviour Material behaviour nblc Number of load cases sigma1 Stress XX Side1 sigma2 Stress XX Side2 Output sigmacr Compressive stress allowable sigmabcr Bending stress allowable MS Margin of safety Return Status of the calculation

Created in NX12.0.0

License requirements: nx_masterfem ("Finite Element Modeling")

Parameters

e	Young's modulus
nu	Elastic Poisson coefficient
n	Ramberg-Osgood parameter
a	Unloaded edge length
b	Loaded edge length
t	Panel thickness
bcUnloaded	Type of support along unloaded edges
bcLoaded	Type of support along loaded edges
behaviour	Material behaviour
sigma1	Stress XX Side1
sigma2	Stress XX Side2
ms	Margin of safety
sigmacr	Compressive stress allowable
sigmabcr	Bending stress allowable

Returns

unsafe NXOpen.CAE.AeroStructures.Author.ABB.Status NXOpen.CAE.AeroStructures.Author.ABB.MsPlateBucklingFlatLongitudinalShearCombined	(	double	e,
		double	nu,
		double	n,
		double	a,
		double	b,
		double	t,
		NXOpen.CAE.AeroStructures.Author.ABB.UnloadedEdgeSupportType	bcUnloaded,
		NXOpen.CAE.AeroStructures.Author.ABB.EdgeSupportType	bcLoaded,
		NXOpen.CAE.AeroStructures.Author.ABB.MaterialBehaviour	behaviour,
		double[]	sigma,
		double[]	tau,
		out double[]	ms,
		out double	sigmacr,
		out double	taucr
	)

MS Plate Buckling Flat Longitudinal Shear Combined Computes margin of safety of a rectangular flat metallic panel in buckling under combined shear and longitudinal loads

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 E Young's modulus nu Elastic Poisson coefficient n Ramberg-Osgood parameter a Unloaded edge length b Loaded edge length t Panel thickness BC_Unloaded Type of support along unloaded edges {'Clamped-Clamped';'Simply Supported-Clamped';'Simply Supported-Simply Supported';'Free-Clamped';'Free-Simply Supported'} BC_Loaded Type of support along loaded edges {'Clamped';'Simply Supported'} behaviour Material behaviour {'Elastic'; 'Elastic-Plastic'} nblc Number of load cases sigma Stress XX tau Stress XY 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: nx_masterfem ("Finite Element Modeling")

Parameters

e	Young's modulus
nu	Elastic Poisson coefficient
n	Ramberg-Osgood parameter
a	Unloaded edge length
b	Loaded edge length
t	Panel thickness
bcUnloaded	Type of support along unloaded edges
bcLoaded	Type of support along loaded edges
behaviour	Material behaviour
sigma	Stress XX
tau	Stress XY
ms	Margin of safety
sigmacr	Compressive stress allowable
taucr	Shear stress allowable

Returns

unsafe NXOpen.CAE.AeroStructures.Author.ABB.Status NXOpen.CAE.AeroStructures.Author.ABB.MsPlateBucklingFlatShear	(	double	e,
		double	nu,
		double	n,
		double	a,
		double	b,
		double	t,
		NXOpen.CAE.AeroStructures.Author.ABB.EdgeSupportType	bc,
		NXOpen.CAE.AeroStructures.Author.ABB.MaterialBehaviour	behaviour,
		double[]	sigma,
		out double[]	ms,
		out 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 coefficient * 't' is the panel thickness * 'a' is the panel longer dimension * 'b' is panel shorter dimension * '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 E Young's modulus nu Elastic Poisson coefficient n Ramberg-Osgood parameter a Panel longer dimension b Panel shorter dimension t Panel thickness BC Type of support along the edges {'Clamped';'Simply Supported'} behaviour Material behaviour nblc Number of load cases sigma Stress coming from load extractor Output sigmaAllowable Stress allowable MS Margin of safety Return Status of the calculation

Created in NX12.0.0

License requirements: nx_masterfem ("Finite Element Modeling")

Parameters

e	Young's modulus
nu	Elastic Poisson coefficient
n	Ramberg-Osgood parameter
a	Unloaded edge length
b	Loaded edge length
t	Panel thickness
bc	Type of support along the edges
behaviour	Material behaviour
sigma	Stress coming from load extractor
ms	Margin of safety
sigmaAllowable	Stress allowable

Returns

unsafe NXOpen.CAE.AeroStructures.Author.ABB.Status NXOpen.CAE.AeroStructures.Author.ABB.MsPlateBucklingFlatShearBendingCombined	(	double	e,
		double	nu,
		double	n,
		double	a,
		double	b,
		double	t,
		NXOpen.CAE.AeroStructures.Author.ABB.UnloadedEdgeSupportType	bcUnloaded,
		NXOpen.CAE.AeroStructures.Author.ABB.EdgeSupportType	bcLoaded,
		NXOpen.CAE.AeroStructures.Author.ABB.MaterialBehaviour	behaviour,
		double[]	sigma1,
		double[]	sigma2,
		double[]	tau,
		out double[]	ms,
		out double	sigmabcr,
		out double	taucr
	)

MS Plate Buckling Flat Shear Bending Combined Computes margin of safety of a rectangular flat metallic panel in buckling under combined bending and shear loads

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 E Young's modulus nu Elastic Poisson coefficient n Ramberg-Osgood parameter a Unloaded edge length b Loaded edge length t Panel thickness BC_Unloaded Type of support along unloaded edges {'Clamped-Clamped';'Simply Supported-Clamped';'Simply Supported-Simply Supported';'Free-Clamped';'Free-Simply Supported'} BC_Loaded Type of support along loaded edges {'Clamped';'Simply Supported'} behaviour Material behaviour {'Elastic'; 'Elastic-Plastic'} nblc Number of load cases sigma1 Stress XX Side1 sigma2 Stress XX Side2 tau Stress XY 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: nx_masterfem ("Finite Element Modeling")

Parameters

e	Young's modulus
nu	Elastic Poisson coefficient
n	Ramberg-Osgood parameter
a	Unloaded edge length
b	Loaded edge length
t	Panel thickness
bcUnloaded	Type of support along unloaded edges
bcLoaded	Type of support along loaded edges
behaviour	Material behaviour
sigma1	Stress XX Side 1
sigma2	Stress XX Side 2
tau	Stress XY
ms	Margin of safety
sigmabcr	Bending stress allowable
taucr	Shear stress allowable

Returns

unsafe NXOpen.CAE.AeroStructures.Author.ABB.Status NXOpen.CAE.AeroStructures.Author.ABB.MsShearTearOut	(	double	tauAllowable,
		double	d,
		double	t,
		double	b,
		double	factor,
		double[]	iPExtracted,
		out 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 tauAllowable Material shear stress allowable D Diameter t Thickness b Edge distance Factor Load factor nblc Number of loadcases PExtracted(nblc) Axial load (extracted) Output MS Margin of safety Return Status of the calculation

Created in NX12.0.0

License requirements: nx_masterfem ("Finite Element Modeling")

Parameters

tauAllowable	Material shear stress allowable
d	Diameter
t	Thickness
b	Edge distance
factor	Load factor
iPExtracted	Axial load (extracted)
ms	Margin of safety

Returns

unsafe NXOpen.CAE.AeroStructures.Author.ABB.Status NXOpen.CAE.AeroStructures.Author.ABB.MsTrescaPlaneStress	(	double	fs,
		double[]	fx,
		double[]	fy,
		double[]	fxy,
		out 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) <= (FS)/2' where * 'S1', 'S2' and 'S3' are the principal stresses. * 'FS' is the material shear strength allowable

A margin of safety can be derived from this formulation: 'MS = (FS) / (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 FS Material shear strength allowable nblc Number of load cases FX Normal stress in the X direction FY Normal stress in the Z direction FXY Shear stress Output MS Margin of safety Return Status of the calculation

Created in NX12.0.0

License requirements: nx_masterfem ("Finite Element Modeling")

Parameters

fs	Material shear strength allowable
fx	Normal stress in the X direction
fy	Normal stress in the Z direction
fxy	Shear stress
ms	Margin of safety

Returns

unsafe NXOpen.CAE.AeroStructures.Author.ABB.Status NXOpen.CAE.AeroStructures.Author.ABB.MsTsaiHillPlaneStress	(	double	matFcL,
		double	matFcLT,
		double	matFtL,
		double	matFtLT,
		double	matFS,
		double[]	fl,
		double[]	flt,
		double[]	fs,
		out double[]	ms
	)

MS Tsai-Hill Computes margin of safety on the basis of Tsai-Hill failure theory (plane stresses hypothesis)

The formula based on yield material allowables is 'MS=1-sqrt(((F_L)/FtcyL)^2+(FLT/FtcyLT)^2-((F_LF_(LT))/(FtcyLFtcyL))+(F_(S)/Fsy)^2)' where: * L and LT are material directions: 'Longitudinal' and 'Longitudinal' 'Transverse'. * 'F_L','FLT' and 'FS' are plane stresses. They are expressed under material direction (with 'S' for shear). * 'F(tc)yL', 'F(tc)yLT' and 'Fsy' are yield material stress allowables. 'tc' is for 'tensile' or 'compressive' properties. Choices are done depending on the type of the corresponding stresses ('F_L' and 'FLT').

The formula can also be based on failure material allowables. The formula is 'MS = 1 - sqrt ( (FL / F(tc)uL ) ^ 2 + ( FLT / F(tc)uLT ) ^ 2 - ( (FL * FLT) / ( F(tc)uL * F(tc)uL) ) + ( FS / Fsu ) ^ 2 )'

where: * 'F(tc)uL','F(tc)uLT' and 'Fsu' are ultimate material stress allowables.

Input Mat_FcL Material compressive stress, longitudinal direction Mat_FcLT Material compressive stress, long transverse direction Mat_FtL Material tensile stress, longitudinal direction Mat_FtLT Material tensile stress, long transverse direction Mat_FS Material shear stress nblc Number of load cases FL Stress(es), longitudinal direction FLT Stress(es), longitudinal transverse direction FS Shear stress(es) Output MS Margin of safety Return Status of the calculation

Created in NX12.0.0

License requirements: nx_masterfem ("Finite Element Modeling")

Parameters

matFcL	Material compressive allowable, longitudinal direction
matFcLT	Material compressive allowable, long transverse direction
matFtL	Material tensile allowable, longitudinal direction
matFtLT	Material tensile allowable, long transverse direction
matFS	Material shear allowable
fl	Stresses, longitudinal direction
flt	Stresses, longitudinal transverse direction
fs	Shear stresses
ms	Margin of safety

Returns

unsafe NXOpen.CAE.AeroStructures.Author.ABB.Status NXOpen.CAE.AeroStructures.Author.ABB.SecantModulus	(	double	e,
		double	n,
		double	fy,
		double	sigma,
		out 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: nx_masterfem ("Finite Element Modeling")

Parameters

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

Returns

unsafe NXOpen.CAE.AeroStructures.Author.ABB.Status NXOpen.CAE.AeroStructures.Author.ABB.StressF07	(	double	iFy,
		double	e,
		double	n,
		out 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 Fy 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: nx_masterfem ("Finite Element Modeling")

Parameters

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

Returns

unsafe NXOpen.CAE.AeroStructures.Author.ABB.Status NXOpen.CAE.AeroStructures.Author.ABB.StressFromStrainInPlasticDomain	(	double	strain,
		double	e,
		double	iF02ys,
		double	n,
		out 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: nx_masterfem ("Finite Element Modeling")

Parameters

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

Returns

unsafe NXOpen.CAE.AeroStructures.Author.ABB.Status NXOpen.CAE.AeroStructures.Author.ABB.TangentModulus	(	double	e,
		double	n,
		double	iFy,
		double	sigma,
		out 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 Fy Yield stress sigma Stress Output Et Tangent modulus

Created in NX12.0.0

License requirements: nx_masterfem ("Finite Element Modeling")

Parameters

e	Young's modulus
n	Ramberg-Osgood parameter
iFy	Yield stress
sigma	Stress
oEt	Tangent modulus

Returns

Property Documentation

Tag NXOpen.CAE.AeroStructures.Author.ABB.Tag

get

Returns the tag of this object.

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

dotnet_pool/CAE_AeroStructures_Author_ABB.cs

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