NX Open C++ Reference Guide
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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 } |
Type of 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 | Status { StatusSuccess, StatusFailed } |
ABB return status. More... | |
enum | UnloadedEdgeSupportType { UnloadedEdgeSupportTypeClampedClamped, UnloadedEdgeSupportTypeSimplySupportedClamped, UnloadedEdgeSupportTypeSimplySupportedSimplySupported, UnloadedEdgeSupportTypeFreeClamped, UnloadedEdgeSupportTypeFreeSimplySupported } |
Type of 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 (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 (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 (const std::vector< double > &n, const std::vector< double > &iAi, const std::vector< double > &iEi, const std::vector< double > &iIxxi, std::vector< double > &a, std::vector< double > &e, std::vector< double > &oYcog, 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 (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 (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 (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 (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... | |
double | 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 (const std::vector< double > &p, const std::vector< double > &iPsn, int nblcXnbbolt, std::vector< double > &oPn) |
Computes bolt loads for multiple bolt fitting - Concentric load. More... | |
NXOpen::CAE::AeroStructures::Author::ABB::Status | MaterialFsyEstimation (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 (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 (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 (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 (double allowable, const std::vector< double > &value, std::vector< double > &ms) |
MS allowable. More... | |
NXOpen::CAE::AeroStructures::Author::ABB::Status | MsBearing (double iFbr, double d, double t, double factor, const std::vector< double > &iPy, const std::vector< double > &iPz, std::vector< double > &ms) |
MS bearing Computes margin of bearing. More... | |
NXOpen::CAE::AeroStructures::Author::ABB::Status | MsBoltBending (double iMba, double b, double factor, const std::vector< double > &iPy, const std::vector< double > &iPz, 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 (double iPTensileAllowable, const std::vector< double > &iPTensileX, double iPShearAllowable, double factor, const std::vector< double > &iPy, const std::vector< double > &iPz, 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 (double iPTensileAllowable, const std::vector< double > &iPTensileX, double iMAllowable, double b, double factorBend, const std::vector< double > &iPyBend, const std::vector< double > &iPzBend, double iPShearAllowable, double factorShear, const std::vector< double > &iPyShear, const std::vector< double > &iPzShear, 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 (double iPShearAllowable, double factor, const std::vector< double > &iPy, const std::vector< double > &iPz, std::vector< double > &ms) |
MS bolt shear Computes margin of safety of a bolt under shear load. More... | |
NXOpen::CAE::AeroStructures::Author::ABB::Status | MsMaterialStressAllowable (double allowable, const std::vector< double > &sigma, std::vector< double > &ms) |
MS material stress allowable. More... | |
NXOpen::CAE::AeroStructures::Author::ABB::Status | MsNetSection (double sigmaAllowable, double d, double t, double b, double factor, const std::vector< double > &iPExtracted, std::vector< double > &ms) |
MS Net section Computes margin of net section (due to bolt hole) More... | |
NXOpen::CAE::AeroStructures::Author::ABB::Status | MsPlateBuckling (double e, double nu, double b, double t, double k, double eta, 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 (double e, double nu, double n, double a, double b, double t, double r, NXOpen::CAE::AeroStructures::Author::ABB::MaterialBehaviour behaviour, 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 (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, 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 (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, 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 (double e, double nu, double n, double a, double b, double beta, double t, NXOpen::CAE::AeroStructures::Author::ABB::MaterialBehaviour behaviour, 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 (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, 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 (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, 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 (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, 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 (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, 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 (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, const std::vector< double > &sigma1, const std::vector< double > &sigma2, const std::vector< double > &tau, std::vector< double > &ms, 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 (double tauAllowable, double d, double t, double b, double factor, const std::vector< double > &iPExtracted, 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 (double fs, const std::vector< double > &fx, const std::vector< double > &fy, const std::vector< double > &fxy, std::vector< double > &ms) |
MS Tresca. More... | |
NXOpen::CAE::AeroStructures::Author::ABB::Status | MsTsaiHillPlaneStress (double matFcL, double matFcLT, double matFtL, double matFtLT, double matFS, const std::vector< double > &fl, const std::vector< double > &flt, const std::vector< double > &fs, std::vector< double > &ms) |
MS Tsai-Hill Computes margin of safety on the basis of Tsai-Hill failure theory (plane stresses hypothesis) More... | |
NXOpen::CAE::AeroStructures::Author::ABB::Status | SecantModulus (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 (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 (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 (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... | |
Represents a AeroStruct application building block (ABB)
To obtain an instance of this class, refer to NXOpen::Session
Created in NX12.0.0.
Type of support along unloaded edges, the choices are: {Clamped-Clamped, Simply Supported-Clamped, Simply Supported-Simply Supported, Free-Clamped, Free-Simply Supported}.
NXOpen::CAE::AeroStructures::Author::ABB::Status NXOpen::CAE::AeroStructures::Author::ABB::CurvedMetallicPanelCompressiveBucklingCoefficient | ( | 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 coefficient Output kc compressive-buckling coefficient Returns Status of the calculation
b | Dimension in radial axis |
t | Panel thickness |
r | Panel radius |
nu | Material Poisson coefficient |
kc | Compressive-buckling coefficient |
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, | ||
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
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 |
NXOpen::CAE::AeroStructures::Author::ABB::Status NXOpen::CAE::AeroStructures::Author::ABB::EquivalentSectionProperties | ( | const std::vector< double > & | n, |
const std::vector< double > & | iAi, | ||
const std::vector< double > & | iEi, | ||
const std::vector< double > & | iIxxi, | ||
std::vector< double > & | a, | ||
std::vector< double > & | e, | ||
std::vector< double > & | oYcog, | ||
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 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)
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) |
NXOpen::CAE::AeroStructures::Author::ABB::Status NXOpen::CAE::AeroStructures::Author::ABB::ExtrudedMetallicSubSectionCripplingAllowable | ( | 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
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 | ( | 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
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 | ( | 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 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
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 |
NXOpen::CAE::AeroStructures::Author::ABB::Status NXOpen::CAE::AeroStructures::Author::ABB::FlatMetallicPanelShearBucklingCoefficient | ( | 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 Type of support along the edges {Simply Supported or Clamped} Output ks Shear-buckling coefficient Returns Computation status
a | Longer plate dimension |
b | Shorter plate dimension |
bc | Type of support along the edges |
ks | Shear-buckling coefficient |
|
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.
double NXOpen::CAE::AeroStructures::Author::ABB::GetIntegerNa | ( | ) |
Integer NA value.
double NXOpen::CAE::AeroStructures::Author::ABB::GetMsThreshold | ( | ) |
The MS (margin of safety) threshold.
double NXOpen::CAE::AeroStructures::Author::ABB::GetPi | ( | ) |
PI number.
double NXOpen::CAE::AeroStructures::Author::ABB::GetRealEpsilon | ( | ) |
Real epsilon.
double NXOpen::CAE::AeroStructures::Author::ABB::GetRealMax | ( | ) |
Maximum real number.
double NXOpen::CAE::AeroStructures::Author::ABB::GetRealNa | ( | ) |
Real NA.
double NXOpen::CAE::AeroStructures::Author::ABB::GetRealNegativeInfinity | ( | ) |
The negative infinity value.
double NXOpen::CAE::AeroStructures::Author::ABB::GetRealPositiveInfinity | ( | ) |
The positive infinity value.
double NXOpen::CAE::AeroStructures::Author::ABB::GetUltimateLimitFactor | ( | ) |
Ultimate limit factor from the customer default.
bool NXOpen::CAE::AeroStructures::Author::ABB::IsRealNa | ( | double | value | ) |
Tests if a value is NA.
value | value |
bool NXOpen::CAE::AeroStructures::Author::ABB::IsRealNegativeInfinity | ( | double | value | ) |
Tests if a value equals negative infinity.
value | value |
bool NXOpen::CAE::AeroStructures::Author::ABB::IsRealPositiveInfinity | ( | double | value | ) |
Tests if a value equals positive infinity.
value | value |
NXOpen::CAE::AeroStructures::Author::ABB::Status NXOpen::CAE::AeroStructures::Author::ABB::LoadDistributionBoltsConcentricLoads | ( | const std::vector< double > & | p, |
const std::vector< double > & | iPsn, | ||
int | nblcXnbbolt, | ||
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
p | Load acting on fitting (nblc) |
iPsn | Allowable shear strength of bolt (nbbolt) |
nblcXnbbolt | nblcxnbbolt |
oPn | Shear load on bolt (nblc x nbbolt) |
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, | ||
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
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 | ( | 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 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
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 | ( | 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 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
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 | ( | 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 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
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 | ( | 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
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 | ( | double | iFbr, |
double | d, | ||
double | t, | ||
double | factor, | ||
const std::vector< double > & | iPy, | ||
const std::vector< double > & | iPz, | ||
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 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
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 |
NXOpen::CAE::AeroStructures::Author::ABB::Status NXOpen::CAE::AeroStructures::Author::ABB::MsBoltBending | ( | double | iMba, |
double | b, | ||
double | factor, | ||
const std::vector< double > & | iPy, | ||
const std::vector< double > & | iPz, | ||
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 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
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 |
NXOpen::CAE::AeroStructures::Author::ABB::Status NXOpen::CAE::AeroStructures::Author::ABB::MsBoltCombinedShearTension | ( | double | iPTensileAllowable, |
const std::vector< double > & | iPTensileX, | ||
double | iPShearAllowable, | ||
double | factor, | ||
const std::vector< double > & | iPy, | ||
const std::vector< double > & | iPz, | ||
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 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
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 |
NXOpen::CAE::AeroStructures::Author::ABB::Status NXOpen::CAE::AeroStructures::Author::ABB::MsBoltCombinedShearTensionBending | ( | double | iPTensileAllowable, |
const std::vector< double > & | iPTensileX, | ||
double | iMAllowable, | ||
double | b, | ||
double | factorBend, | ||
const std::vector< double > & | iPyBend, | ||
const std::vector< double > & | iPzBend, | ||
double | iPShearAllowable, | ||
double | factorShear, | ||
const std::vector< double > & | iPyShear, | ||
const std::vector< double > & | iPzShear, | ||
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 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
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 |
NXOpen::CAE::AeroStructures::Author::ABB::Status NXOpen::CAE::AeroStructures::Author::ABB::MsBoltShear | ( | double | iPShearAllowable, |
double | factor, | ||
const std::vector< double > & | iPy, | ||
const std::vector< double > & | iPz, | ||
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 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
iPShearAllowable | Single shear load allowable |
factor | Shear load factor |
iPy | Shear load Y direction |
iPz | Shear load Z direction |
ms | Margin of safety |
NXOpen::CAE::AeroStructures::Author::ABB::Status NXOpen::CAE::AeroStructures::Author::ABB::MsMaterialStressAllowable | ( | double | allowable, |
const std::vector< double > & | sigma, | ||
std::vector< 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
allowable | Material stress allowable |
sigma | Stress |
ms | Margin of safety |
NXOpen::CAE::AeroStructures::Author::ABB::Status NXOpen::CAE::AeroStructures::Author::ABB::MsNetSection | ( | double | sigmaAllowable, |
double | d, | ||
double | t, | ||
double | b, | ||
double | factor, | ||
const std::vector< double > & | iPExtracted, | ||
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 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
sigmaAllowable | Material stress allowable |
d | Diameter |
t | Thickness |
b | Width |
factor | Load factor |
iPExtracted | Axial load (extracted) |
ms | Margin of safety |
NXOpen::CAE::AeroStructures::Author::ABB::Status NXOpen::CAE::AeroStructures::Author::ABB::MsPlateBuckling | ( | double | e, |
double | nu, | ||
double | b, | ||
double | t, | ||
double | k, | ||
double | eta, | ||
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 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
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 |
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, | ||
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 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
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 |
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, | ||
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 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
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 |
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, | ||
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 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
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 |
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, | ||
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 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
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 |
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, | ||
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 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
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 |
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, | ||
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 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
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 |
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, | ||
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 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
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 |
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, | ||
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 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
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 |
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, | ||
const std::vector< double > & | sigma1, | ||
const std::vector< double > & | sigma2, | ||
const std::vector< double > & | tau, | ||
std::vector< double > & | ms, | ||
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 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
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 |
NXOpen::CAE::AeroStructures::Author::ABB::Status NXOpen::CAE::AeroStructures::Author::ABB::MsShearTearOut | ( | double | tauAllowable, |
double | d, | ||
double | t, | ||
double | b, | ||
double | factor, | ||
const std::vector< double > & | iPExtracted, | ||
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 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
tauAllowable | Material shear stress allowable |
d | Diameter |
t | Thickness |
b | Edge distance |
factor | Load factor |
iPExtracted | Axial load (extracted) |
ms | Margin of safety |
NXOpen::CAE::AeroStructures::Author::ABB::Status NXOpen::CAE::AeroStructures::Author::ABB::MsTrescaPlaneStress | ( | double | fs, |
const std::vector< double > & | fx, | ||
const std::vector< double > & | fy, | ||
const std::vector< double > & | fxy, | ||
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) <= (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
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 |
NXOpen::CAE::AeroStructures::Author::ABB::Status NXOpen::CAE::AeroStructures::Author::ABB::MsTsaiHillPlaneStress | ( | double | matFcL, |
double | matFcLT, | ||
double | matFtL, | ||
double | matFtLT, | ||
double | matFS, | ||
const std::vector< double > & | fl, | ||
const std::vector< double > & | flt, | ||
const std::vector< double > & | fs, | ||
std::vector< 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
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 |
NXOpen::CAE::AeroStructures::Author::ABB::Status NXOpen::CAE::AeroStructures::Author::ABB::SecantModulus | ( | 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
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 | ( | 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 Fy Yield stress allowable E Young's modulus n Ramberg-Osgood parameter Output F07 Secant yield stress F0.7
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 | ( | 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
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 | ( | 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 Fy Yield stress sigma Stress Output Et Tangent modulus
e | Young's modulus |
n | Ramberg-Osgood parameter |
iFy | Yield stress |
sigma | Stress |
oEt | Tangent modulus |