Elements

Elements are a fundamental part of any finite element analysis, since they completely represent (to an acceptable approximation), the geometry and variation in displacement based on the deformation of the structure.

Elastic, Damper, and Mass Elements

For such continuum elements, the displacement field over a volume of material which is represented by an element is approximated by corresponding shape functions based on the nodal coordinates. For example, in linear axial elements, the displacement vector is expressed as a linear polynomial whose constants are obtained from the nodal displacements.

Implementation

OptiStruct supports several elements, ranging from 0D, 1D, 2D, to 3D elements. Depending upon the type of analysis, modeling, the level of detail, and the computational time available, any of the available elements, or a combination of them can be selected to achieve the required results.

Zero-dimensional Elements

Elements in this group only connect to grid points having a single degree of freedom at each end. Elements also included in this group are those that connect to scalar points at one end and ground at the other, like the following:

CELAS1, CELAS2, CELAS3, and CELAS4 that are used to model elastic springs. The properties for CELAS1 and CELAS3 are defined on PELAS. CELAS2 and CELAS4 define spring properties.
CDAMP1, CDAMP2, CDAMP3, and CDAMP4 that are used to model scalar dampers. The properties for CDAMP1 and CDAMP3 are defined on PDAMP. CDAMP2 and CDAMP4 define scalar damper properties.
CMASS1, CMASS2, CMASS3, and CMASS4 that are used to model point masses. The properties for CMASS1 and CMASS3 are defined on PMASS. CMASS2 and CMASS4 define the mass.
CONM1 and CONM2, which are concentrated mass elements. CONM1 defines a 6x6 mass matrix at a grid point. CONM2 defines mass and inertia properties at a grid point.
CVISC is used to model viscous dampers. The properties for CVISC are defined on PVISC.

One-dimensional Elements

Elements in this group are represented by a line connecting grid points at each end. The following actions involving forces (and displacements) at each end are possible:

Forces and displacements along the axis of the element
Transverse shear forces (and displacements) in the two lateral directions
Bending moments (and rotations) in two perpendicular, bending planes
Torsional moments (and resulting rotations)
Twisting of the cross-section (or cross-sectional warping)

The elements in this category are:

CBEAM: A general beam element that supports all types of action listed above.
CBAR: A simple, prismatic beam element that supports all of the above types of actions except cross-sectional warping.
CBUSH: A general spring-damper element that supports forces, moments, and displacements along the axis of the element.
CBUSH1D: A rod-type spring-damper element.
CGAP: A gap element that supports axial and friction forces.
CGAPG: A gap element that supports axial and friction forces. It does not have to be placed between grid points. It can also connect surface patches.
CROD: A simple, axial bar element that supports only axial forces and torsional moments.
CWELD: A simple, axial bar element that supports forces, moments, and torsional moments. It does not have to be placed between grid points. It can also connect surface patches.

The properties for these elements are defined on PBEAM, PBAR, PBUSH, PBUSH1D, PGAP, PROD, and PWELD, respectively.

CONROD: A simple, axial bar element that supports only axial forces and torsional moments. This element does not reference a property definition; the property information is provided with the element definition.

Two-dimensional Shell Elements

Two-dimensional shell elements are used to model thin-shell or thick-shell behavior. Thin-shell behavior can be applied to situations where transverse shear deformation in bending can be ignored, whereas, thick-shell behavior is required in applications where transverse shear appreciably affects model behavior. OptiStruct shell elements have the ability to incorporate in-plane or membrane actions, plane strain, and bending action (including transverse shear characteristics and membrane-bending coupling actions). Reissner-Mindlin shell theory is used to model bending. A plane-strain option is available for pure 2D applications. These properties can be controlled using the PSHELL Bulk Data Entry. For example, the MID# fields on the PSHELL, can be used to define material properties to include bending, transverse shear, membrane-bending coupling, and so on.

The element shapes may be triangular (CTRIA3) or quadrilateral (CQUAD4). Second order triangular (CTRIA6) and quadrilateral (CQUAD8) shell elements are also available.

The first order shell element formulation for CQUAD4 and CTRIA3 has the special characteristic of using six degrees of freedom per grid. Hence, there is stiffness associated to each degree of freedom. In some finite element codes, shell elements do not have a drilling stiffness normal to the mid-plane, which may cause singular stiffness matrix. Then, a user-defined artificial stiffness value is assigned to this degree of freedom to avoid the singularity.

The second order shell elements (CTRIA6 and CQUAD8) have five degrees of freedom per grid. Rotational degrees of freedom without stiffness are removed through SPC.

Another form of two-dimensional elements may also be used to model thin buckled plates. These elements support shear stress in their interior and extensional forces between their adjacent grid points. These elements are used in situations where the bending stiffness and axial membrane stiffness of a plate is negligible. The elements are quadrilateral and are defined as CSHEAR. Their properties are defined on the PSHEAR entry.

Two-dimensional Shell Element Formulation (Implicit Analysis)

Element formulations indicate the theory used to construct the element, which includes the approximations and improvements applied for an accurate simulation.

The table here is applicable to MAT1, MATS1, and corresponding MAT# entries.

Table 1. Summary of Integration Schemes (Implicit Analysis)
	Linear Analysis			Nonlinear Analysis (Contact Nonlinearity only)			Nonlinear Analysis (Geometric Nonlinearity/Plasticity)
Elements	In-Plane	Through-Thickness	Bubble Functions	In-Plane	Through-Thickness	Bubble Functions	In-Plane	Through-Thickness	Bubble Functions
CTRIA3	3 point IS	Analytical Integration	Yes ²	3 point IS	Analytical Integration	Yes ²	3 point IS	6 point IS ¹	Yes ²
CQUAD4	5 point IS	Analytical Integration	Yes ²	5 point IS	Analytical Integration	Yes ²	5 point IS	6 point IS ¹	Yes ²
CTRIA6	3 point IS	Analytical Integration	No	3 point IS	Analytical Integration	No	NA	NA	NA
CQUAD8	4 point IS	Analytical Integration	No	4 point IS	Analytical Integration	No	NA	NA	NA

¹ 6-point Gauss-Lobatto quadrature for the through-thickness integration (for models with MATS1).

² Incompatible modes (bubble function) would introduce additional displacement degree of freedom which are not associated with nodes. Bubble function help add flexibility to the element especially for bending.

³ IS implies Integration Scheme.

Two-dimensional Shell Element Formulation (Explicit Nonlinear Analysis)

Element formulations indicate the theory used to construct the element, which includes the approximations and improvements applied for an accurate simulation. For explicit analysis, the integration scheme can be changed using ISOPE field on PSOLID, PLSOLID, or PSHELL entries, or via PARAM,EXPISOP. The settings on the ISOPE field will overwrite the settings on PARAM,EXPISOP.

Table 2. Summary of Integration Schemes (Explicit Nonlinear Analysis)
	Belytschko-Tsay (`ISOPE`=1)				Belytschko-Wong-Chiang with full projection (`ISOPE`=3)		C0 Triangular Shell (`ISOPE`=4)
Elements	In-Plane	Through-Thickness	In-Plane	Through-Thickness	In-Plane	Through-Thickness	In-Plane	Through-Thickness
CTRIA3	NA	NA	NA	NA	NA	NA	1 point IS	3 point IS ¹
CQUAD4	1 point IS	3 point IS ¹	1 point IS	3 point IS ¹	1 point IS	3 point IS ¹	NA	NA

¹ Through the thickness direction, the default number of integration points for Explicit analysis is 3 points. This can be controlled using the NIP field on PSHELL entry. The value of NIP can vary from 1 to 10. (a) To mimic membrane behavior, NIP can be set to 1 and/or MID2 can be left blank. (b) For elastic material, NIP can be set to 2. (c) For nonlinear material, NIP should be set to a minimum of 3.

² IS implies Integration Scheme

Two-dimensional Axisymmetric Solid Elements (Implicit Analysis)

Two-dimensional Axisymmetric solid elements CTAXI, CTRIAX6, and CQAXI are available. CTAXI and CTRIAX6 are triangular, and CQAXI is a quadrilateral axisymmetric element. The materials for these elements can be defined by MAT1, MAT3, MATS1, and MATHE entries. The properties for these elements are defined by PAXI entry.

Table 3. Summary of Integration (Implicit Analysis)
	Linear Analysis	Nonlinear Analysis (MAT# or MAT# with MATS1)	Nonlinear Analysis (MATHE)
Elements	Regular Elements ¹	Regular Elements ¹	Regular Elements ¹
CQAXI (1st order)	4 point IS	4 point IS	5 point IS
CTAXI (1st order)	3 point IS	3 point IS	3 point IS
CTRIAX6 (1st order)	3 point IS	3 point IS	3 point IS
CQAXI (2nd order)	9 point IS	9 point IS	9 point IS
CTAXI (2nd order)	7 point IS	7 point IS	3 point IS
CTRIAX6 (2nd order)	7 point IS	7 point IS	3 point IS

¹ Contact Friendly elements are not supported for 2D axisymmetric solid elements.

² IS implies Integration Scheme

Two-dimensional Plane-Strain Elements (Implicit Analysis)

Two-dimensional plane-strain elements CQPSTN and CTPSTN are available. CTPSTN is triangular, and CQPSTN is a quadrilateral plane-strain element. The materials for these elements can be defined by MAT1, MAT3, and MATHE entries. The properties for these elements are defined by PPLANE entry.

Table 4. Summary of Integration (Implicit Analysis)
	Linear Analysis	Nonlinear Analysis (MAT#)	Nonlinear Analysis (MATHE)
Elements	Regular Elements ¹	Regular Elements ¹	Regular Elements ¹
CQPSTN (1st order)	4 point IS	4 point IS	5 point IS
CTPSTN (1st order)	3 point IS	3 point IS	3 point IS
CQPSTN (2nd order)	9 point IS	9 point IS	9 point IS
CTPSTN (2nd order)	7 point IS	7 point IS	3 point IS

¹ Contact Friendly elements are not supported for two-dimensional plane-strain elements.

² IS implies Integration Scheme

Three-dimensional Solid Elements

The three-dimensional solid elements are used to model thick plates, solid structures. In general, structures in which the lateral dimensions are of the same order of magnitude as the longitudinal dimensions can support the use of three-dimensional solid elements in modeling. The elements in this category are CHEXA, CPENTA, CPYRA, and CTETRA.

Three-dimensional Solid Element Formulation (Implicit Analysis)

Element formulations indicate the theory used to construct the element, which includes the approximations and improvements applied for an accurate simulation. The number of integration points mentioned here are the generic defaults. Depending on the solution and model parameters, a different number of integration points may be used. For example, Hyperelastic elements or integration points on surfaces of solids.

Table 5. Summary of Integration Schemes (Implicit Analysis)
	Linear Analysis		Nonlinear Analysis
	Linear Analysis		MAT# or MAT# with MATS1, MATVE, MATVP					MATHE
Elements	Regular Elements	Contact-Friendly Elements	Regular Elements (`ISOP`=FULL)	Contact-Friendly Elements (`ISOP`=FULL)	Regular Elements (`ISOP`=MODPLAST)	Regular Elements (`ISOP`=REDPLAST)	Regular Elements (`ISOP`=INT0)	Regular Elements
CTETRA (1st order)	1 point IS	NA	1 point IS	NA	1 point IS	1 point IS	1 point IS	4 point IS
CHEXA (1st order)	8 point IS	NA	8 point IS	NA	8 point IS	8 point IS	9 point IS	8 point IS
CTETRA (2nd order)	4 point IS	5 point IS	5 point IS	5 point IS	5 point IS	4 point IS	9 point IS	4 point IS
CHEXA (2nd order)	27 point IS	27 point IS	27 point IS	27 point IS	14 point IS	9 point IS	27 point IS	8 point IS
CPENTA (1st order)	6 point IS	NA	6 point IS	NA	6 point IS	6 point IS	12 point IS	6 point IS
CPENTA (2nd order)	21 point IS	21 point IS	21 point IS	21 point IS	21 point IS	12 point IS	28 point IS	6 point IS
CPYRA (1st order)	8 point IS	NA	8 point IS	NA	8 point IS	8 point IS	9 point IS	NA
CPYRA (2st order)	27 point IS	27 point IS	27 point IS	14 point IS	27 point IS	9 point IS	27 point IS	NA

¹ IS implies Integration Scheme

Table 6. Summary of Integration Schemes for Gasket Elements (Implicit Analysis)
	Linear Analysis		Nonlinear Analysis
Elements	Regular Elements	Contact Friendly Elements	Regular Elements	Contact Friendly Elements
CGASK8	4 point IS	NA	4 point IS	NA
CGASK6	3 point IS	NA	3 point IS	NA
CGASK16	9 point IS	25 point IS	9 point IS	25 point IS
CGASK12	7 point IS	19 point IS	7 point IS	19 point IS

¹ The integration points are located on the mid-plane of the 3D gasket elements.

² IS implies Integration Scheme

Three-dimensional Solid Element Formulation (Explicit Nonlinear Analysis)

Element formulations indicate the theory used to construct the element, which includes the approximations and improvements applied for an accurate simulation. Note that the number of integration points mentioned here are the generic defaults. Depending on the solution and model parameters, a different number of integration points may be used. For example, Hyperelastic elements or integration points on surfaces of solids. For explicit analysis, the integration scheme can be changed using the ISOPE field on PSOLID, PLSOLID, or PSHELL entries, or via PARAM,EXPISOP. The settings on the ISOPE field will overwrite the settings on PARAM,EXPISOP.

Table 7. Summary of Integration Schemes (Explicit Nonlinear Analysis)
Elements	Regular Elements (`ISOPE`=URI)	Regular Elements (`ISOPE`=AURI)	Regular Elements (`ISOPE`=SRI)	Regular Elements (Full Integration)
CHEX (1st order)	Uniform Reduced Integration 1-point IS	Average Reduced Uniform Integration B matrix is volume-averaged over the element	Selective Reduced Integration Full IS for deviatoric term and 1-point IS for bulk term	NA
CTETRA (2nd order)	NA	NA	NA	5 point IS
CPENTA (1st order)	NA	NA	Selective Reduced Integration Full IS for deviatoric term and 1-point IS for bulk term	NA
CTETRA (1st order)	NA	NA	NA	1 point IS

¹ IS implies Integration Scheme

Interface Elements

Interface elements are elements which are specialized for a particular purpose of simulating behavior at the interfaces between structures or on the surface of the structural elements interacting with the environment (for example, CHBDYE - thermal boundary surface elements, CIFPEN/CIFHEX - cohesive elements, and so on).

The number of integration points listed is for each surface of the cohesive elements. Each Cohesive element has two surfaces.

Table 8. Summary of Integration for Cohesive Elements (Implicit Analysis)
Elements	Gaussian IS Default: `INT`=0 (On PCOHE)	Newton-Cotes IS =1 (On PCOHE)
CIFPEN (1st order)	3 point IS	3 point IS
CIFHEX (1st order)	4 point IS	4 point IS
CIFPEN (1st order)	7 point IS	6 point IS
CIFHEX (2nd order)	9 point IS	8 point IS

¹ The number of integration points listed is for each surface of the cohesive elements. Each Cohesive element has two surfaces.

² IS implies Integration Scheme

Offset for One-dimensional and Two-dimensional Elements

Some one-dimensional and two-dimensional elements can use offset to “shift” the element stiffness relative to the location determined by the element’s nodes. For example, shell elements can be offset from the plane defined by element nodes by means of ZOFFS. In this case, all other information, such as material matrices or fiber locations for the calculation of stresses, are given relative to the offset reference plane. Similarly, the results, such as shell element forces, are output on the offset reference plane.

Offset is applied to all element matrices (stiffness, mass, and geometric stiffness), and to respective element loads (such as gravity). Hence, in principle, offset can be used in all types of analysis and optimization.

However, caution is advised when interpreting the results, especially in linear buckling analysis. Without offset, a typical simple structure will bifurcate and loose stability “instantly” at the critical load. With offset, though, the loss of stability is gradual and asymptotically reaches a limit load, as shown in Figure 1(b):

Figure 1.

In practice, the structure with offset can reach excessive deformation before the limit load is reached.

Note: More complex structures, such as frames or structures experiencing bending moments, buckle via limit load even in absence of ZOFFS on the element card.

Furthermore, in a fully nonlinear approach, additional instability points may be present on the limit load path.

Comments

Through-Thickness direction, the default number of integration points for Explicit analysis is 3 points. This can be controlled using the NIP field on PSHELL entry. The value of NIP can vary from 1 to 10.
- To mimic membrane behavior, NIP can be set to 1
- For elastic material, NIP can be set to 2
- For nonlinear material, NIP should be set to a minimum of 3

Non-structural Mass

Non-structural mass may be specified in two different ways.

Many property definitions (PSHELL, PCOMP, PBAR, PBARL, PBEAM, PBEAML, PROD, CONROD, PSHEAR, and PTUBE), have an NSM data field that allows a value of non-structural mass per unit area or non-structural mass per unit length to be defined.
When non-structural mass is defined in this way, it is considered in all analyses.
Non-structural mass may be defined via a number of non-structural mass Bulk Data Entries (NSM, NSM1, NSML, NSML1, and NSMADD) for a list of elements or properties. In the case of a list of properties, non-structural mass is applied to the elements referencing the properties in the list.
These non-structural mass definitions must be selected for use in an analysis through the NSM Subcase Information Entry.
The NSM Subcase Entry is currently subcase-dependent only for Linear Static and Nonlinear Static Analysis. For all other solution sequences, the NSM Subcase Entry should be defined globally above the first SUBCASE statement. If the NSM Subcase Entry is specified within any subcase which is not linear static or nonlinear static, then the run will be terminated with an error.
- Input non-structural mass per unit area/length/volume (NSM/NSM1)
  The NSM Bulk Data Entry and its alternate form NSM1 allow you to define a value of non-structural mass per unit area, non-structural mass per unit length, or non-structural mass per unit volume to be applied to a selected list of elements
  
  The NSM field on various property entries listed above also inputs mass per unit area/length/volume directly.
- Input lumped non-structural mass (NSML/NSML1)
  The NSML Bulk Data Entry and its alternate form NSML1 allow you to allocate and smear a lumped non-structural mass value to be evenly distributed over a list of elements.
  - Default Distribution (DTYPE=blank on NSML/NSML1)
    The non-structural mass value per unit area, per unit length, or per unit volume to be applied to the elements is: (1) $N S M_{per unit area} = \frac{V A L U E}{n \sum i = 1 A_{i}}$ $N S M_{per unit area} = \frac{V A L U E}{\sum_{i = 1}^{n} A_{i}}$ (2) $N S M_{per unit length} = \frac{V A L U E}{n \sum i = 1 L_{i}}$ $N S M_{per unit length} = \frac{V A L U E}{\sum_{i = 1}^{n} L_{i}}$ (3) $N S M_{per unit volume} = \frac{V A L U E}{\sum_{i = 1}^{n} V_{i}}$
    
    For the default case when DTYPE is blank, referencing a mixture of different element or property types is not supported.
  - Distribution based on Mass/Volume (DTYPE=MASS/VOLUME on NSML/NSML1)
    The non-structural mass value per unit mass or volume to be applied to the elements is: (4) $N S M_{per unit mass} = \frac{V A L U E}{\sum_{i = 1}^{n} M_{i}}$ (5) $N S M_{per unit volume} = \frac{V A L U E}{\sum_{i = 1}^{n} V_{i}}$
Where,

$n$

Number of elements in the set

$V A L U E$

Value of the lumped mass

$L_{i}$

Length of element $i$

$A_{i}$

Area of element $i$

$V_{i}$

Volume of element $i$

$M_{i}$

Mass of element $i$

An important difference between the default distribution (DTYPE=blank) and DTYPE=MASS/VOLUME, is that a mixture of multiple element types (1D, 2D, and 3D elements) can be defined on a single NSML/NSML1 entry when TYPE field is set to ELEMENT/ELSET (mixture of elements) or MIXED (mixture of properties).

The NSMADD Bulk Data Entry allows you to form combinations of NSM, NSM1, NSML, and NSML1.

An element can have more than one non-structural mass value specified for it. The actual non-structural mass value will be the sum of all of the individual non-structural mass values.

Virtual Fluid Mass

Virtual Fluid Mass mimics the mass effect of an incompressible inviscid fluid in contact with a structure. There is no mesh needed for the fluid domain. The Virtual Fluid Mass represents the full coupling between acceleration and pressure at the fluid-structure interface.

A dense mass matrix is generated among damp grids at the fluid-structure interface. This simulation is applicable to automobile containers, such as a fuel tank, which hold non-pressurized fluids.

Assumptions

The fluid is inviscid and incompressible. The fluid flow is a potential flow.
Because the fluid is nearly incompressible, the structural modes are below the compressible fluid modes.
There is no gravity effect or sloshing effect.
There is no acoustic effect involved. The modes from the structural side do not couple with the modes of the nearly incompressible fluid modes.
Fully enclosed wet surface without any open surface is currently not supported.

MFLUID Interface

If a fish can swim to every point inside fluid domain without leaving the fluid, the fluid domain can be represented by a single MFLUID card in the Bulk Data section. Each MFLUID card in the Bulk Data section can only be referred to by a single MFLUID card in the control section. Multiple Bulk Data MFLUID cards can be referred by a single MFLUID card in the control section. Symmetry and anti-symmetry options can be applied to a MFLUID card.

PARAM,VMOPT
If PARAM,VMOPT,1 is used (default), the virtual mass is included in the regular mass matrix and it can be applied to both direct and modal dynamic subcases. Because the virtual mass matrix is dense for the damp grids, the computational time increases significantly.

However, you have the option to use PARAM,VMOPT,2; although, PARAM,VMOPT,2 can only be applied to modal dynamic subcases. In this case, the virtual mass is added after the eigen solution, and the computational time is not increased significantly. When PARAM,VMOPT,2 is used, the dry modes are computed without adding virtual mass in the computation. Then the modes are modified based on the virtual mass matrix.

To generate accurate wet modes results with PARAM,VMOPT,2, it is recommended to request 2 to 4 times (or even higher, depending on the density of fluid) the number of dry modes than the desired number of wet modes. If the density of fluid is larger, the number of dry modes required could be larger accordingly in order to maintain the accuracy of wet modes that are based on dry modes.
PARAM,VMMASS
PARAM,VMMASS,YES can be used in conjunction with PARAM,VMOPT,1 to include MFLUID mass to the Grid Point Weight Generator output in the .out file.

Theory

The elemental pressure and acceleration are calculated with respect to the source potential of the element. The pressure is calculated based on displacement potential as:(6)

$p = - ρ \frac{\partial^{2} ϕ}{\partial t^{2}}$

If the source potential of element

$j$ is

$τ_{1 z}$ , the pressure can be represented as:(7)

$p_{i} = \sum_{j} ρ \frac{{\ddot{σ}}_{j}}{| r_{i} - r_{j} |} d A_{j}$

An additional area integration is done to convert pressure into force.

Similarly, the acceleration vector

${\ddot{u}}_{i}$ can be represented as:(8)

${\ddot{u}}_{i} = \sum_{j} \int_{A_{j}} \frac{{\ddot{σ}}_{j}}{{| r_{i} - r_{j} |}^{2}} d A_{j}$

Using the force and acceleration, the effective mass matrix can be calculated.

Arbitrary Beam Section Definition

In addition to using predefined beam cross-sections selected by the TYPE field on the PBARL and PBEAML Bulk Data Entries, defining arbitrary beam cross-sections. This is referred to here as section definitions. To define an Arbitrary Beam Section, HYPRBEAM should be entered into the GROUP field on the PBARL and PBEAML Bulk Data Entries. Also, the ND field should specify the number of dimensions input during the definition of the arbitrary beam section in the DIMi fields of the PBARL and PBEAML Bulk Data Entries.

Section definitions are contained within the Bulk Data section of the input file. A section definition begins with the statement BEGIN and ends with the statement END. Section definitions are referenced from a PBARL or PBEAML definition through the NAME field. The NAME entered on the PBARL or PBEAML definition must match the NAME following the BEGIN statement.

The section is defined by a 2D finite element mesh. The finite element mesh is composed of nodes (specified by GRIDS entries), which are connected by 2-node, 3-node, 4-node, 6-node or 8-node elements (specified by CSEC2, CSEC3, CSEC4, CSEC6, or CSEC8 entries, respectively). These elements reference PSEC entries; these provide a material reference for all elements and thickness information for the 2-noded CSEC2 elements.

▸Example: Simple Thin-walled Section Definition Named SQUARE

$
BEGIN,HYPRBEAM,SQUARE
$
GRIDS,1,0.0,0.0
GRIDS,2,1.0,0.0
GRIDS,3,1.0,1.0
GRIDS,4,0.0,1.0
$
CSEC2,10,100,1,2
CSEC2,20,100,2,3
CSEC2,30,100,3,4
CSEC2,40,100,4,1
$
PSEC,100,1000,0.1
$
END,HYPRBEAM
$

▸Example: Solid Section Definition Named CUTOUT

$
BEGIN,HYPRBEAM,CUTOUT
$
GRIDS,1,0.0,0.0
GRIDS,2,0.05,0.0
...
...
GRIDS,895,0.35,1.18
GRIDS,896,0.38,1.19
$
CSEC3,806,100,887,873,872
CSEC3,809,100,868,820,885
CSEC3,812,100,813,803,817
$
CSEC4,1,100,147,148,149,157
CSEC4,2,100,157,149,150,158
...
...
CSEC4,813,100,648,712,895,896
CSEC4,814,100,647,646,896,895
$
PSEC,100,1000
$
END,HYPRBEAM
$

Rigid Elements and Multi-Point Constraints

Rigid elements and multi-point constraints are used to constrain one or more degrees of freedom to be equal to linear combinations of the values of other degrees of freedom.

Rigid elements are equations generated internally. You provide the connection data only. Rigid elements function as rigid bodies; therefore they are also known as rigid bodies or constraint elements. Internally, they are treated the same way as multi-point constraints.

The RROD element can be used to model a pin-ended rod which is rigid in extension. One equation of constraint will be generated for this element. The RBAR element can be used to model a rigid bar with six degrees of freedom at each end. Anywhere from one to six (depending on your input) equations of constraint will be generated for this element.

The RBE1 and RBE2 elements are rigid bodies connected to an arbitrary number of grid points. The number of equations of constraint generated is equal to or greater than one, depending on the dependent degrees of freedom selected by you. For the RBE1 element, the independent degrees of freedom are six components of motion that must be jointly capable of representing any general rigid body motion of the element; whereas for the RBE2 element, the independent degrees of freedom are the six components of motion at a single grid point.

The RBE3 element provides for specification from one to six equations of constraint developed from the relation that the motion at a "reference grid point" is the least square weighted average of the motion at other grid points. This element is generally used to "beam" loads and masses from a reference point to a set of grid points. Multi-point constraints are equations in which you explicitly provide the coefficients of the equations. Each multi-point constraint is described by a single equation that specifies a linear relationship for two or more degrees of freedom. Multiple sets of multi-point constraints can be provided in the Bulk Data section. In the Subcase Information section, the multi-point constraints are assigned to the specific load case using the MPC statement.

The Bulk Data Entry MPC is the statement for defining multi-point constraints. The first coordinate mentioned on the card is taken as the dependent degree of freedom (that is, the degree of freedom that is removed from the equations of motion). Dependent degrees of freedom may appear as independent terms in other equations of the set; however, they may appear as dependent terms in only a single equation.

Some uses of multi-point constraints are:

To enforce zero motion in directions other than those corresponding to components of the global coordinate system. In this case, the multi-point constraint will involve only the degrees of freedom at a single grid point. The constraint equation relates the displacement in the direction of zero motion to the displacement components in the global system at the grid point.
To describe rigid elements and mechanisms such as levers, pulleys, and gear trains. In this application, the degrees of freedom associated with the rigid element that are in excess of those needed to describe rigid body motion are eliminated with multi-point constraint equations. Treatment of very stiff members as being rigid elements eliminates the ill-conditioning associated with their treatment as ordinary elastic elements.
To be used with scalar elements to generate non-standard structural elements and other special effects.

When using rigid elements or multi-point constraints, you must make sure that the following requirements are satisfied:

A dependent degree of freedom cannot be in the SPC.
A dependent degree of freedom in any rigid element or multi-point constraint cannot be defined as a dependent degree of freedom in any other rigid element or multi-point constraint.

JOINTG (Connectors)

The various joints identified by the JTYPE field require certain corresponding coordinate system rules.

Note: The OptiStruct joints defined using JOINTG are different from the Multibody Dynamics (OS-MBD) joints which are defined using the JOINT entry with OptiStruct-MotionSolve integration.

Universal Joint

A Universal Joint is a joint which allows rotary motion transmission in multiple shafts which are at an angle to each other (for example, in a powertrain drive shaft). The joint works by allowing free rotation along two mutually perpendicular degrees of freedom of the two grid points associated with the joint. The remaining rotational degrees of freedom are automatically constrained. The translational degrees of freedom can be constrained by defining an additional Ball joint.

On the JOINTG entry, follow these rules to define a universal joint:

JTYPE should be set to UNIVERSA.
The X-axis of the coordinate system (CID1) of Grid Point 1 should be mutually perpendicular to the Z-axis of coordinate system (CID2) of Grid Point 2.
The Y-axes of coordinate systems 1 and 2 should be along the corresponding shaft axes. Additionally, they should point in the same direction (should not point opposite to one another).
The translational degrees of freedom can be constrained by defining an additional Ball joint.

Figure 4.

Revolute Joint

A Revolute Joint is a joint which allows single axis rotation functions (for example, in a door hinge). The joint works by allowing free rotation (or enforced displacement via MOTNJG) about one degree of freedom of the two grid points associated with the joint (the two selected degrees of freedom should be the same). The remaining rotational degrees of freedom are automatically constrained. The translational degrees of freedom can be constrained by defining an additional Ball joint.

On the JOINTG entry, follow these rules to define a revolute joint:

JTYPE should be set to REVOLUTE.
The X-axis of the coordinate system (CID1) of Grid Point 1 should be parallel (and in the same direction) to the X-axis of coordinate system (CID2) of Grid Point 2. The MOTNJG Subcase Information and Bulk Data Entries can be used to define the value of rotation (dof=4) about the X-axis.
The other axes of the coordinate system may point in any direction.
The translational degrees of freedom can be constrained by defining an additional Ball joint.

Figure 5.

Ball Joint

A Ball Joint is a joint which allows free rotation in all three directions and translations are constrained in all three directions (for example, in automobile steering and suspension systems). The joint works by allowing free rotation about all three degrees of freedom of the two grid points associated with the joint. The remaining translational degrees of freedom are constrained. For BALL joint, there is no relative translation between the two degrees of freedom in the basic system. Local systems should not be defined for the BALL joint and will not be used if specified.

On the JOINTG entry, follow these rules to define a ball joint.

JTYPE should be set to BALL.
Only the grid points GID1 and GID2 should be specified. The coordinate systems are not required.
The grid points GID1 and GID2 should be coincident to simulate physical joints. If they are not, the specified joint may deviate from expected behavior.

Figure 6.

Axial Joint

An Axial Joint is a joint which allows connection between two grid points by enforcing relative displacement along the line joining them. The relative displacement is enforced only along the line connecting the two grid points, and other degrees of freedom are not constrained by this joint.

On the JOINTG entry, follow these rules to define an axial joint.

JTYPE should be set to AXIAL.
Only the grid points GID1 and GID2 should be specified. The coordinate systems are not required and will be ignored if specified.
The MOTNJG Bulk Data Entry should be used to identify the value of the enforced relative displacement via the VALUE field ( $u_{r e l}$ ). The MOTNJG Subcase Information Entry can then be used to identify the corresponding MOTNJG Bulk Data Entries.
To hold the value of the relative displacement from the previous subcase in the subsequent nonlinear subcase (via CNTNLSUB), the VALUE field can be set to FIXED on the MOTNJG Bulk Data Entry. Alternatively, a different value of relative motion can be specified for the continuing subcase.

Figure 7.

Cartesian Joint

A Cartesian Joint allows connection between two grid points by enforcing relative displacement along three directions (1,2,3) of a local Cartesian coordinate system CID1 defined on GID1. The other degrees of freedom are not constrained by this joint.

On the JOINTG entry, follow these rules to define a Cartesian joint.

JTYPE should be set to CARTES.
The grid points GID1 and GID2 should be specified. The coordinate system CID1 on GID1 is required. CID2 is not required and will be ignored if specified.
The MOTNJG Bulk Data Entry should be used to identify the value of the enforced relative displacement via the VALUE fields corresponding to the 1, 2, and 3 degrees of freedom. The MOTNJG Subcase Information Entry can then be used to identify the corresponding MOTNJG Bulk Data Entries.
To hold the value of the relative displacement from the previous subcase in the subsequent nonlinear subcase (via CNTNLSUB), the VALUE field can be set to FIXED on the MOTNJG Bulk Data Entry. Alternatively, a different value of relative motion can be specified for the continuing subcase.

Cardan Joint

A Cardan Joint allows connection between two grid points by enforcing relative rotation along three directions (4,5,6). Three successive rotations are performed based on the Cardan angles that correspond to the local coordinate system directions at GID1 and GID2. The other degrees of freedom are not constrained by this joint.

On the JOINTG entry, follow these rules to define a Cardan joint.

JTYPE should be set to CARDAN.
The grid points GID1 and GID2 should be specified. The coordinate system CID1 is required. CID2 is not required and will be ignored if specified.
The MOTNJG Bulk Data Entry should be used to identify the value of the Cardan angles via the VALUE fields corresponding to the 4, 5, and 6 degrees of freedom. The MOTNJG Subcase Information Entry can then be used to identify the corresponding MOTNJG Bulk Data Entries.
To hold the value of the relative displacement from the previous subcase in the subsequent nonlinear subcase (via CNTNLSUB), the VALUE field can be set to FIXED on the MOTNJG Bulk Data Entry. Alternatively, a different value of relative motion can be specified for the continuing subcase.

In-Plane Joint

An in-plane joint allows connection between two grid points by enforcing zero relative displacement along direction 1 of a local Cartesian coordinate system CID1 defined on GID1. Additionally, enforced relative displacement is applied in the 2 and 3 directions of CID1. The other degrees of freedom are not constrained by this joint.

On the JOINTG entry, follow these rules to define a In-Plane joint.

JTYPE should be set to INPLANE.
The grid points GID1 and GID2 should be specified. The coordinate system CID1 on GID1 is required. CID2 is not required and will be ignored if specified.
The MOTNJG Bulk Data Entry should be used to identify the value of the enforced relative displacement via the VALUE fields corresponding to the 2, and 3 degrees of freedom. The MOTNJG Subcase Information Entry can then be used to identify the corresponding MOTNJG Bulk Data Entries.
To hold the value of the relative displacement from the previous subcase in the subsequent nonlinear subcase (via CNTNLSUB), the VALUE field can be set to FIXED on the MOTNJG Bulk Data Entry. Alternatively, a different value of relative motion can be specified for the continuing subcase.

In-Line Joint

An in-line joint allows connection between two grid points by enforcing zero relative displacement along directions 2 and 3 of a local Cartesian coordinate system CID1 defined on GID1. Additionally, enforced relative displacement is applied in the 1 direction of CID1. The other degrees of freedom are not constrained by this joint.

On the JOINTG entry, follow these rules to define a In-Line joint.

JTYPE should be set to INLINE.
The grid points GID1 and GID2 should be specified. The coordinate system CID1 on GID1 is required. CID2 is not required and will be ignored if specified.
The MOTNJG Bulk Data Entry should be used to identify the value of the enforced relative displacement via the VALUE field corresponding to the 1 degree of freedom. The MOTNJG Subcase Information Entry can then be used to identify the corresponding MOTNJG Bulk Data Entries.
To hold the value of the relative displacement from the previous subcase in the subsequent nonlinear subcase (via CNTNLSUB), the VALUE field can be set to FIXED on the MOTNJG Bulk Data Entry. Alternatively, a different value of relative motion can be specified for the continuing subcase.

Orient Joint

An Orient joint allows connection between two grid points by enforcing zero relative rotations along directions 4, 5, and 6 of two local Cartesian coordinate systems CID1 and CID2. The other degrees of freedom are not constrained by this joint.

On the JOINTG entry, follow these rules to define an Orient joint.

JTYPE should be set to ORIENT.
The grid points GID1 and GID2 should be specified.
The coordinate systems CID1 and CID2 are required.

Hinge Joint

A Hinge joint allows connection between two grid points by enforcing zero relative translations along directions 1, 2, and 3 of two local Cartesian coordinate systems CID1 and CID2. Additionally, the relative rotations in 5 and 6 are also constrained. Only degree of freedom 4 is not constrained by this joint. The joint works by allowing free rotation in degree of freedom 4 of the two grid points associated with the joint (the two X axes of both CID1 and CID2 should match for this joint).

Therefore, on the JOINTG entry, the following rules should be followed to define a Hinge joint:

JTYPE should be set to HINGE.
The grid points GID1 and GID2 should be specified. The coordinate systems CID1 and CID2 are required.
The X-axes of both CID1 and CID2 should match.
The Hinge joint is equivalent to a combination of Revolute joint and Rigid Pin joint.

Rigid Pin Joint

A Rigid Pin joint allows connection between two grid points by enforcing zero relative translations along directions 1, 2, and 3 of a local Cartesian coordinate system CID1 defined on grid GID1. The joint works by allowing free rotation in degrees of freedom 4, 5 and 6 of the two grid points associated with the joint. For RPIN joint, there is no relative translation between the grids in the local system defined on CID1 (this is where RPIN differs from BALL joint). Note that for any local system defined on a grid for the joints, the local systems move/rotate along with the grids on which they are defined. Therefore, even though from the perspective of the basic system, there may seem to be relative translation between the grids in RPIN joint, there will not be any relative translation between the grids in the local CID1 which moves/rotates with grid GID1.

Therefore, on the JOINTG entry, the following rules should be followed to define a Rigid Pin joint:

JTYPE should be set to RPIN.
The grid points GID1 and GID2 should be specified.
The coordinate systems CID1 is required and CID2 should not be specified. CID2 will be ignored if defined.

Rigid Link Joint

A Rigid Link joint allows connection between two grid points by enforcing zero relative translations along direction 1 of the basic coordinate system. The joint does not constrain degrees of freedom 2, 3, 4, 5 and 6 of the two grid points associated with the joint. For RLINK joint, there is no relative translation between the grids in direction 1 in the basic system.

Note: No local coordinate systems are required for the Rigid Link joint.

Therefore, on the JOINTG entry, the following rules should be followed to define a Rigid Link joint.

JTYPE should be set to RLINK.
The grid points GID1 and GID2 should be specified.
The coordinate systems CID1 and CID2 should not be specified and will be ignored if defined.

Rigid Beam Joint

A Rigid Beam joint allows connection between two grid points by enforcing zero relative translations along directions 1, 2, and 3 of a local default basic coordinate system on grid GID1. Additionally, zero relative rotations along directions 4, 5, and 6 of two local basic coordinate systems on GID1 and GID2.

Note: No local coordinate systems are required for the Rigid Beam joint, and default local basic systems are used at the two grid points.

Therefore, on the JOINTG entry, the following rules should be followed to define a Rigid Beam joint.

JTYPE should be set to RBEAM.
The grid points GID1 and GID2 should be specified.
By default, CID1 and CID2 are defined as the basic coordinate system and the results are output in the basic coordinate system.
If a local coordinate system is assigned to these fields, the results are output in the local coordinate system.
The Rigid Beam joint is equivalent to a combination of Rigid Pin joint and Orient joint.

Universal Connection with Rigid Pin Joint

A Universal connection with Rigid Pin Joint allows connection between two grid points by allowing free rotation along two mutually perpendicular degrees of freedom of the two grid points associated with the joint. The remaining rotational degrees of freedom are automatically constrained by enforcing zero relative translations along directions 1, 2, and 3 of a local default basic coordinate system on grid GID1. Additionally, zero relative rotations along directions 4, 5, and 6 of two local coordinate systems, CID1 and CID2, on GID1 and GID2.

Note: Both local coordinate systems are required for this joint.

Therefore, on the JOINTG entry, the following rules should be followed to define a UJOINT joint:

JTYPE should be set to UJOINT.
The X-axis of the coordinate system (CID1) of Grid Point 1 should be mutually perpendicular to the Z-axis of coordinate system (CID2) of Grid Point 2.
The Y-axes of coordinate systems 1 and 2 should be along the corresponding shaft axes. Additionally, they should point in the same direction (should not point opposite to one another).
The grid points GID1 and GID2 should be specified.
The coordinate systems CID1 and CID2 should also be specified and follow the setup mentioned in points 2 and 3 above.

The UJOINT joint is equivalent to a combination of Rigid Pin joint and Universal joint.

Cylindrical Joint

A Cylindrical joint allows connection between two grid points by enforcing zero relative translation along directions 2 and 3 and zero relative rotation along directions 4 and 5 of a local Cartesian coordinate system CID1 defined on GID1. Additionally, free translation (or enforced relative displacement via MOTNJG) is allowed in the 1 direction of CID1, and free rotation (or enforced displacement via MOTNJG) is allowed about degree of freedom 4 of both CID1 and CID2.

Note: Both local coordinate systems are required for the Cylindrical joint and the degree of freedom 1 should match for both systems.

Therefore, on the JOINTG entry, the following rules should be followed to define a Cylindrical joint:

JTYPE should be set to CYLINDRI.
The grid points GID1 and GID2 should be specified.
The coordinate systems CID1 and CID2 should be specified and the direction 1 of both systems should match

The Cylindrical joint is equivalent to a combination of In-Line joint and Revolute joint.

Translator Joint

A Translator joint allows connection between two grid points by enforcing zero relative displacement along directions 2 and 3 of a local Cartesian coordinate system CID1 defined on GID1. Additionally, free translation (or enforced relative displacement via MOTNJG) is allowed in the 1 direction of CID1, and zero relative rotations along directions 4, 5, and 6 of two local coordinate systems CID1 and CID2 on GID1 and GID2.

Note: Both local coordinate systems are required for the Translator joint.

Therefore, on the JOINTG entry, the following rules should be followed to define a Translator joint:

JTYPE should be set to TRANSLAT.
The grid points GID1 and GID2 should be specified.
The coordinate systems CID1 and CID2 should be specified.

The Translator joint is equivalent to a combination of In-Line joint and Orient joint.

Combination Joints

Axial and Orient Joint

A combination of Axial and Orient joints allow connection between two grid points by enforcing relative displacement along the line joining them and by enforcing zero relative rotations along directions 4, 5, and 6. The other degrees of freedom are not constrained by this joint.

Note: Both local coordinate systems are required for this joint.

Therefore, on the JOINTG entry, the following rules should be followed to define this joint:

JTYPE should be set to AXIAORIE.
The grid points GID1 and GID2 should be specified. The coordinate systems CID1 and CID2 should be specified.

Inline and Cardan Joint

A combination of Inline and Cardan joints allows connection between two grid points by enforcing zero relative displacement along directions 2 and 3 of a local cartesian coordinate system CID1 defined on GID1. Additionally, enforced relative displacement is applied in direction 1 of CID1. the line joining them and by enforcing zero relative rotations along directions 4, 5, and 6. Additionally, relative rotation along directions 4, 5, and 6 are enforced. The three successive rotations are performed based on the Cardan angles that correspond to the local system directions at GID1 and GID2.

Note: Both local coordinate systems are required for this joint.

Therefore, on the JOINTG entry, the following rules should be followed to define this joint:

JTYPE should be set to INLICARD.
The grid points GID1 and GID2 should be specified. The coordinate systems CID1 and CID2 should be specified.

Rigid Link and Orient Joint

A combination of Rigid Link and Orient joints allow connection between two grid points by enforcing zero relative translations along direction 1 of the basic coordinate system them and by enforcing zero relative rotations along directions 4, 5, and 6 along the local coordinate systems. The other degrees of freedom are not constrained by this joint.

Note: Both local coordinate systems are required for this joint.

Therefore, on the JOINTG entry, the following rules should be followed to define this joint:

JTYPE should be set to RLINORIE.
The grid points GID1 and GID2 should be specified. The coordinate systems CID1 and CID2 should be specified.

Define Local Coordinate Systems for JOINTG

Local coordinate systems (via CID1 and CID2) are important to define the interpretation of joint loading (LOADJG), joint motion (MOTNJG), and for STOP and LOCK options (PJOINTG).

Local coordinate systems (CID1 and CID2) are not mandatory for all joint types. Depending on the joint, either CID1, CID2, or both may be required. For some joints, like BALL or RLINK, both CID1 and CID2 are not required. For more information, refer to JOINTG (Connectors). This is also tabulated on the JOINTG Bulk Data Entry.

Note: With regard to JOINTG, local coordinate systems (CID1 and CID2) always rotate and translate in conjunction with the grid points they are associated to (corresponding, GID1 and GID2).

Interpretation of Joint Characteristics

The interpretation of joint characteristics, such as joint length, loading, motion, STOP, LOCK options, and output are influenced by:

Order of joint grids, GID1 and GID2.
The order of GID1 and GID2 influences the calculation of relative displacement between the two grids. Typically for a particular degree of freedom, the relative displacement is calculated as:(9) $u_{r e l} = u_{G I D 2} - u_{G I D 1}$

Where, $u_{G I D 1}$ and $u_{G I D 2}$ are displacements of GID1 and GID2 in a particular degree of freedom.
Local Coordinate System(s) CID1 and CID2 at GID1 and GID2, respectively.
Direction of the degree of freedom of interest identified via CID1 or CID2 influences the interpretation of length, motion, STOP, LOCK options, and output.
Nature of applied loading, motion, or value of STOP/LOCK.
For instance, the effect of compressive loading (negative LOADJG) on the joint is opposite to that of tensile loading (positive LOADJG).

The following sections investigate in detail, the interpretation of individual joint characteristics. Simple examples with corresponding JOINTG are used to illustrate the concepts, as well.

Joint Loading (LOADJG)

Loading on a joint can be applied using LOADJG entry or via other external loads. Here you will study the behavior of loading using LOADJG.

If the VALUE field for a particular dof on LOADJG Bulk Data Entry is positive (tensile), then opposing forces are internally applied on the grid points to cause a corresponding increase in the value of

$u_{r e l}$ . Where,

$u_{r e l} = u_{G I D 2} - u_{G I D 1}$ . Similarly, a negative (compressive) LOADJG will lead to forces which act on the joint to decrease the value of

$u_{r e l}$ .

Note: The actual direction of forces applied on the joint grids may point towards or away from each other depending on the factors listed in Interpretation of Joint Characteristics.

For example, in Figure 8, the joint grids move towards each other for a positive value of LOADJG and move away from each other for a negative value of LOADJG.

At a first glance, it seems counter-intuitive, since a positive LOADJG is leading to the joint grids moving together and a negative LOADJG is moving the joint grids apart. However, upon closer inspection, it becomes clear that, the value of

$u_{r e l}$ is +1.50 for a LOADJG of 600.0 and

$u_{r e l}$ is -1.50 for a LOADJG of -600.0. This is a consequence of the order of GID1 (node 8) and GID2 (node 7) having a direction opposite to the X-axis of the local coordinate system (CID1) for this INLINE joint (as listed in Interpretation of Joint Characteristics). Therefore, although this result is technically accurate, caution should be exercised to examine your model setup to make sure that you intend to define the joint direction opposite to the local X-axis of the joint.

When the direction of X-axis is flipped, note that the effect of LOADJG is more intuitive; wherein, positive LOADJG leads to the grids moving apart, and a negative LOADJG leads of the grids moving together.

The key here is the calculation of U7 and U8. In the LOADJG=600.0 image above, U7 in basic Y is -0.6. Since Local X was flipped, it points opposite to basic Y. Therefore, U7 in local X is +0.6. Similarly, U8 in basic Y is 0.9 and in local X it is -0.9. Therefore, U7-U8 in local X is 1.5. The value of U7 and U8 for LOADJG=-600.0 case can also be inferred similarly.

You can see that the only change is that the local CID1 X-axis is flipped (the local Z-axis is also flipped, but it does not influence the results of this model. It is not possible to only flip the X-axis since it will then no longer be a Right-handed coordinate system).

Enforced Joint Motion (MOTNJG)

Enforced Motion on a joint can be applied using MOTNJG entry or via other external SPCD entries. In this section, you will study the behavior of loading using MOTNJG.

If the VALUE field for a particular dof on MOTNJG Bulk Data Entry is positive, then a positive relative motion is enforced on the joint (that is, a positive

$u_{r e l}$ is enforced). This is similar to a tensile LOADJG applied to the joint. Similarly, a negative MOTNJG will lead to a decrease in the value of

$u_{r e l}$ .

Note: The actual motion of the joint grids may be towards or away from each other depending on the factors listed in Interpretation of Joint Characteristics.

For example, in Figure 12, the joint grids move towards each other for a positive value of MOTNJG and move away from each other for a negative value of MOTNJG.

At a first glance, it seems counter-intuitive, since a positive MOTNJG is leading to the joint grids moving together and a negative MOTNJG is moving the joint grids apart. However, upon closer inspection, it becomes clear that, the value of

$u_{r e l}$ is +1.2 for a MOTNJG of 1.2 and

$u_{r e l}$ is -1.2 for a MOTNJG of -1.2. Similar to the example in the LOADJG section, this is a consequence of the order of GID1 (node 8) and GID2 (node 7) having a direction opposite to the X-axis of the local coordinate system (CID1) for this INLINE joint (as listed in Interpretation of Joint Characteristics). Therefore, although this result is technically accurate, caution should be exercised to examine your model setup to make sure that you intend to define the joint direction opposite to the local X-axis of the joint.

When the direction of X-axis is flipped, you see that the effect of MOTNJG is more intuitive, wherein, positive MOTNJG leads to the grids moving apart, and a negative MOTNJG leads to the grids moving together.

The key here is the calculation of U7 and U8. In the MOTNJG=1.2 image above, U7 in basic Y is -0.48. Since Local X was flipped, it points opposite to basic Y. Therefore, U7 in local X is +0.48. Similarly, U8 in basic Y is 0.72 and in local X it is -0.72. Therefore, U7-U8 in local X is 1.2. The value of U7 and U8 for MOTNJG=-1.2 case can also be inferred similarly.

You can clearly see that the only change is that the local CID1 X-axis is flipped (the local Z-axis is also flipped, but it does not influence the results of this model. It is not possible to only flip the X-axis since it will then no longer be a Right-handed coordinate system).

STOP and LOCK (PJOINTG)

STOP and LOCK options are available via the PROPERTY field on the PJOINTG Bulk Data Entry, to restrict the range of movement of the grids associated with a joint defined via JOINTG.

Note: STOP and LOCK should not be used in conjunction with the MOTNJG entry as they are opposing constraints on the joint which cannot be resolved. For example, a MOTNJG value of 4.5 enforces a relative displacement of 4.5 and a LOCK motion value of 1.0 restricts motion beyond 1.0. Both constraints cannot be satisfied simultaneously.

The direction of the local system axis along the degree of freedom of interest influences the interpretation of length of the joint. Therefore, it influences the interpretation of length that is used to quantify the defined lower and upper bounds on the PJOINTG entry for STOP and LOCK options, when the TYPE field is set to 1.

Length of a joint in a particular degree of freedom is positive, if the GID1 → GID2 direction is in the same direction as the corresponding local degree of freedom axis. For instance, in Figure 16, a CARTESIAN joint is illustrated with LOCK property applied. An SPC of 3.5 is applied at the outer CBUSH grid. The absolute value of the length of the joint is 2.0 and the length of the joint in local X direction when the local X axis is aligned with GID1 → GID2 is also equal to 2.0. The length of the joint in local X axis, when local X axis is opposite to GID1 → GID2 is equal to -2.0. A positive SPC value of 2.0 is applied in basic Y direction on the model. To lock the upper bound of the length of the joint at an absolute value of 2.2.

When local X is aligned with GID1 → GID2, the length is positive and to apply an absolute upper limit of 2.2, the upper bound field of LOCK should be set to 2.2.
When local X is opposite to GID1 → GID2, the length is negative and to apply an absolute upper limit of 2.2, the lower bound field of LOCK should be set to -2.2.

Based on the CARTESIAN joint example in Figure 16, you can infer the process of applying similar constraints on the length of other joints of other degrees of freedom of interest, depending on the interplay of GID1 → GID2 direction and the local axis direction of the degree of freedom of interest.

Composite Laminates

Shells and solid elements can be made of composites in which several layers of different materials (plies) are bonded together to form a cohesive structure.

Typically, the plies are made of unidirectional fibers or of woven fabrics and are joined together by a bonding medium (matrix). Composite Shells are modeled based on PCOMP, PCOMPP, or PCOMPG properties assigned to shell elements, while Continuum Shells are modeled based on PCOMPLS property assigned to solid elements. For Composite Shells, the plies are assumed to be laid in layers parallel to the middle plane of the shell. Each layer may have a different thickness and different orientation of fiber directions.

Figure 18. Four-layer Composite Shell with Ply Angle

Classical lamination theory is used to calculate effective stiffness and mass density of the composite shell. This is done automatically within the code using the properties of individual plies. The homogenized shell or solid properties are then used in the analysis.

After the analysis, the stresses and strains in the individual layers and between the layers can be calculated from the overall shell stresses and strains. These results may then be used to assess the failure indices of individual plies and of the bonding matrix.

Analysis of Composite Shells (PCOMP, PCOMPG, PCOMPP)

Analysis of composite shells is similar to the solution of standard shell elements. The primary difference is the use of the PCOMP, PCOMPP or PCOMPG property card, instead of PSHELL, to specify shell element properties.

From the ply information specified on the corresponding PCOMP, PCOMPG entries or from the PLY entries (in case of PCOMPP), OptiStruct automatically calculates the effective properties of the shell element.

After the analysis, the available results include shell-type stresses as well as stresses, strains, and failure indices for individual plies and their bonding. These results are controlled by the results flags on the PCOMP or PCOMPG entry and the typical I/O control cards, including CSTRESS, CSTRAIN, and CFAILURE entries.

In addition, for composite shells defined using PCOMP/PCOMPG/PCOMPP with Hashin/Puck failure criteria, the output of composite failure indices for all failure modes (fiber tension, fiber compression, matrix tension and matrix compression) are available through the CFAILURE entry.

Differences between PCOMP and PCOMPG
PCOMP and PCOMPG define the composite lay-up in two different ways.

PCOMP defines the structure and properties of a composite lay-up, which is then assigned to an element. The plies are only defined for a particular property and there is no relationship of plies that reach across several properties.

PCOMPG defines the structure and properties of a composite lay-up allowing for global ply identification which is then assigned to an element. The plies of different PCOMPG definitions can have a relationship because of the use of global ply IDs.
PCOMPP
PCOMPP allows ply-based modeling using PLY and STACK entries to define plies. The element sets to which plies are assigned are identified on the PLY entries via the ESID# fields. The stacking information and stacking sequence are defined via the STACK entries. Optionally, substacks and interface definitions are also possible using the STACK entries.

Some remarks regarding the specifics of composite analysis:

The most typical material type used for composite plies is MAT8, which is planar orthotropic material. The use of isotropic MAT1 or general anisotropic MAT2 for ply properties is also supported.
While it is possible to specify ply angles relative to the element coordinate system, the results become strongly dependent upon the node numbering in individual elements. Thus, it is advisable to specify a material coordinate system for composite elements and specify ply angles relative to this system.
Depending on the specific lay-up structure, the composite may be offset from the reference plane of the shell element, i.e. have more material below than above the reference plane (or vice versa).
Stress results for composites include both shell-type stresses and individual ply stresses. Importantly, shell-type stresses are calculated using homogenized properties and thus only represent the overall stress-state in the shell. To assess the actual stress-state in the composite, individual ply results need to be examined.

Analysis of Continuum Shells (PCOMPLS)

Continuum Shells can be effective in dealing with a three-dimensional stress state and/or if the laminate thickness is high enough that the classical shell theory limitations are met.

Analysis of Continuum Shells involves using the PCOMPLS entry to assign ply information to solid elements. This is currently supported only for CHEXA and CPENTA elements. For instance, the interlaminar normal stress ( $σ_{z z}$ ) is only available when Continuum Shells are used. Interlaminar shear stresses ( $σ_{z x}$ and $σ_{z y}$ ) are available in both Composite Shell and Continuum Shell laminates.

After the analysis, the available results include Layered Solid stresses, as well as stresses, strains, and failure indices for individual plies and their bonding. These results are controlled by the typical I/O control cards, including CSTRESS, CSTRAIN, and CFAILURE entries.

In addition, for continuum shells defined using PCOMPLS with Hashin/Puck failure criteria, the output of composite failure indices for all failure modes (fiber tension, fiber compression, matrix tension and matrix compression) are available through the CFAILURE entry.

Some remarks regarding the specifics of Continuum Shell analysis.

The material types supported for Continuum Shells are MAT1, MAT9, MAT9OR, and MATUSR materials.
While it is possible to specify ply angles relative to the element coordinate system, the results become strongly dependent upon the node numbering in individual elements. Thus, it is advisable to prescribe a material coordinate system for composite elements and specify ply angles relative to this system.

For more information, refer to Continuum Shells in the User Guide.

Continuum Shells

Continuum shells can provide some advantages over directly using shell elements for Composite laminates.

For composite laminates, there are two approaches to accomplish the modeling. One is directly using shell elements via the PCOMP/PCOMPP/PCOMPG properties, or you can use solid elements using Continuum Shells via the PCOMPLS property. For instance, for thicker laminates, or when the stress state is three-dimensional in the laminate, continuum shells may be a better choice for the simulation.

Input

Continuum shells can be activated by using CHEXA and CPENTA solid elements referenced by the PCOMPLS property entry. The various plies in the laminate can be listed on the PCOMPLS entry directly. The assumed strain enhanced formulation is used by default to help improve bending behavior. The ply material coordinate system is defined by the CORDM field, and is set to 0 by default (which indicates the basic system).

Note: The material coordinate system can also be defined on the CORDM continuation line of the corresponding element data.

(1)	(2)	(3)	(4)	(5)
PCOMPLS	`PID`		`CORDM`	`SB`
	`C8`		`INT8`
	`ID1`	`MID1`	`T1`	`THETA1`
	`ID2`	`MID2`	`T2`	`THETA2`

Output

The elemental results are output by default in the Ply material coordinate system (defined by CORDM on PCOMPLS or on the CORDM continuation line of the corresponding solid element entries). If CORDM is not provided on PCOMPLS or on the element entries, then the Basic Coordinate System is used by default. The Ply material system only uses the X-axis from the systems (CORDM or Default Basic system) and performs a projection of this X-axis onto the ply plane. The Z-axis is the thickness direction, and the cross product of X and Z-axes provides the Y-axis. Additionally, if the X-axis cannot be projected, then the Y-axis is projected and Z-axis is again the thickness directions. Now, X-axis is calculated from the Y and Z-axes.

Note: The thickness direction of the composite element by default starts from face G1-G2-G3-G4 to face G5-G6-G7-G8 of the solid element. Ply numbering also follows this thickness direction. This is used to only determine the direction of the local Z axis of the plies. The local Z-axis of each ply is perpendicular to the ply plane and aligned to the thickness direction.

Example Using `CORDM` on PCOMPLS

Elemental results are output by default in the ply material coordinate system. For Continuum Shells, the material coordinate system can be defined by either by the CORDM field on the PCOMPLS entry or the CORDM continuation line on the corresponding solid element. The following example uses a CHEXA element beam model which is referenced by PCOMPLS. The PCOMPLS assigns a single ply of thickness 5.0 to each element. Isotropic material properties are used via the MAT1 entry.

Here you will consider the effect of the CORDM field in PCOMPLS on the elemental output. To clearly determine if the CORDM field is being respected for elemental stress output, you will consider four variations of the model:

Model 1
model_1_blank_cordm.fem

PCOMPLS with blank CORDM
Model 2
model_2_rotated_user_cordm.fem

Model 1 is rotated by 90° about Y-axis.

Additionally, PCOMPLS with CORDM defined referring to CORD2R (X-axis can be projected).

Figure 21. Projected X-axis of CORDM on PCOMPLS
Model 3
model_3_rotated_user_cordm.fem

Model 1 is rotated by 90° about Y-axis.

Additionally, PCOMPLS with CORDM defined referring to CORD2R (X-axis cannot be projected).

Figure 22. Non-Projected X-axis of CORDM on PCOMPLS
Model 4
model_4_rotated_blank_cordm.fem

Model 1 is rotated by 90° about Y-axis.

Additionally, PCOMPLS with blank CORDM.

Figure 23. (a) Model 1: Blank CORDM on PCOMPLS (basic system); (b) Model 2: Rotated model with CORDM on PCOMPLS (local system with CORD2R); . (c) Model 3: Rotated model with CORDM on PCOMPLS (local system with CORD2R); (d) Model 4: Rotated model with blank CORDM on PCOMPLS (basic system)

As mentioned in Output, the elemental stress results are output in the Material Coordinate system for Continuum Shells. This can be illustrated by the four models listed above and in the interpretation of results (Figure 23).

In Model 1, the basic X-axis is projected onto the plane of G1-G2-G3-G4 for each element. As an example, you can see the G1-G2-G3-G4 plane for element 208 (Figure 24).

For Model 1, Figure 24 also illustrates how the local material system is generated for element 208 from the basic system (since in Model 1, the CORDM field is blank). Similarly, for Model 2 (Figure 25), instead of the basic system, since CORDM is specified, the user-defined CORDM is projected to create local material systems for each element. Figure 21 shows the CORDM system specified for Model 2, clearly the X-axis can be projected on G1-G2-G3-G4 plane and the thickness direction is along the CORDM Z, as well. Therefore, the local material Y-axis is defined as the cross product of Z and X-axes.

In Figure 24 and Figure 25, you can expect that the Stress output in Material X-axis for Model 1 should be identical to the Stress output in Material Y-axis for Model 2.

Note: Both of these axes are along the length of the beam. This is evident from the matching contours and stress values in Figure 23(a) and (b).

In Figure 24 and Figure 26, you can expect that the Stress output in Material X-axis for Model 1 should be identical to the Stress output in Material X-axis for Model 3.

Note: Both of these axes are along the length of the beam. Again, this is evident from the matching contours and stress values in Figure 23(a) and (c).

In Figure 24 and Figure 27, you can expect that the Stress output in Material X-axis for Model 1 should be identical to the Stress output in Material Y-axis for Model 4.

Note: Both of these axes are along the length of the beam. Again, this is evident from the matching contours and stress values in Figure 23(a) and (d).

The calculation of the local Material system for Continuum shell elements depends on the definition of the CORDM field on PCOMPLS or the CORDM continuation line on the element entries (CHEXA entry). The following table summarizes these options and also illustrates the difference between how the material system is calculated for elements referenced by PSOLID or PCOMPLS.

		Generation of Local Material Coordinate Systems
Input Data		PSOLID	PCOMPLS
`CORDM` field on Property PCOMPLS	`CORDM`=0 or blank (Basic System)	Basic System is used directly (No projection)	The X-axis of the Basic System is projected. ³ The Z-axis is always in the Thickness Direction. ⁴ The Y-axis is the cross-product of these material Z and X-axes. ⁵
	`CORDM`=-1 (Elemental System)	Elemental System1 is used directly (No projection)	The X-axis of the Elemental System ⁶ is projected. ³ The Z-axis is always in the Thickness Direction. ⁴ The Y-axis is the cross-product of these material Z and X-axes. ⁵
	`CORDM`=Integer (User-defined System)	User-defined System is used directly (No projection)	The X-axis of the User-defined System is projected. ³ The Z-axis is always in the Thickness Direction. ⁴ The Y-axis is the cross-product of these material Z and X-axes. ⁵
`CORDM` continuation line on element card (CHEXA)	`CID`=0 (Basic System)	Basic System is used directly (No projection)	The X-axis of the Basic System is projected. ³ The Z-axis is always in the Thickness Direction. ⁴ The Y-axis is the cross-product of these material Z and X-axes. ⁵
	`CID`=-1 (Elemental System)	Elemental System ¹ is used directly (No projection)	The X-axis of the Elemental System6 is Projected. ³ The Z-axis is always in the Thickness Direction. ⁴ The Y-axis is the cross-product of these material Z and X-axes. ⁵
	`CID` (User-defined System)	User-defined System is used directly (No projection)	The X-axis of the User-defined System is projected. ³ The Z-axis is always in the Thickness Direction. ⁴ The Y-axis is the cross-product of these material Z and X-axes. ⁵
	`THETA`/`PHI`	The Elemental System ¹ is rotated based on `THETA`/`PHI` ² (No projection)	The X-axis of the Rotated Elemental System ⁷ is projected. ³ The Z-axis is always in the Thickness Direction. ⁴ The Y-axis is the cross-product of these material Z and X-axes. ⁵

Interpretation of Results for Composites

Several composite-specific results are calculated for composite shell and continuum shell elements. Due to the specialized nature of these results, some explanation is provided regarding their meaning.

Ply Stresses and Strains (CSTRESS and CSTRAIN entries)
Classical lamination theory assumes two-dimensional stress-state in individual plies (so-called membrane state) for composite shells. The values of stresses and strains are calculated at the mid-plane of each ply, i.e. halfway between its upper and lower surface. For sufficiently thin plies, these values can be interpreted as representing uniform stress in the ply.

For composite shells, ply stresses and strains are calculated in coordinate systems aligned with ply material angles as specified on the corresponding composite property card. In particular, $σ_{1}$ correspond to the primary ply direction, $σ_{2}$ is orthogonal to it, and $τ_{12}$ represents in-plane shear stress.

Composite materials typically have a low matrix Young’s modulus in comparison to the fiber modulus. Since the matrix is the bonding material in between plies, a shearing effect on the laminate is built up by the contributions of each interlaminar zone of the matrix. Because the longitudinal and transverse shear moduli is relatively lower than the longitudinal and transverse Young’s modulus, the effect of transverse shear stresses are important in composite panels than for isotropic plates. The theory behind the calculation of transverse shear stress is given in the subsequent section.

Ply stresses and strains can also be calculated at planes between the top and bottom planes of each ply. The NDIV field on the CSTRESS and CSTRAIN entries can be used to request the corresponding results for the required planes.
Inter-laminar Stress
Inter-laminar bonding matrix usually has different material properties and stress-state than the individual plies. For composite shells, the primary stress that is of importance here is inter-laminar shear with two components: $τ_{1 z}$ and $τ_{2 z}$ . For continuum shells, in addition to interlaminar shear, interlaminar normal stress ( $σ_{3}$ ) at the interface between plies is also available.
Failure Indices
To facilitate prediction of potential failure of the laminate, failure indices are calculated for plies and bonding material. While there are several theories available for such calculations, their common feature is that failure indices are scaled relative to allowable stresses or strains, so that:
- the value of a failure index lower than 1.0 indicates that the stress/strain is within the allowable limits (as specified on the material data card), and
- a failure index above 1.0 indicates that the allowable stress/strain has been exceeded.
- according to the formula, some failure criteria (for example, Tsai-Wu and Hoffman) would produce the negative ply failure, depending on the problem.

Failure Criteria for Composite Laminated Shells

Hill's Theory of Ply Failure

The CRITERIA field on MATF or FT field of PCOMP/PCOMPP/PCOMPG should be set to HILL.

According to Hill's theory, the ply failure index is calculated as:(10)

$F_{i n d e x} = \frac{σ_{1}^{2}}{X^{2}} - \frac{σ_{1} σ_{2}}{X^{2}} + \frac{σ_{2}^{2}}{Y^{2}} + \frac{τ_{12}^{2}}{S^{2}}$

Where,

$X$: The allowable stress in the ply material direction (1).
$Y$: The allowable stress in the ply material direction (2).
$S$: The allowable in-plane shear stress.

Note: Hill's theory does not differentiate between tension and compression stresses and it is strongly recommended to use the same values for both allowable stresses.

On MAT8 entry, $X_{t} = X_{c} = X$ and $Y_{t} = Y_{c} = Y$ , $S = S$ . If this suggestion is not adopted, warning messages will be output and the following rules will be applied: If $σ_{1} > 0.0$ , $X = X_{t}$ ; otherwise, $X = X_{c}$ , and similarly for $Y$ and $σ_{2}$ . For the interaction term, if $σ_{1} σ_{2} > 0.0$ , $X = X_{t}$ ; otherwise, $X = X_{c}$ .

On MATF entry, $V 1 = X$ , $V 3 = Y$ , $V 5 = S$

Hoffman's Theory of Ply Failure

The CRITERIA field on MATF or FT field of PCOMP/PCOMPP/PCOMPG should be set to HOFF.

In Hoffman's theory, the ply failure index is calculated as:(11)

$F_{i n d e x} = (\frac{1}{X_{t}} - \frac{1}{X_{c}}) σ_{1} + (\frac{1}{Y_{t}} - \frac{1}{Y_{c}}) σ_{2} + \frac{σ_{1}^{2}}{X_{t} X_{c}} + \frac{σ_{2}^{2}}{Y_{t} Y_{c}} - \frac{σ_{1} σ_{2}}{X_{t} X_{c}} + \frac{τ_{12}^{2}}{S^{2}}$

On MAT8 entry, $X_{t} = X_{t}$ , $X_{c} = X_{c}$ , $Y_{t} = Y_{t}$ , $Y_{c} = Y_{c}$ , $S = S$

On MATF entry, $V 1 = X_{t}$ , $V 2 = X_{c}$ , $V 3 = Y_{t}$ , $V 4 = Y_{c}$ , $V 5 = S$

Tsai-Wu Theory of Ply Failure

The CRITERIA field on MATF or FT field of PCOMP/PCOMPP/PCOMPG should be set to TSAI.

In Tsai-Wu theory, the ply failure index is calculated as:(12)

$F_{i n d e x} = (\frac{1}{X_{t}} - \frac{1}{X_{c}}) σ_{1} + (\frac{1}{Y_{t}} - \frac{1}{Y_{c}}) σ_{2} + \frac{σ_{1}^{2}}{X_{t} X_{c}} + \frac{σ_{2}^{2}}{Y_{t} Y_{c}} + \frac{τ_{12}^{2}}{S^{2}} + 2 F_{12} σ_{1} σ_{2}$

Where, $F_{12}$ is a factor to be determined experimentally.

On MAT8 entry, $X_{t} = X_{t}$ , $X_{c} = X_{c}$ , $Y_{t} = Y_{t}$ , $Y_{c} = Y_{c}$ , $S = S$ , $F_{12} = F_{12}$

On MATF entry, $V 1 = X_{t}$ , $V 2 = X_{c}$ , $V 3 = Y_{t}$ , $V 4 = Y_{c}$ , $V 5 = S$

Maximum Strain Theory of Ply Failure

The CRITERIA field on MATF or FT field of PCOMP/PCOMPP/PCOMPG should be set to STRN.

In maximum strain theory, the ply failure index is calculated as the maximum ratio of ply strains to allowable strains:(13)

$F_{i n d e x} = \max (| \frac{ε_{1}}{X} |, | \frac{ε_{2}}{Y} |, | \frac{γ_{12}}{S} |)$

Where,

$X$: The allowable strain in the ply material direction (1).
$Y$: The allowable strain in the ply material direction (2).
$S$: The allowable in-plane engineering shear strain.

If you provide different values of

$X$ and

$Y$ for tension and compression, the appropriate values are used depending on the signs of

$ε_{1}$ and

$ε_{2}$ , respectively.

Note: If you set allowable stresses rather than strains on the material data card, the allowable strains are calculated via simple division by the relevant material module.

On MAT8 entry, $X_{t} or X_{c} = X$ , $Y_{t} or Y_{c} = Y$ , $S = S$ . The STRN field can be used to identify whether input values are stress or strain allowables.

On MATF entry, $V 1 or V 2 = X$ , $V 3 or V 4 = Y$ , $V 5 = S$ .

Maximum Stress Theory of Ply Failure

The CRITERIA field on MATF should be set to STRS.

In maximum stress theory, the ply failure index is calculated as the maximum ratio of ply stresses to allowable stresses.(14)

$F_{i n d e x} = \max (| \frac{σ_{1}}{X} |, | \frac{σ_{2}}{Y} |, | \frac{σ_{12}}{S} |)$

Where,

$X$: The allowable stress in the ply material direction (1).
$Y$: The allowable stress in the ply material direction (2).
$S$: The allowable in-plane engineering shear stress.

If you provide different values of

$X$ and

$Y$ for tension and compression, the appropriate values are used depending on the signs of

$σ_{1}$ and

$σ_{2}$ , respectively.

On MATF entry, $V 1 or V 2 = X$ , $V 3 or V 4 = Y$ , $V 5 = S$ .

Bonding Material Failure

The primary failure mode of the bonding material is due to inter-laminar shear. The corresponding failure index is calculated as:(15)

$F_{i n d e x} = \frac{\max (| τ_{1 z} |, | τ_{2 z} |)}{S_{B}}$

Where, $S_{B}$ is the allowable shear in the bonding material.

On PCOMP/PCOMPP/PCOMPG entry, $S B = S_{B}$

Hashin Failure Criteria

The CRITERIA field on MATF or FT field of PCOMP/PCOMPP/PCOMPG should be set to HASH.

The Hashin Failure criteria is calculated for four basic failure modes: in fiber tension, fiber compression, matrix tension, and matrix compression and the failure indices are output for all modes separately.

The corresponding failure indices are calculated as:

Fiber Tension ( $σ_{1} > 0$ )(16) $F_{f i b e r}^{T} = {(\frac{σ_{1}}{σ_{1}^{A T}})}^{2} + {(\frac{τ_{12}}{τ_{12 L}^{A}})}^{2}$
Fiber Compression ( $σ_{1} < 0$ )(17) $F_{f i b e r}^{C} = | \frac{σ_{1}}{σ_{1}^{A C}} |$
Matrix Tension ( $σ_{2} > 0$ )(18) $F_{m a t r i x}^{T} = {(\frac{σ_{2}}{σ_{2}^{A T}})}^{2} + {(\frac{τ_{12}}{τ_{12 L}^{A}})}^{2}$
Matrix Compression ( $σ_{2} < 0$ )(19) $F_{m a r i x}^{C} = {(\frac{σ_{2}}{2 τ_{12 T}^{A}})}^{2} + {(\frac{τ_{12}}{τ_{12 L}^{A}})}^{2} + [{(\frac{σ_{2}^{A C}}{2 τ_{12 T}^{A}})}^{2} - 1] \frac{σ_{2}}{σ_{2}^{A C}}$

Where,

$σ_{1}^{A T}$: The allowable homogenized longitudinal tension strength of the composite.
$σ_{1}^{A C}$: The allowable homogenized longitudinal compression strength of the composite.
$σ_{2}^{A T}$: The allowable homogenized transverse tension strength of the composite.
$σ_{2}^{A C}$: The allowable homogenized transverse compression strength of the fibers.
$τ_{12 L}^{A}$: The allowable homogenized longitudinal shear strength of the composite.
$τ_{12 T}^{A}$: The allowable homogenized transverse shear strength of the composite, defined by the Hashin approximation: (20) $τ_{12 L}^{A} = τ_{12 T}^{A}$
$σ_{1}$: The stress in the 1-direction.
$σ_{2}$: The stress in the 2-direction.
$τ_{12}$: The shear stress in 1-2 plane.

On MAT8 entry, $X_{t} = σ_{1}^{A T}$ , $X_{c} = σ_{1}^{A C}$ , $Y_{t} = σ_{2}^{A T}$ , $Y_{c} = σ_{2}^{A C}$ , $S = τ_{12 L}^{A} = τ_{12 T}^{A}$ .

On MATF entry, $V 1 = σ_{1}^{A T}$ , $V 2 = σ_{1}^{A C}$ , $V 3 = σ_{2}^{A T}$ , $V 4 = σ_{2}^{A C}$ , $V 5 = τ_{12 L}^{A}$ .

Puck Failure Criteria

The CRITERIA field on MATF or FT field of PCOMP/PCOMPP/PCOMPG should be set to PUCK.

The Puck failure criteria is calculated for two basic failure modes based on 2D plane stress, in fiber failure mode and inter-fiber failure mode. The failures indices are output separately for all these failure modes.

The allowable material data should be specified on the MATF Bulk Data Entry for Puck Failure Criterion. The corresponding failure indices are calculated as:

Fiber Failure Mode:

Fiber Tension ( $σ_{11} > 0$ )(21) $F_{f i b e r}^{T} = \frac{σ_{11}}{σ_{1}^{T}}$
Fiber Compression ( $σ_{11} < 0$ )(22) $F_{f i b e r}^{C} = \frac{| σ_{11} |}{σ_{1}^{C}}$

Inter-Fiber Failure Mode:

Mode A ( $σ_{22} > 0$ )(23) $F_{i n t e r}^{A} = \sqrt{{(\frac{τ_{12}}{τ})}^{2} + {(1 - P_{12}^{+} \frac{σ_{2}^{T}}{τ})}^{2} {(\frac{σ_{22}}{σ_{2}^{T}})}^{2}} + P_{12}^{+} \frac{σ_{22}}{τ}$
Mode B ( $σ_{22} < 0$ )(24) $F_{i n t e r}^{B} = \frac{1}{τ} (\sqrt{τ_{12}^{2} + {(P_{12}^{-} σ_{22})}^{2}} + P_{12}^{-} σ_{22})$
Mode C ( $σ_{22} < 0$ )(25) $F_{i n t e r}^{C} = ({(\frac{τ_{12}}{2 (1 + P_{22}^{-}) τ})}^{2} + {(\frac{τ_{12}}{σ_{2}^{C}})}^{2}) (\frac{σ_{2}^{C}}{- σ_{22}})$

Where,

$σ_{1}^{T}$: The allowable longitudinal tension strength.
$σ_{1}^{C}$: The allowable longitudinal compression strength.
$σ_{2}^{T}$: The allowable transverse tension strength.
$σ_{2}^{C}$: The allowable transverse compression strength.
$τ$: The allowable shear strength.
$σ_{1}$: The stress in the 1-direction.
$σ_{2}$: The stress in the 2-direction.
$τ_{12}$: The shear stress in 1-2 plane.
$P_{12}^{+}$: The failure envelope factor 12(+).
$P_{12}^{-}$: The failure envelope factor 12(-).
$P_{22}^{-}$: The failure envelope factor 22(-).

On MATF entry, $V 1 = σ_{1}^{T}$ , $V 2 = σ_{1}^{C}$ , $V 3 = σ_{2}^{T}$ , $V 4 = σ_{2}^{C}$ , $V 5 = τ$ , $W 1 = P_{12}^{-}$ , $W 2 = P_{12}^{+}$ , $W 3 = P_{22}^{-}$ .

The output results of failure mode for Hashin and Puck failure criterion are mutually exclusive. For example, a specified ply cannot fail due to tension and compression simultaneously. In such cases, the result plot for the other failure modes of the ply are not valid and this situation is represented by the notation – N/A, on the result plot.

Final Failure Index for Composite Element

After calculation of failure indices for individual plies, the potential failure index for the composite shell element is obtained. This is based on the premise that failure of a single layer qualifies as failure of the composite. Thus, the failure index for composite element is calculated as the maximum of all computed ply and bonding failure indices.

Note: Only plies with requested stress output are taken into account here.

Failure Criteria for Composite Anisotropic Solid and Continuum Shell Elements

The available criteria for continuum shells (PCOMPLS) are:

HILL3D
PUCK3D
HOFF3D
TSAI3D
HASH3D
STRN3D
STRS3D
CNTZ3D

The available criteria for anisotropic solid elements (MAT9OR) are:

HILL3D
HOFF3D
TSAI3D
STRN3D
STRS3D

The details of each failure criteria are presented in this section.

The normal stresses, $σ_{i}$ $(i = 1, 2, 3)$ , and shear stresses, $τ_{i j}$ $(i, j = 1, 2, 3; i \neq j)$ , are in the material coordinate system (solid elements with MAT9/MAT9OR) or in fiber coordinate system (PCOMPLS).

The symbols

$X^{t}$ ,

$Y^{t}$ , and

$Z^{t}$ are normal tension stress limits in 1-1, 2-2 and 3-3 direction, respectively. The symbols

$X^{c}$ ,

$Y^{c}$ , and

$Z^{c}$ are normal compression stress limits in 1-1, 2-2 and 3-3 direction, respectively.

$S_{12}$ ,

$S_{23}$ and

$S_{13}$ are the shear stress limits in 1-2 plane, 2-3 plane and 1-3 plane, respectively.

Note: The assumption,

$Z^{t} = Y^{t}$ ,

$Z^{c} = Y^{c}$ , is only valid for transversely isotropic materials, and hence is not used for failure criteria calculations for solid anisotropic composite MAT9/MAT9OR elements or for continuum shell PCOMPLS elements. Therefore, as this assumption is not used, the V5 and V6 fields on MATF entry are also used for failure criteria calculations.

Hill Criteria

On MATF, set CRITERIA to HILL3D.

The failure index,

$f$ , is calculated as:(26)

$f = F {(σ_{2} - σ_{3})}^{2} + G {(σ_{3} - σ_{1})}^{2} + H {(σ_{1} - σ_{2})}^{2} + L τ_{12}^{2} + M τ_{23}^{2} + N τ_{13}^{2}$

Where,

$F = \frac{1}{2} (C_{22} + C_{33} - C_{11})$
$G = \frac{1}{2} (C_{33} + C_{11} - C_{22})$
$H = \frac{1}{2} (C_{11} + C_{22} - C_{33})$

$C_{11} = {(\frac{1}{X^{t}})}^{2}$ or ${(\frac{1}{X^{c}})}^{2}$ , depending on $σ_{1}$ in tension or compression.

$C_{22} = {(\frac{1}{Y^{t}})}^{2}$ or ${(\frac{1}{Y^{c}})}^{2}$ , depending on $σ_{2}$ in tension or compression.

$C_{33} = {(\frac{1}{Z^{t}})}^{2}$ or ${(\frac{1}{Z^{c}})}^{2}$ , depending on $σ_{3}$ in tension or compression.

$L = {(\frac{1}{S_{12}})}^{2}$ , $M = {(\frac{1}{S_{23}})}^{2}$ , $N = {(\frac{1}{S_{13}})}^{2}$ .

On the MATF Bulk Data Entry,

V1: $X^{t}$
V2: $X^{c}$
V3: $Y^{t}$
V4: $Y^{c}$
V5: $Z^{t}$
V6: $Z^{c}$
V7: $S_{12}$
V8: $S_{23}$
V9: $S_{13}$

Hoffman Criteria

On MATF, set CRITERIA to HOFF3D.

The failure index,

$f$ , is calculated as:(27)

$f = F {(σ_{2} - σ_{3})}^{2} + G {(σ_{3} - σ_{1})}^{2} + H {(σ_{1} - σ_{2})}^{2} + I σ_{1} + J σ_{2} + K σ_{3} + L τ_{12}^{2} + M τ_{23}^{2} + N τ_{13}^{2}$

Where,

$F = \frac{1}{2} [(\frac{1}{Y^{t} Y^{c}}) + (\frac{1}{Z^{t} Z^{c}}) - (\frac{1}{X^{t} X^{c}})]$
$G = \frac{1}{2} [(\frac{1}{Z^{t} Z^{c}}) + (\frac{1}{X^{t} X^{c}}) - (\frac{1}{Y^{t} Y^{c}})]$
$H = \frac{1}{2} [(\frac{1}{X^{t} X^{c}}) + (\frac{1}{Y^{t} Y^{c}}) - (\frac{1}{Z^{t} Z^{c}})]$
$I = \frac{1}{X^{t}} - \frac{1}{X^{c}}$
$J = \frac{1}{Y^{t}} - \frac{1}{Y^{c}}$
$K = \frac{1}{Z^{t}} - \frac{1}{Z^{c}}$
$L = {(\frac{1}{S_{12}})}^{2}$
$M = {(\frac{1}{S_{23}})}^{2}$
$N = {(\frac{1}{S_{13}})}^{2}$

On the MATF Bulk Data Entry,

V1: $X^{t}$
V2: $X^{c}$
V3: $Y^{t}$
V4: $Y^{c}$
V5: $Z^{t}$
V6: $Z^{c}$
V7: $S_{12}$
V8: $S_{23}$
V9: $S_{13}$

Tsai-Wu Criteria

On MATF, set CRITERIA to TSAI3D.

The failure index,

$f$ , is calculated as:(28)

$\begin{array}{l} f = C_{11} σ_{1}^{2} + C_{22} σ_{2}^{2} + C_{33} σ_{3}^{2} + C_{44} τ_{12}^{2} + C_{55} τ_{23}^{2} + C_{66} τ_{13}^{2} + 2 C_{23} σ_{2} σ_{3} + 2 C_{13} σ_{1} σ_{3} + 2 C_{12} σ_{1} σ_{2} + \\ C_{1} σ_{1} + C_{2} σ_{2} + C_{3} σ_{3} \end{array}$

Where,

$C_{1} = \frac{1}{X^{t}} - \frac{1}{X^{c}}$
$C_{2} = \frac{1}{Y^{t}} - \frac{1}{Y^{c}}$
$C_{3} = \frac{1}{Z^{t}} - \frac{1}{Z^{c}}$
$C_{11} = \frac{1}{X^{t} X^{c}}$
$C_{22} = \frac{1}{Y^{t} Y^{c}}$
$C_{33} = \frac{1}{Z^{t} Z^{c}}$
$C_{44} = {(\frac{1}{S_{12}})}^{2}$
$C_{55} = {(\frac{1}{S_{23}})}^{2}$
$C_{66} = {(\frac{1}{S_{13}})}^{2}$
$C_{12}$ , $C_{23}$ , $C_{13}$: Defined in MATF card as V10, V11 and V12, respectively.

If V10, V11 and V12 are blank, the coupling coefficients are calculated by:(29)

$C_{i j} = \frac{1}{2 b_{i j}^{2}} [1 - b_{i j} (C_{i} + C_{j}) - b_{i j}^{2} (C_{i i} + C_{j j})]$

Where, $i, j = 1, 2, 3; i \neq j$ and the $b_{i j}$ terms are the tensile stress limits in equal-biaxial tension tests.

On the MATF Bulk Data Entry,

W1: $b_{12}$
W2: $b_{23}$
W3: $b_{13}$

W1 is the tension stress limit in equal-biaxial tests where the two tension loads are in directions 1 and 2. W1 is mandatory, while W2 and W3 are optional. If W2 and W3 are not specified, then they are set equal to W1. The definition of W2 and W3 is similar to W1. W2 is the tension stress limit in equal-biaxial tension tests where the two tension loads are in directions 2 and 3. W3 is the tension stress limit in equal-biaxial tension tests where the two tension loads are in directions 1 and 3.

In Tsai-Wu criteria, the following conditions must be met:(30)

$C_{i i} C_{j j} - C_{i j}^{2} \geq 0$

On the MATF Bulk Data Entry,

V1: $X^{t}$
V2: $X^{c}$
V3: $Y^{t}$
V4: $Y^{c}$
V5: $Z^{t}$
V6: $Z^{c}$
V7: $S_{12}$
V8: $S_{23}$
V9: $S_{13}$
W1: $b_{12}$
W2: $b_{23}$
W3: $b_{13}$

If V10, V11, V12, W1, W2 and W3 are all blank, the coupling coefficients $C_{12}$ , $C_{23}$ , and $C_{13}$ are 0.0.

Maximum Strain Criteria

On MATF, set CRITERIA to STRN3D.

The failure index is taken as the maximum value from the following 6 values:(31)

$f = \max_{i = 1 ~ 6} (f_{i})$

$f_{i} = | \frac{ε_{i}}{C_{i i}} |$ $i = 1, 2, 3$

$f_{4} = | \frac{ε_{12}}{C_{12}} |$ ,

$f_{5} = | \frac{ε_{23}}{C_{23}} |$ ,

$f_{6} = | \frac{ε_{13}}{C_{13}} |$

$C_{i i}$: Strain limit in $i - i$ direction. It can be taken as tension or compression strain limit, depending on the sign of corresponding normal strain ( $C_{11}$ = $X^{t}$ or $X^{c}$ ; $C_{22}$ = $Y^{t}$ or $Y^{c}$ ; and $C_{33}$ = $Z^{t}$ or $Z^{c}$ ).; $C_{12}$ is the strain limit in 1-2 direction, $C_{23}$ is the strain limit in 2-3 direction, $C_{13}$ is the strain limit in 1-3 direction ( $C_{12} = S_{12}$ , $C_{23} = S_{23}$ , $C_{13} = S_{13}$ )

On the MATF Bulk Data Entry,

V1: $X^{t}$
V2: $X^{c}$
V3: $Y^{t}$
V4: $Y^{c}$
V5: $Z^{t}$
V6: $Z^{c}$
V7: $S_{12}$
V8: $S_{23}$
V9: $S_{13}$

In continuum shell elements (PCOMPLS), the above four criteria are available, $Z^{t} = Y^{t}$ , and $Z^{c} = Y^{c}$ . Also, the Hashin, Puck and Cuntze criteria can be used.

Maximum Stress Criteria

The CRITERIA field on MATF should be set to STRS3D.

The failure index is taken as the maximum value from the following 6 values:(32)

$f = \max_{i = 1 ~ 6} (f_{i})$

$f_{i} = | \frac{σ_{i}}{C_{i i}} |$ , $i = 1, 2, 3$

$f_{4} = | \frac{σ_{12}}{C_{12}} |$ ,

$f_{5} = | \frac{σ_{23}}{C_{23}} |$ ,

$f_{6} = | \frac{σ_{13}}{C_{13}} |$

$C_{i i}$: Stress limit in $i - i$ direction. It can be taken as tensile or compressive stress limit, depending on the sign of corresponding normal stress ( $C_{11}$ = $X^{t}$ or $X^{c}$ , $C_{22}$ = $Y^{t}$ or $Y^{c}$ , and $C_{33}$ = $Z^{t}$ or $Z^{c}$ ).

On the MATF Bulk Data Entry, V1 = $X^{t}$ , V2 = $X^{c}$ , V3 = $Y^{t}$ , V4 = $Y^{c}$ , V5 = $Z^{t}$ , V6 = $Z^{c}$ , V7 = $S_{12}$ , V8 = $S_{23}$ , and V9 = $S_{13}$ .

In continuum shell elements (PCOMPLS), the above five criteria are available. Besides, three additional criteria, which are only available for PCOMPLS can be used: Hashin, Puck and Cuntze.

Hashin Criteria

On MATF, set CRITERIA to HASH3D.

In Hashin failure criteria, four failure modes are distinguished:

Fiber Tension
Fiber Compression
Matrix Tension
Matrix Compression

All four modes are checked, and all four failure indices are output separately. The four failure indices corresponding to the four modes are expressed as:

Fiber Tension ( $σ_{1} > 0$ )(33) $f_{1} = {(\frac{σ_{1}}{X^{t}})}^{2} + α {(\frac{1}{S_{12}})}^{2} (τ_{12}^{2} + τ_{13}^{2}) \leq 1$
Where, α is a user-defined empirical parameter. This is used to define the contribution of transverse shear stress taken into account in the Fiber Tension mode. The coefficient α is automatically set as 1.0, if W1 is left as blank in the MATF card.
Fiber Compression ( $σ_{1} < 0$ )(34) $f_{2} = | \frac{σ_{1}}{X^{c}} |$
Matrix Tension ( $σ_{2} + σ_{3} > 0$ )(35) $f_{3} = {(\frac{σ_{2} + σ_{3}}{Y^{t}})}^{2} + {(\frac{1}{S_{23}})}^{2} (τ_{23}^{2} - σ_{2} σ_{3}) + {(\frac{1}{S_{12}})}^{2} (τ_{12}^{2} + τ_{13}^{2})$
Matrix Compression ( $σ_{2} + σ_{3} < 0$ )(36) $f_{4} = \frac{1}{Y^{c}} [{(\frac{Y^{c}}{2 S_{23}})}^{2} - 1] (σ_{2} + σ_{3}) + {(\frac{1}{2 S_{23}})}^{2} {(σ_{2} + σ_{3})}^{2} + {(\frac{1}{S_{23}})}^{2} (τ_{23}^{2} - σ_{2} σ_{3}) + {(\frac{1}{S_{12}})}^{2} (τ_{12}^{2} + τ_{13}^{2})$

On the MATF Bulk Data Entry,

V1: $X^{t}$
V2: $X^{c}$
V3: $Y^{t}$
V4: $Y^{c}$
V5: $Z^{t}$
V6: $Z^{c}$
V7: $S_{12}$
V8: $S_{23}$
V9: $S_{13}$
W1: $α$ which is used in fiber tension failure check

Puck Criteria

On MATF, set CRITERIA to PUCK3D.

Five failure modes are distinguished in PUCK failure criteria.

Fiber Tension Mode ( $σ_{1} > 0$ )(37) $f_{1} = | \frac{σ_{1}}{σ_{1}^{t}} |$
Fiber Compression Mode ( $σ_{1} < 0$ )(38) $f_{2} = | \frac{σ_{1}}{σ_{1}^{c}} |$
Inter-Fiber check 1 ( $σ_{n} > 0$ )(39) $f (θ) = \sqrt{{(\frac{1}{Y^{t}} - \frac{p_{2 φ}^{+}}{R_{2 φ}^{A}})}^{2} σ_{n}^{2} + {(\frac{τ_{n t}}{R_{⊥ ⊥}^{A}})}^{2} + {(\frac{τ_{n 1}}{S_{12}})}^{2}} + \frac{p_{2 φ}^{+}}{R_{2 φ}^{A}} σ_{n}$
Inter-Fiber check 2 ( $σ_{n} < 0$ )(40) $f (θ) = \sqrt{{(\frac{τ_{n t}}{R_{⊥ ⊥}^{A}})}^{2} + {(\frac{τ_{n 1}}{S_{12}})}^{2} + {(\frac{p_{2 φ}^{-}}{R_{2 φ}^{A}} σ_{n})}^{2}} + \frac{p_{2 φ}^{-}}{R_{2 φ}^{A}} σ_{n}$
Where,

$\frac{p_{2 φ}^{+}}{R_{2 φ}^{A}} = {\begin{matrix} \frac{1}{τ_{n t}^{2} + τ_{n 1}^{2}} (\frac{p_{22}^{+}}{R_{⊥ ⊥}^{A}} τ_{n t}^{2} + \frac{p_{12}^{+}}{R_{⊥ ∥}^{A}} τ_{n 1}^{2}) if τ_{n t}^{2} + τ_{n 1}^{2} > 0 \\ 0 if τ_{n t}^{2} + τ_{n 1}^{2} = 0 \end{matrix}$

$\frac{p_{2 φ}^{-}}{R_{2 φ}^{A}} = {\begin{matrix} \frac{1}{τ_{n t}^{2} + τ_{n 1}^{2}} (\frac{p_{22}^{-}}{R_{⊥ ⊥}^{A}} τ_{n t}^{2} + \frac{p_{12}^{-}}{R_{⊥ ∥}^{A}} τ_{n 1}^{2}) if τ_{n t}^{2} + τ_{n 1}^{2} > 0 \\ 0 if τ_{n t}^{2} + τ_{n 1}^{2} = 0 \end{matrix}$

$R_{⊥ ⊥}^{A} = \frac{S_{12}}{2 p_{12}^{-}} (\sqrt{1 + 2 p_{12}^{-} \frac{p_{22}^{-}}{S_{12}}} - 1)$

$σ_{n} = \frac{σ_{2} + σ_{3}}{2} - \frac{σ_{2} - σ_{3}}{2} \cos 2 θ - τ_{23} \sin 2 θ$

$τ_{n t} = \frac{σ_{3} - σ_{2}}{2} \sin 2 θ + \frac{τ_{23}}{2} \cos 2 θ$

$τ_{1 n} = τ_{12} \cos 2 θ + τ_{13} \sin 2 θ$

$p_{12}^{-}$ , $p_{12}^{+}$ , $p_{22}^{-}$ , and $p_{22}^{+}$

Coefficients for the envelope of failure curve, and they should be provided by users in the MATF card as W1, W2, W3, and W4, respectively.

A search on the critical failure plane is performed automatically from -90° to 90° at every 1°.

On the MATF Bulk Data Entry,

V1: $X^{t}$
V2: $X^{c}$
V3: $Y^{t}$
V4: $Y^{c}$
V5: $Z^{t}$
V6: $Z^{c}$
V7: $S_{12}$
V8: $S_{23}$
V9: $S_{13}$
W1: $p_{12}^{-}$
W2: $p_{12}^{+}$
W3: $p_{22}^{-}$
W4: $p_{22}^{+}$

Cuntze Criteria

On MATF, set CRITERIA to CNTZ3D.

In Cuntze failure criteria, five potential failure modes (two fiber failure modes and three inter-fiber failure modes) are calculated separately, and a stress effort is obtained for each mode. The final failure index is calculated, based on the stress effort of each mode.

FF1 (41) $E f f_{1} = \frac{σ_{1}}{X^{t}}$
FF2 (42) $E f f_{2} = \frac{- σ_{1}}{X^{c}}$
IFF1(43) $E f f_{3} = \frac{[(σ_{2} + σ_{3}) + \sqrt{σ_{2}^{2} - 2 σ_{2} σ_{3} + σ_{3}^{2} + 4 τ_{23}^{2}}]}{2 Y^{t}}$
IFF2(44) $E f f_{4} = \frac{[(b_{⊥}^{τ} - 1) (σ_{2} + σ_{3}) + b_{⊥ | |} \sqrt{σ_{2}^{2} - 2 σ_{2} σ_{3} + σ_{3}^{2} + 4 τ_{23}^{2}}]}{2 Y^{c}}$
IFF3(45) $E f f_{5} = {\frac{[b_{⊥ | |} I_{23 - 5} + \sqrt{b_{⊥ | |} I_{23 - 5}^{2} + 4 S_{12} {(τ_{31}^{2} + τ_{21}^{2})}^{2}}]}{2 S_{12}^{3}}}^{0.5}$

Where, $I_{23 - 5} = 2 σ_{2} τ_{21}^{2} + 2 σ_{3} τ_{31}^{2} + 4 τ_{23} τ_{31} τ_{21}$ .

If the mode stress effort is negative, zero should be used instead. The resultant stress effort

$E f f$ , which is taken as the failure index, is calculated as:(46)

$E f f = {[\sum_{k = 1}^{5} E f f_{k}^{m}]}^{\frac{1}{m}}$

Where, $m$ is the interaction exponent.

On the MATF Bulk Data Entry,

V1: $X^{t}$
V2: $X^{c}$
V3: $Y^{t}$
V4: $Y^{c}$
V5: $Z^{t}$
V6: $Z^{c}$
V7: $S_{12}$
V8: $S_{23}$
V9: $S_{13}$
W1: $b_{⊥ ∥}$ (Default = 0.15)
W2: $b_{⊥}^{τ}$ (Default = 1.0)
W3: $m$ (Default = 2.6)

Interlaminar Shear Failure Index

In continuum shell elements, interlaminar shear failure index can be output. The index is calculated as:(47)

$f = m a x (| τ_{23} |, | τ_{13} |) / τ^{*}$

Where, $τ^{*}$ is user-defined in the SB field on the PCOMPLS card.

The elemental system for PSOLID is calculated based on the centroidal method (see comment 4 on the CHEXA Bulk Data Entry).

The rotation based on THETA/PHI for elements referenced by PSOLID is explained in comment 5 of the CHEXA Bulk Data Entry

For an example CHEXA element, the projection is conducted onto the G1-G2-G3-G4 plane of CHEXA

Example CHEXA element, the thickness direction is always the direction of G1-G2-G3-G4 plane to G5-G6-G7-G8 plane

If X-axis cannot be projected (for instance, if X-axis is perpendicular to G1-G2-G3-G4 plane), then Y-axis is projected and then the X-axis is calculated based on local material Y and Z-axes

The X-axis of the elemental system for material system calculation for elements referencing PCOMPLS is calculated based on the bisection method applied to the G1-G2-G3-G4 plane (the bisection method is explained on comment 3 of the CQUAD4 element)

The X-axis of the Elemental system for the case when THETA/PHI is specified and PCOMPLS is referenced by an element, is the G1-G2 direction of the mid-plane of the element (for example, the mid-plane between G1-G2-G3-G4 and G5-G6-G7-G8 planes of the CHEXA element). This G1-G2 axis on the mid-plane is then rotated based on the THETA/PHI values specified on the CORDM continuation line. The rotation convention for THETA/PHI rotation is the counter-clockwise direction.

Elements

Elastic, Damper, and Mass Elements

Implementation

Zero-dimensional Elements

One-dimensional Elements

Two-dimensional Shell Elements

Three-dimensional Solid Elements

Interface Elements

Offset for One-dimensional and Two-dimensional Elements

Comments

Non-structural Mass

Virtual Fluid Mass

Assumptions

MFLUID Interface

Theory

Arbitrary Beam Section Definition

▸Example: Simple Thin-walled Section Definition Named SQUARE

▸Example: Solid Section Definition Named CUTOUT

Rigid Elements and Multi-Point Constraints

JOINTG (Connectors)

Universal Joint

Revolute Joint

Ball Joint

Axial Joint

Cartesian Joint

Cardan Joint

In-Plane Joint

In-Line Joint

Orient Joint

Hinge Joint

Rigid Pin Joint

Rigid Link Joint

Rigid Beam Joint

Universal Connection with Rigid Pin Joint

Cylindrical Joint

Translator Joint

Combination Joints

Axial and Orient Joint

Inline and Cardan Joint

Rigid Link and Orient Joint

Define Local Coordinate Systems for JOINTG

Interpretation of Joint Characteristics

Joint Loading (LOADJG)

Enforced Joint Motion (MOTNJG)

STOP and LOCK (PJOINTG)

Composite Laminates

Analysis of Composite Shells (PCOMP, PCOMPG, PCOMPP)

Analysis of Continuum Shells (PCOMPLS)

Continuum Shells

Input

Output

Example Using CORDM on PCOMPLS

Interpretation of Results for Composites

Failure Criteria for Composite Laminated Shells

Hill's Theory of Ply Failure

Hoffman's Theory of Ply Failure

Tsai-Wu Theory of Ply Failure

Maximum Strain Theory of Ply Failure

Maximum Stress Theory of Ply Failure

Bonding Material Failure

Hashin Failure Criteria

Puck Failure Criteria

Final Failure Index for Composite Element

Failure Criteria for Composite Anisotropic Solid and Continuum Shell Elements

Hill Criteria

Hoffman Criteria

Tsai-Wu Criteria

Maximum Strain Criteria

Maximum Stress Criteria

Hashin Criteria

Puck Criteria

Cuntze Criteria

Interlaminar Shear Failure Index

Example Using `CORDM` on PCOMPLS