SHELL281 Element Description

SHELL281 is suitable for analyzing thin to moderately-thick shell structures. The element has eight nodes with six degrees of freedom at each node: translations in the x, y, and z axes, and rotations about the x, y, and z-axes. (When using the membrane option, the element has translational degrees of freedom only.)

SHELL281 is well-suited for linear, large rotation, and/or large strain nonlinear applications. Change in shell thickness is accounted for in nonlinear analyses. The element accounts for follower (load stiffness) effects of distributed pressures.

SHELL281 may be used for layered applications for modeling composite shells or sandwich construction. The accuracy in modeling composite shells is governed by the first-order shear-deformation theory (usually referred to as Mindlin-Reissner shell theory).

The element formulation is based on logarithmic strain and true stress measures. The element kinematics allow for finite membrane strains (stretching). However, the curvature changes within a time increment are assumed to be small.

See SHELL281 for more details about this element.

SHELL281 Input Data

The following figure shows the geometry, node locations, normal direction, and multilayer construction for this element. The element is defined by shell section information and by eight nodes (I, J, K, L, M, N, O and P).

Midside nodes may not be removed from this element. See Quadratic Elements (Midside Nodes) in the Modeling and Meshing Guide for more information about the use of midside nodes.

A triangular-shaped element may be formed by defining the same node number for nodes K, L and O.

Figure 281.1: SHELL281 Geometry

Single-Layer Definition

To define the thickness (and other information), use section definition, as follows:

A single-layer shell section definition provides flexible options. For example, you can specify the number of integration points used and the material orientation.

Multilayer Definition

The shell section commands allow for layered shell definition. Options are available for specifying the thickness, material, orientation, and number of integration points through the thickness of the layers.

You can designate the number of integration points (1, 3, 5, 7, or 9) located through the thickness of each layer when using section input. When only one, the point is always located midway between the top and bottom surfaces. If three or more points, two points are located on the top and bottom surfaces respectively and the remaining points are distributed at equal distances between the two points. The default number of integration points for each layer is three; however, when a single layer is defined and plasticity is present, the number of integration points is changed to a minimum of five during solution.

The following additional capabilities are available when defining shell layers:

The layers are stacked from the shell bottom surface in the direction of shell normal N, which is aligned with the third element coordinate axis e3. The definition of e3 is described below.

Element and Layer Coordinate Systems

SHELL281 has element coordinate systems (e1-e2-e3) established at four in-plane integration points:

Figure 281.2: SHELL281 Default Element Coordinate Systems

When KEYOPT(11) = 0, the default first element coordinate axis e1 is aligned with the first parametric direction S1 of the element at the in-plane integration points. S1 and the second parametric direction S2 can be defined respectively as:

where the geometry is given as:

where:

= two isoparametric element coordinates

= shape functions associated with eight element nodes

= global nodal coordinates of the eight element nodes

With KEYOPT(11) = 1, the default first element coordinate axis e1 is directed from node I to node J.

The default third element coordinate axis e3 is normal to the element surface, and the default second element coordinate axis e2 is perpendicular to the e1 and e3 axes. Coordinate axes e3 and e2 are obtained respectively as follows:

As shown in the following figure, you can also define element orientation via ESYS. The user-defined element coordinate system (e1-e2-e3) is obtained by projecting a local coordinate system (x-y-z) to the shell surface. When KEYOPT(4) = 0, the user-defined third element coordinate axis e3 is always aligned with the default e3. When KEYOPT(4) = 1, the user-defined e3 is set to the opposite of default e3 if local coordinate axis z and default e3 are in the opposite directions.

Figure 281.3: SHELL281 User-Defined Element Coordinate Systems

The layer coordinate systems (L1-L2-L3) as shown in the following figure are identical to the element coordinate system if no layer orientation angles are specified; otherwise, the layer coordinate system can be generated by rotating the element coordinate system about e3. (For the definition of layer orientation angles θ, see SECDATA.) Material properties are defined in the layer systems; therefore, the layer system is also called the material coordinate system.

Figure 281.4: SHELL281 Layer Coordinate Systems

Other Input

The element supports degeneration into a triangular form. For better accuracy, however, Ansys, Inc. recommends quadrilateral shaped elements. The triangle form is generally more robust when using the membrane option with large deflections.

To evaluate stresses and strains on exterior surfaces, set KEYOPT(1) = 2. When used as overlaid elements on the faces of 3D elements, this option is similar to the surface stress option, but is more general and applicable to nonlinear analysis. The element used with this option provides no stiffness, mass, or load contributions. Use this option in single-layer shells only. Irrespective of other settings, SHELL281 provides stress and strain output at the four in-plane integration points of the layer.

SHELL281 uses a penalty method to relate the independent rotational degrees of freedom about the normal (to the shell surface) with the in-plane components of displacements. The program determines an appropriate penalty stiffness by default. A drill-stiffness factor can be specified via SECCONTROL. Default drill stiffness is calculated from linear section stiffness (integrated linear elastic material stiffness through the thickness). The default drill stiffness remains constant even when materials become nonlinear. For elements with softening materials, a smaller drill-stiffness scaling factor should be specified via SECCONTROL.

Element loads are described in Element Loading. Pressures may be input as surface loads on the element faces as shown by the circled numbers in Figure 281.1: SHELL281 Geometry. Positive pressures act into the element. Because shell edge pressures are input on a per-unit-length basis, per-unit-area quantities must be multiplied by the shell thickness.

Temperatures may be input as element body loads at the corners of the outside faces of the element and at the corners of the interfaces between layers. The first corner temperature T1 defaults to TUNIF. If all other temperatures are unspecified, they default to T1. If KEYOPT(1) = 0 and if exactly NL+1 temperatures are input, one temperature is used for the four bottom corners of each layer, and the last temperature is used for the four top corner temperatures of the top layer. If KEYOPT(1) = 1 and if exactly NL temperatures are input, one temperature is used for the four corners of each layer. That is, T1 is used for T1, T2, T3, and T4; T2 (as input) is used for T5, T6, T7, and T8, etc. For any other input pattern, unspecified temperatures default to TUNIF.

SHELL281 includes the effects of transverse shear deformation. The transverse shear stiffness of the element is a 2x2 matrix as shown below:

To define transverse shear stiffness values, issue the SECCONTROL command.

Transverse shear-correction factors k are calculated once at the start of the analysis for each section. The material properties used to evaluate the transverse shear correction factors are at the current reference temperature during solution. User-field variables and frequency are all set to zero when evaluating the material properties used to calculate the transverse shear correction factors.

where shear-correction factor k = 5/6, G = shear modulus, and h = thickness of the shell.

The bending stiffness is defined by either a standard or preintegrated shell section (SECTYPE,,SHELL or GENS, respectively). Further bending-stiffness scaling is available via a user-specified factor (BENSTIF on the SECCONTROL command). For a standard shell section, Mechanical APDL rebalances the element stresses to reflect the change in bending stiffness.

SHELL281 can be associated with linear elastic, elastoplastic, creep, or hyperelastic material properties. Only isotropic, anisotropic, and orthotropic linear elastic properties can be input for elasticity. The von Mises isotropic hardening plasticity models can be invoked with BISO (bilinear isotropic hardening) and NLISO (nonlinear isotropic hardening) options. The kinematic hardening plasticity models can be invoked with BKIN (bilinear kinematic hardening) and CHABOCHE (nonlinear kinematic hardening). Invoking plasticity assumes that the elastic properties are isotropic (that is, if orthotropic elasticity is used with plasticity, the program assumes the isotropic elastic modulus = EX and Poisson's ratio = NUXY).

Hyperelastic material properties (2, 3, 5, or 9 parameter Mooney-Rivlin material model, Neo-Hookean model, polynomial form model, Arruda-Boyce model, and user-defined model) can be used with this element. Poisson's ratio is used to specify the compressibility of the material. If less than 0, Poisson's ratio is set to 0; if greater than or equal to 0.5, Poisson's ratio is set to 0.5 (fully incompressible).

Both isotropic and orthotropic thermal expansion coefficients can be input using MP,ALPX. When used with hyperelasticity, isotropic expansion is assumed.

Use the TREF command to specify the global value of reference temperature. If MP,REFT is defined for the material number of the element, it is used for the element instead of the value from the TREF command. But if MP,REFT is defined for the material number of the layer, it is used instead of either the global or element value.

When KEYOPT(5) = 0, SHELL281 uses an advanced shell formulation that accurately incorporates initial curvature effects. The calculation for effective shell-curvature change accounts for both shell-membrane and thickness strains. The new formulation generally offers improved accuracy in curved-shell structure simulations, especially when thickness strain is significant or the material anisotropy in the thickness direction cannot be ignored, or in thick shell structures with unbalanced laminate construction or shell offsets..

When KEYOPT(5) = 1, a simplified curved-shell formulation is adopted. Unlike the advanced curved-shell formulation (KEYOPT(5) = 0), the curvature effects in the shell-offset handling are ignored. The simplified formulation generally leads to more robust nonlinear convergence.

The curved-shell formulation is automatically disabled for excessively thick and curved structures with an r / t ratio below 5 / 6, where r is the radius of curvature measured at shell mid-plane and t is the total shell thickness.

KEYOPT(8) = 2 stores midsurface results in the results file for single or multi-layer shell elements. If you use SHELL,MID, you will see these calculated values, rather than the average of the TOP and BOTTOM results. Use this option to access these correct midsurface results (membrane results) for those analyses where averaging TOP and BOTTOM results is inappropriate; examples include midsurface stresses and strains with nonlinear material behavior, and midsurface results after mode combinations that involve squaring operations such as in spectrum analyses.

KEYOPT(9) = 1 reads initial thickness data from a user subroutine.

KEYOPT(10) = 1 outputs normal stress component Sz, where z is shell normal direction. The element uses a plane-stress formulation that always leads to zero thickness normal stress. With KEYOPT(10) = 1, Sz is independently recovered during the element solution output from the applied pressure load. The pressure must be applied directly to the shell, and not via surface elements (SURFnnn).

The effects of pressure load stiffness are automatically included for this element. If an unsymmetric matrix is needed for pressure load stiffness effects, use NROPT,UNSYM.

The element supports both consistent and lumped mass matrices. Use LUMPM,ON to activate a lumped mass matrix. A consistent mass matrix is used by default.

A summary of the element input is given in "SHELL281 Input Summary". A general description of element input is given in Element Input.

SHELL281 Output Data

The solution output associated with the element is in two forms:

Several items are illustrated in Figure 281.5:  SHELL281 Stress Output.

KEYOPT(8) controls the amount of data output to the results file for processing with the LAYER command. Interlaminar shear stress is available as SYZ and SXZ evaluated at the layer interfaces. KEYOPT(8) must be set to either 1 or 2 to output these stresses in the POST1 postprocessor. A general description of solution output is given in Solution Output. See the Basic Analysis Guide for ways to review results.

The element stress resultants (N11, M11, Q13, etc.) are parallel to the element coordinate system, as are the membrane strains and curvatures of the element. Such generalized strains are available through the SMISC option at the element centroid only. The transverse shear forces Q13, Q23 are available only in resultant form: that is, use SMISC,7 (or 8). Likewise, the transverse shear strains, γ₁₃ and γ₂₃, are constant through the thickness and are only available as SMISC items (SMISC,15 and SMISC,16, respectively).

The program calculates moments (M11, M22, M12) with respect to the shell reference plane. By default, the program adopts the shell midplane as the reference plane. To offset the reference plane to any other specified location, issue the SECOFFSET command. When there is a nonzero offset (L) from the reference plane to the midplane, moments with respect to the midplane () can be recovered from stress resultants with respect to the reference plane as follows:

SHELL281 does not support extensive basic element printout. POST1 provides more comprehensive output processing tools; therefore, it is good practice to issue the OUTRES command to ensure that the required results are stored in the database.

SHELL281 allows for transformation of stresses and strains to other coordinate systems in postprocessing (RSYS). By default, the element stresses and strains are displayed or listed in the global Cartesian coordinate system.

Figure 281.5: SHELL281 Stress Output

x0 = Element x axis if element orientation (ESYS) is not specified. (See KEYOPT(11).)

x = Element x axis if element orientation is specified.

The Element Output Definitions table uses the following notation:

A colon (:) in the Name column indicates that the item can be accessed by the Component Name method (ETABLE, ESOL). The O column indicates the availability of the items in the file jobname.out. The R column indicates the availability of the items in the results file.

In either the O or R columns, “Y” indicates that the item is always available, a letter or number refers to a table footnote that describes when the item is conditionally available, and “-” indicates that the item is not available.

Table 281.2: SHELL281 Item and Sequence Numbers lists output available through ETABLE using the Sequence Number method. See Creating an Element Table and The Item and Sequence Number Table for more information. The following notation is used in Table 281.2: SHELL281 Item and Sequence Numbers:

SHELL281 Assumptions and Restrictions

SHELL281 Product Restrictions

When used in the product(s) listed below, the stated product-specific restrictions apply to this element in addition to the general assumptions and restrictions given in the previous section.

Ansys Mechanical Pro  —