OptiStruct is a proven, modern structural solver with comprehensive, accurate and scalable solutions for linear and nonlinear
analyses across statics and dynamics, vibrations, acoustics, fatigue, heat transfer, and multiphysics disciplines.
The OptiStruct Example Guide is a collection of solved examples for various solution sequences and optimization types and provides
you with examples of the real-world applications and capabilities of OptiStruct.
A uniform, homogeneous plate which is symmetric about horizontal axes in both geometry and loading, to find the maximum
axial stress in the plate with a hole.
Snap-fit is a combination of two components namely mating and base part which form a mechanical attachment between them
by means of locators, locks and enhancements. Nonlinear Static Analysis with large displacement theory is used to solve
this example.
Contact smoothing is useful to increase accuracy of the contact solution. An enforced displacement to push two concentric
rings toward each other to engage the contact is used. The usage of NLOUT entry allows you to study the progression of SPC force over successive increments.
Demonstrate a revolute joint using JOINTG and MOTNJG. The JOINTG entry can be used for defining a variety of joints, including revolute, ball, universal, cardan, and so on. Motion on
these joints can be applied using the MOTNJG entry.
The PCOMPLS entry can be used to define continuum shell composites using solid elements. Currently first order CHEXA and CPENTA solid elements are supported.
Demonstrates self-contact which is used in this nonlinear large displacement implicit analysis involving hyperelastic
material and contacts using OptiStruct.
This section presents optimized topology examples generated using OptiStruct. Each example uses a problem description, execution procedures, and results to demonstrate how OptiStruct is used as a design concept tool.
This section presents size (parameter) optimization examples solved using OptiStruct. Each example uses a problem description, execution procedures, and results to demonstrate how OptiStruct is used in size optimization.
This section presents shape optimization example problems, solved using OptiStruct. Each example uses a problem description, execution procedures and results to demonstrate how OptiStruct is used in shape optimization.
The examples in this section demonstrate how topography optimization generates both bead reinforcements in stamped
plate structures and rib reinforcements for solid structures.
The examples in this section demonstrate how the Equivalent Static Load Method (ESLM) can be used for the optimization
of flexible bodies in multibody systems.
The OptiStruct Example Guide is a collection of solved examples for various solution sequences and optimization types and provides
you with examples of the real-world applications and capabilities of OptiStruct.
The PCOMPLS entry can be used to define continuum shell composites using solid elements. Currently first order CHEXA and CPENTA solid elements are supported.
OS-E: 0175 Continuum Shell Composites Using PCOMPLS
The PCOMPLS entry can be used to define continuum shell composites
using solid elements. Currently first order CHEXA and
CPENTA solid elements are supported.
Model Description
Conduct a continuum shell composite analysis of a bracket using PCOMPLS
entry. A force is applied on the RBE2 element and the other end of the
bracket is fixed at all degrees of freedom (Figure 1).
In addition to shell-based composites (via PCOMP,
PCOMPP, or PCOMPG), solid elements using
CHEXA and CPENTA elements can now be used to define
composite elements using the PCOMPLS entry. Multiple plies can be defined
on the PCOMPLS entry referencing corresponding materials, thicknesses,
and ply orientations. The current model under consideration consists of 7 plies with
different thicknesses and orientations. All plies reference the MAT9OR
material entry for orthotropic material entries.
FE Model
Elements Types
CHEXA
CPENTA
The linear material properties are:
MAT9OR
Young’s Modulus
E1=1.0E5
E2=5.0E3
E3=5.0E3
Poisson's Ratio
NU1=0.4
NU2=0.3
NU3=0.015
Results
The displacements and composite stresses can be seen in Figure 2.