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.

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.

The different material types provided by OptiStruct are: isotropic, orthotropic, and anisotropic materials. The material property definition cards are used to
define the properties for each of the materials used in a structural model.

High Performance Computing leverages computing power, in standalone or cluster form, with highly efficient software,
message passing interfaces, memory handling capabilities to allow solutions to improve scalability and minimize run
times.

Contact is an integral aspect of the analysis and optimization techniques that is utilized to understand, model, predict,
and optimize the behavior of physical structures and processes.

OptiStruct and AcuSolve are fully-integrated to perform a Direct Coupled Fluid-Structure Interaction (DC-FSI) Analysis based on a
partitioned staggered approach.

Aeroelastic analysis is the study of the deflection of flexible aircraft structures under aerodynamic loads, wherein
the deformation of aircraft structures in turn affect the airflow.

OptiStruct provides industry-leading capabilities and solutions for Powertrain applications. This section aims to highlight OptiStruct features for various applications in the Powertrain industry. Each section consists of a short introduction, followed
by the typical Objectives in the field for the corresponding analysis type.

This section provides an overview of the capabilities of OptiStruct for the electronics industry. Example problems pertaining to the electronics industry are covered and common solution
sequences (analysis techniques) are demonstrated.

OptiStruct generates output depending on various default settings and options. Additionally,
the output variables are available in a variety of output
formats, ranging from ASCII (for example, PCH) to binary files (for example,
H3D).

A semi-automated design interpretation software, facilitating the recovery of a modified geometry resulting from a
structural optimization, for further use in the design process and FEA reanalysis.

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.

OptiStruct can be use different solution sequences for
aircraft analysis.

Some of the OptiStruct solution sequences that can be
used are:

Type

Description

STATICS

Linear Static or Nonlinear Static Gap Analysis

MODES

Normal Modes Analysis

BUCK

Linear Buckling Analysis

DFREQ

Direct Frequency Response Analysis

LGDISP

Large Displacement Nonlinear Static Analysis (available as
PARM card entry)

HEAT

Linear Steady-state or Transient Heat Transfer Analysis

FATIGUE

Fatigue Analysis

Static Analysis

OptiStruct can be used to solve time-independent static
analysis. Figure 1 shows a fuselage section with SPC
boundary conditions on the bulkhead and a uniform pressure applied to the skin.

An analysis is termed nonlinear when the relationship between the Force
and Displacement is nonlinear. Most of the structural components in an aircraft
structure are subjected to large deformations, which are best analyzed through
nonlinear analysis. The main reasons for nonlinearity are:

Material nonlinearities

Geometric nonlinearities

Presence of nonlinear forces

Contact nonlinearities

Inertial Relief Analysis

Inertia relief analysis is mostly performed on unsupported structures to determine
the impact loads of structures or to calculate the distribution of forces. OptiStruct has two options for Inertia relief analysis.

PARAM, INREL, -1 is used when certain boundary conditions
are specified.

PARAM, INREL, -2 is used when no boundary conditions are
specified.

Figure 2 shows the results from an Inertia Relief
Analysis performed on a fuselage model.

Normal Modes Analysis

Mode shapes provide the frequencies at which the structure will absorb all the
supplied energy when no load is acting on it. To analyze the displacement of a
structure at these frequencies, you can use Frequency Response Analysis. Normal
Modes Analysis of aircraft structures will help in determining:

Under constrained and loose components

The rotating speed which matches the natural frequencies in case of the
analysis of a blade or a rotor

The areas to be constrained or loaded.

Figure 3 shows the results from the Normal
Modes Analysis for a fuselage and a drone. Both models have free-free boundary
conditions.

Frequency Response Analysis

Each frequency is solved independently and can also solve a several frequencies at a
time. This can be further used to determine the displacement versus frequency plots.
This helps to study the displacements of the structure when subjected to its natural
frequency calculated using Modal Analysis. The frequencies can be specified using
the FREQi card.