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6.1 INTRODUCTION

FEMAP (Finite Element Modeling And Postprocessing) is an engineering analysis pre- and postprocessor

for the simulation of complex engineering problems using the finite element method. It runs on Microsoft

Windows and provides CAD import, modeling and meshing tools to create a finite element model, as well

as postprocessing functionality that allows structural engineers to interpret analysis results. The finite

element method allows engineers to virtually model components, assemblies, or systems to determine

behavior under a given set of boundaries loads conditions, and is typically used in the design process to

reduce costly prototyping and testing, evaluate differing designs and materials, and for structural

optimization to reduce weight.

Product simulation applications include basic strength analysis, frequency and transient dynamic

simulation, system-level performance evaluation and advanced response, fluid flow and multi-physics

engineering analysis for simulation of functional performance.

Femap is used by engineering organizations and consultants to model complex products, systems and

processes including satellites, aircraft, defense electronics, heavy construction equipment, lift cranes,

marine vessels and process equipment.

Using Femaps digital simulation capabilities we can:

Predict and improve product performance and reliability. Reduce time-consuming and costly physical prototyping and testing. Evaluate different designs and materials. Optimize our design and reduce material usage.

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6.2 Case Studies

6.2.1 Beam Under bending

Consider the circular cantilever beam shown in Figure below. It is fixed at end A and loaded with force Fat the other end:

Where:

F= 100 N

L= 1 m

D= 0.08 m

E=29E6 Pa

= 0.32

6.2.1.1 Finite Element Model

Total number of element 10

Total number of nodes 11Total number of degree of freedom 60

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6.2.1.2 Result

Total displacement (max) = 0.512 m Max comb stress= 1987945 Pa

Buckling factor of = 2.0251

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6.2.2 PLATE UNDER INPLANE LOADING

It is required to perform plane-stress analysis for cantilever rectangular plate under distributed load asshown:

6.2.2.1 Problem Data

property value

Plate thickness 0.01 m

Poisson's ratio 0.32Young's modules of elasticity 29E6 PaDistributed load (in -Y direction) 100 PaThe dimensions 10 x 5 m

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6.2.2.2 Finite Element Model

Total number of elements 100Total number of nodes 66Total number of degrees of freedom 396

6.2.2.3 Results

Von Misses stress with max= 10734.53 Pa Total displacement max = 0.0051 m

Buckling factor of = - 0.0024

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6.2.3 BENDING PLATE0 (SQURE PLATE WITH A HOLE)

It is required to perform the stress and transverse displacement analysis for a square plate with a

circular hole. The plate is rigidly supported (CFCF) and subjected to distributed load in Y-direction as

shown:

6.2.3.1 Problem Data

property value

Plate thickness 0.01 mPoisson's ratio 0.32Young's modules of elasticity 10.3E6 Pa

Distributed load (in - Z-direction) 100 PaThe dimensions 1 x 1 m

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6.2.3.2 Finite Element Model

Total number of elements 168Total number of nodes 108Total number of degrees of freedom 648

6.2.3.3 Results

Von Misses stress with max= 312533.612 Pa Total displacement (max) = 0.2825 m

Buckling factor of = - 84.213

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6.2.4 SHELL STRUCTURE

It is required to perform the stress and transverse displacement analysis for a shell structure used as in

fuselage applications. The barrel is supported on rigid diaphragms, and loaded by uniform pressure.

6.2.4.1 Problem Data

property value

Plate thickness 0.01 mPoisson's ratio 0.32

Young's modules of elasticity 10.7E6 PaDistributed load (in X-direction) 100 Pa

The dimensions 1 x 1 mThe hole radius 0.2 m

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6.2.4.2 Finite Element Model

Total number of elements 261Total number of nodes 161Total number of degrees of freedom 966

6.2.4.3 Results

Von Misses stress with max= 48416 Pa Total displacement (max) = 0.00652 m

Buckling factor of = -1.00965

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