Final Project Ansys

8/12/2019 Final Project Ansys

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Dept of Engineering and Technology

A Project of Aircraft Structure Analysis


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FINAL PROJECT ( ANSYS)

Submitted by : MUHAMMAD HARIS MUNIR (BAT11343)

DANIAL ALI (BAT11362)

Submitted to: Prof.IMTIAZ HUSSAIN

Date :26/12/13
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Acknowledgement ................................................................................. 4

Executive Summary ................................................................................. 5

Ansys Mechanical APDL.............................................................................6

Table of Contents


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This project would not have been possible without the support of our professor. We wish

to express our gratitude to his supervision, Prof. IMTIAZ HUSSAIN who was

abundantly helpful and offered invaluable assistance, support and guidance. The

knowledge about our project is really interesting and technical. During this project we

learnt many new things and different aspects of structure analysis.

ACKNOWLEDGEMENT


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Structural analysis is important because it can evaluate whether a specific structural

design will be able to withstand external and internal stresses and forces expected for

the design.This in turn produces an electronic virtual working model for future design

development.Structural analysis is the determination of the effects of loads on physical

structures and their components. Structures subject to this type of analysis include all

that must withstand loads, such as buildings, bridges, vehicles, machinery, furniture,

attire, soil strata, prostheses and biological tissue. Structural analysis incorporates the

fields of applied mechanics, materials science and applied mathematics to compute a

structure's deformations, internal forces, stresses, support reactions, accelerations, andstability. The results of the analysis are used to verify a structure's fitness for use, often

saving physical tests. Structural analysis is thus a key part of the engineering design of

structures. The structure on which we have to analysis was a double joint composite

material structure. We have used ANSYS software for this job and end up with certain

results.

EXECUTIVE SUMMARY


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DRAWING MODELING

DATA GIVEN

Part A:

Metallic plates

Material = MS

Thickness = 3 mm

Length = 82 mm

Width = 50 mm

Part B:

Composite plates

Thickness = 10 mm

Length = 100 mm

Width = 50 mm

Number of plies = 10

Part C:

Pins

Dia = 4 mm

Maximum two rows

Applied force = 1kN


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Firstly I have divided the basic drawing, after that Iv selected option

PREPROCESSORMODELINGCREATEAREASRECTANGLE-> 2 corner

I made two rectangles which are the skin of aircraft. Then I made two more rectanglesfor patch. Then I extruded the 4 rectangles along normal axis 50 mm lengths. The basic

drawings was ready.

BASIC DRAWING


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Then I made circles on the surface of the joint to make space for rivets. I made circles and

extruded. Then I subtracted that extruded holes from the joint. We subtract the holes so that we

can define rivets in those holes.

SUBTRACTION OF RIVETS


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After subtraction, I made the circle again on the already hollow holes and extruded. These again

made extruded circles represents the rivets.

After filling the holed with rivets, I defined the element type. Here, two types of element are. One

of composite and other rivets and patch plates are of steel. So I selected solid186 for steel and

solid46 for composite material.

After material definition, I defined the real constant for solid46 and I defined the layers of

composite material which are 10 of 1 mm thickness. I also defined the layers orientation which

was 15, 30 and 45. These angles of layers give optimum strength to the composite material inall directions.

RECIRCLE

Element Type

Real Constant


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After real constant, I defined the material properties for composite and steel. For composite Ive

selected the orthotropic in solid46 and for steel, isotropic in solid186. The properties values are

given in the start of this report. I define these values so that software can understand in which

direction and as a whole the strength of material.

After this i selected PREPROCESSORMESHINGMESH TOOL and select the

option volumes and select all, we will get the following drawing as meshing. I do

meshing so that the structure is divided in infinite parts and analysis will be

better. After analysis on each part, the software will differentiate these resultsand give accurate value.

MESHING

Element Properties


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I moved the pin out of the structure so that i can define contact of pin and the holes easily. If the

pins are in the holes then contact pair is difficult to define.

MOVE PINS


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I defined contact pair so that software can understand that these surfaces are in contact, not

fixed.

CONTACT PAIR


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After applying forces we have to done its solution for this purpose we select

SOLUTIONSOLVECURRENT LS

According to the given data and follow all steps correctly the message must be

shown on screen SOLUTION IS DONE

The solution status is given in the table in picture.

SOLUTION IS DONE


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This graph tells that as the cumulative irritation number increases, the absolute convergence

norm decreases. The cumulative irritation numbers is the term which tells that on a specific part,

for how many times the analysis is applied. The absolute convergence norm tells that it is a non

standard forces analysis. Non standard mean the forces are not in their standard units.

GRAPH OBTAINED


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GENERAL POSTPROCESSINGPLOT RESULTSDEFORMED SHAPE

DEFORMED+UNDEFORMED

This shape tells us that after deformation, how our structure will look like. How much our

structure will bend.

DEFORMED/UNDEFORMED SHAPE


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Von Mises stress is widely used by designers, to check whether their design will withstand given

load condition. Von mises stress is considered to be a safe haven for design engineers .Using

this information an engineer can say his design will fail, if maximum value of Von Mises stress

induced in the material is more than strength of the material. It works well for most of the cases,

especially when material is ductile in nature.

VON MISES STRESS

EXAMPLE FOR UNDERSTANDING


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GENERAL POSTPROCESSINGPLOT RESULTSCONTOR PLOTELEMENT

SOLUTIONSTRESSVONMISSES

This analysis tells that on a particular area, how much force is present. The forces range is

given in different colors. If at any particular area is red, this tells that at that area maximum force

is present. If the whole structure is red then this cannot be manufactured as It will damage

earlier.

VON MISES STRESS


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MAXIMUM STRESS


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LOG FILE UNDERSTANDING


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(1)http://www.ansys.com/Products/Simulation+Technology/Structural+Analysis

REFERENCES
http://www.ansys.com/Products/Simulation+Technology/Structural+Analysishttp://www.ansys.com/Products/Simulation+Technology/Structural+Analysishttp://www.ansys.com/Products/Simulation+Technology/Structural+Analysishttp://www.ansys.com/Products/Simulation+Technology/Structural+Analysis

Final Project Ansys

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