STRENGTH OF MATERIALS
TABLE OF CONTENTS
INTRODUCTION
Deflection of beams and cantilevers is an important study for clear understanding of behavioral properties of various structural components in aircrafts and around us. Various aircraft structural components such as wing and fuselage ribs and spars (or longerons) require structural analysis for research and cross-examination.
Our aim is to study the phenomenal deflection changes experienced during beam and cantilever deflection, we will be conducting controlled experiments of various beam materials and sizes and we will also be studying change of properties such as shape deflection and circular bending.
This lab experiment report details our practical and theoretical experimentation with graphical aids and reasoning.
DESCRIPTION OF THE EXPERIMENT
We will set up the required tools and materials to experiment and study the deflection of a cantilever, simply supported beam, shape of a simply supported beam and circular bending in accordance to the instructions in the provided lecturer’s guide.
REQUIRED TOOLS AND MATERIALS
Backboard with a digital dial test indicator (to measure amount of deflection)
Two moveable knife-edge supports (adjustable for experimentation).
Knife-edge load hanger (To hang the masses).
Two clamps (To secure beam).
Five Hanger and masses (For adjustable weight configurations).
Aluminum, steel and brass beams (different material configurations).
Reading scale (For accurate measurement and placement).
EXPERIMENT 1 - DEFLECTION OF A CANTILEVER
VALUES FOR ALUMINUM
Material
Aluminium
E value: 69x109 Nm-2
Width (b): 19 mm
I: 4.275x10-11 m4
Depth (d): 3 mm
Mass (g)
Actual Deflection (mm)
Theoretical Deflection (mm)
0
0
0
100
-1.07
0.89
200
-2.15
1.77
300
-3.03
2.66
400
-4.04
3.54
500
-4.31
4.43
VALUES FOR STEEL
Material
Steel
E value: 207x109 Nm-2
INTRODUCTION
Deflection of beams and cantilevers is an important study for clear understanding of behavioral properties of various structural components in aircrafts and around us. Various aircraft structural components such as wing and fuselage ribs and spars (or longerons) require structural analysis for research and cross-examination.
Our aim is to study the phenomenal deflection changes experienced during beam and cantilever deflection, we will be conducting controlled experiments of various beam materials and sizes and we will also be studying change of properties such as shape deflection and circular bending.
This lab experiment report details our practical and theoretical experimentation with graphical aids and reasoning.
DESCRIPTION OF THE EXPERIMENT
We will set up the required tools and materials to experiment and study the deflection of a cantilever, simply supported beam, shape of a simply supported beam and circular bending in accordance to the instructions in the provided lecturer’s guide.
REQUIRED TOOLS AND MATERIALS
Backboard with a digital dial test indicator (to measure amount of deflection)
Two moveable knife-edge supports (adjustable for experimentation).
Knife-edge load hanger (To hang the masses).
Two clamps (To secure beam).
Five Hanger and masses (For adjustable weight configurations).
Aluminum, steel and brass beams (different material configurations).
Reading scale (For accurate measurement and placement).
EXPERIMENT 1 - DEFLECTION OF A CANTILEVER
VALUES FOR ALUMINUM
Material
Aluminium
E value: 69x109 Nm-2
Width (b): 19 mm
I: 4.275x10-11 m4
Depth (d): 3 mm
Mass (g)
Actual Deflection (mm)
Theoretical Deflection (mm)
0
0
0
100
-1.07
0.89
200
-2.15
1.77
300
-3.03
2.66
400
-4.04
3.54
500
-4.31
4.43
VALUES FOR STEEL
Material
Steel
E value: 207x109 Nm-2