design and fabrication of unmanned aerial vehicle pieas university islamabad pakistan (part-2)

PIEAS University Islamabad, Pakistan

Group Members:Mazhar IqbalUmar HayatShahid Waqas Khan

Design and Fabrication of UAVSupervisor:

Engr. M. Abdul basitCo-supervisor:

Dr. Kamran Rasheed Qureshi

2 PIEAS University Islamabad, Pakistan

Presentation Outline●Our Objective●Brief Introduction to Remote Control(R/C) Plane●Overview of Design●Modifications●Fabrication of Fuselage●Fabrication of Wing●Fabrication of Empennage●Covering●Testing●Achievements●Future Recommendations

Our Objective●Project

●Design and Fabrication of Electric Driven Unmanned Aerial Vehicle(UAV)

●Previous Semester●Design

● Conceptual● Preliminary● Detailed

●This Semester●Modifications●Fabrication●Testing

Brief Introduction

Brief Introduction (Continued)

●The Forces on an R/C Plane

Design Overview

Wing DimensionsAirfoil NACA 4412Span 60 inChord 11 inAR 5.45Area 660 in2

Dihedral Angle 30

Angle of Attack 80

Material Styrofoam + Balsa Wood

Design Overview (Continued)

Fuselage DimensionsHeight 6.42 inLength from Leading edge to nose

10.5 in

Length for airfoil 11 inLength from trailing edge of wing to tail

21.5 in

Total Length 42.91 inWidth at nose 3.5 in

Design Overview (Continued)

TailHorizontal tailHorizontal tail area 115 in2

Horizontal tail AR 4Horizontal Tail Span 21 inTaper Ratio 0.60 inVertical TailArea 55 in2

Chord 4.64 inTaper Ratio 0.40

Design Overview (Continued)

Control SurfacesAilerons  

Area 40.5 in2

Chord 1.5 inSpan 27 inElevator  Area 42 in2

Span 21 inChord 2 inRudderArea 40.5 in2

Root Height 9.2 inTip height 7.8 in

Complete Airplane Model

Modifications●Rudders

●Included rudders for yaw-control●Nose Gear Controllable

●For efficient handling on runway●Dihedral Angle

●For stability ●Wing Material

●To reduce weight (Styro-foam & balsa)

Dihedral Angle● Angle of an aircraft's wing, from the wing root

to the wing tip.

●Positive(Dihedral)

●Negative(Anhedral)

Dihedral Angle (Continued)

●Effect of zero dihedral angle●Each wing has the same constant angle of

attack●No difference in the lift generated by each

wing●No restoring moment

Dihedral Angle (Continued)

●Effect of Dihedral Angle●Difference in the angle of attack of each

wing,●The lift they create, is responsible for the

dihedral effect

Modifications in Wing

16

●Before ●Modified

PIEAS University Islamabad, Pakistan

Modification in Wing (Continued)

●Fabrication●Weight●Increased Strength

Fabrication of Fuselage

Fabrication of Fuselage

●Drawing●Cutting of Plywood sheet●Marking & cutting of Fuselage sides●Cutting of formers●Joining the parts

Fabrication of Fuselage(Continued)

●Side view of fuselage

Fabrication of Fuselage (Continued)

●Cutting of Ply Wood

Fabrication of Fuselage (Continued)

●Marking and Cutting of sides of the Fuselage

Fabrication of Fuselage (Continued)

●Marking and Cutting of Base and Top Structure of Fuselage

Fabrication of Fuselage (Continued)

●Cutting of Formers

Fabrication of Fuselage (Continued)

●Joining the parts

Fabrication of Fuselage (Continued)

●Joining the parts…

Fabrication of Fuselage (Continued)

●Joining the parts…

Fabrication of Fuselage (Continued)

●Filing

Fabrication of Fuselage (Continued)

●Final Shape of the Fuselage

Fabrication of Wing

Steps for Fabrication of Wing1. Cutting the pieces of thermo-col sheet2. Cutting two aero-foils 3. Cutting wing shape 4. Strengthening by Balsa5. Reducing the wing weight6. Rounding the Nose7. Joining the wing parts8. Fabrication of aileron

Drawing of the Wing

Wing Cutting (Basic Theory )● 

Cutting of Thermo-col Sheet●The part where heat is supplied the

thermo-col sheet will burn leaving the required part.

Cutting of Aero-foils●Cut two aero-foils to cut

the shape of wing

Cutting Wing Shape●Support the thermo-col sheet for indication

of final wing cut●The heating wire will make apart the wing

shape illustrated in the coming video

Cutting Wing Shape (Continued)

Final Wing Shape●The wing shape is final but thermo-col sheet

has not strength to bear bending moments produced due to weight and lift forces

●We need to strengthen the wing

38 PIEAS University Islamabad, Pakistan

Strengthening by Balsa Wood●Preparation of sheets of Balsa wood●Most important thing in making the sheets is

that fibers of the wood should be in the direction of wing span

Strengthening by Balsa Wood (Continued)

●Gluing balsa onto the wing

Strengthening by Balsa Wood (Continued)

Reducing the Wing Weight

●Wing’s own weight should be minimum

●Make the wing hollow but strength should not decrease

●Make the wing hollow aft the center of pressure

Reducing the Wing Weight (Continued)

●Drawing a sketch on the wing according to the dimensions mentioned in the design process

43 PIEAS University Islamabad, Pakistan

Reducing the Wing Weight (Continued)

●Removing balsa wood

44 PIEAS University Islamabad, Pakistan

Reducing the Wing Weight (Continued)

●Removing thermo-col

Rounding the Nose●Nose has to face stress produced due to air

coming from front side●So high strength is required in nose of wing●To strengthen nose, we made nose of balsa

wood separately and glued to the wing●Nose radius is 1.58% of chord●Nose radius is 0.1738 in= 4.4 mm●Made the nose round as explained in next

slide

Rounding the Nose (Continued)

47 PIEAS University Islamabad, Pakistan

Joining the Wing Parts●Two parts of the wing were made●Now glue them to make complete span

Fabrication of Aileron

Fabrication of Aileron (Continued)

Fabrication of Empennage

Horizontal Tail

Horizontal Tail (Continued)

Horizontal Tail (Continued)

Horizontal Tail (Continued)

Other Parts of Empennage●Other parts of empennage

●Vertical tail●Elevator●Rudder

●They are simple to fabricate, as illustrated in horizontal tail fabrication

Final Shape of Empennage

Covering

Covering● Color of covering sheet is very important● It should be visible to pilot at high altitudes in the

flight● Therefore we chose purple color● White color at wing nose● Blue color at wing trailing edge and horizontal tail● These different colors indicates direction of the

plane when plane is not completely visible

Covering (Continued)

●To cut the covering sheet, make sketch of each part on the sheet

●Cut the covering sheet from the sketch

61

Covering (Continued)

PIEAS University Islamabad, Pakistan

Covering (Continued)

●Covering each part using iron

Final Plane

Final Plane

Components of Electric circuit are:●Battery●ESC●Motor●Receiver●Servos●Connector

Electric Circuit

Following table shows plane Structural performance:

Quantity ValueMax. CL 1.2

Max. L/D 12

Wing Loading [lb/ft2] 1.26

Weight without components [lbs.]

2.64

Weight with components [lbs.]

5.88

Performance

Following table show plane mission performance: Quantity Value

Max. L/D speed [ft/s] 64

Cruise speed [ft/s] 45

Stall speed [ft/s] 39

Take-off distance [feet] 100

Number of Laps 04

Average time per Lap [min.] 01

Landing distance [feet] 60

Performance (Continued)

Testing

Following tests were performed:

●Tensile testing of Balsa & Ply wood●3-Point bending test (Wing)●Landing Gear Test●Flight Test

Tensile Test Balsa and Plywood testing was done to check Strength

Wing Test●Testing of wing by applying maximum take-

off weight

Landing Gear Test●Vertical Drop test was performed for

landing gear●Result

●Landing gear capable of bearing shock●No permanent deformation in landing gear

Stability Test

Flight TestTest Flight was done to:●Verify calculated performance of plane●Check stability of plane●Check structural conformity of plane●Check battery timing●Check Take-off and landing distances

Competition●Participation in DBFC-10●Organized by GIKI in coordination with

●PIEAS●STEM Careers●HEC●AIAA(GIKI Chapter)

Rules for solar category were:●Battery pack max. weight limit was 1.75 lb.●Max. 4 flight attempts were allowed.●Solar energy to be used for propulsion.●Max. take-off distance was 150 feet.●Safe Landing to get score.●Max. current was limited to 20 Ampere.

Competition (Continued)

AchievementsFollowing are the achievements of our team:●Performance in viva and Quiz●Light weight plane (5.88 pounds)●Current of our plane was 17.5 Amperes●Successful flight in first attempt●Stable flight

First Position in Solar Category

Future RecommendationsFollowing improvements can be made:

●Plane can be used for surveillance

●Plane can be controlled using Autopilot

●Inverter can be used to harness solar energy

during Flight

●Projectile mechanism can be used in plane

Flight Video

https://www.youtube.com/watch?v=ZPjru23VhvU

Or write :

“DBFC10 Flight video PIEAS University Islamabad Solar Aircraft(Winner Team at GIKI)” on youtube.

References1. D. W. A. a. S. Eberhardt, Understanding Flight, Second

Edition, McGraw-Hill Professional, September 2, 2009 2. A. Lennon, R/C Model Aircraft Design, East Ridge USA: Air Age

Media Inc., 2002;20053. D. Raymer, Aircraft Design: A Conceptual Approach, Fourth

Edition, AIAA Education4. Alex Wiess, R/C Sports Aircraft from Scratch, 1998 5. Naresh K. ,Design, Development and Demonstration of RC

Airplanes6. White, F. M. (4th Edition). Fluid Mechanics. McGraw-Hill7. Regis B. Miller, The Encyclopedia of Wood, U.S Dept. of

Agriculture,19998. TRANSPORTATION, U. D. (2003). PILOT’S HANDBOOK Of

Aeronautical Knowledge