Project Specifications and Scope
Presentation Outline
 Team Introduction
 Project Overview
 Competition Specifications
 Mission Profile
 Score Analysis
 Subsystem Breakdown
 Project Timeline
 Summary
UAV Team
 Matthew Martin – Project Manager, ME
 Josiah Shearon – Mechanical Technical Lead, ME
 TJ Worden – Design Req. Specialist, ME
 David Neira – Treasurer, ME
 Josh Mellen – Electrical Technical Lead, ECE
 Ona Okonkwo – Secretary, ECE
Overview
 Develop a UAV which will satisfy the AIAA
Design/Build/Fly Competition mission profile
 Competition Details
Sponsors:
Cessna, Raytheon
Location:
Tucson, AZ
Design Report Submission Date:
Competition Date:
March 1, 2011
April 15-17, 2011
Aircraft Design Requirements
System
Constraint
Aircraft
• Must weigh less than 55 lbs.
• Cannot be rotary wing or lighter-than-air
• Hand-launched
• 5-minute assembly
• Payload contained within UAV
Wings
• Fixed-wing
• Must support 2.5 gram load at wing tip
Propulsion
• Propeller driven
• Commercially available propeller
• Electric motor
Battery
• ¾ lbs. maximum weight
• NiCad or NiMH
• 20 Amp max draw
• Fully insulated
• Commercially available cells
UAV Container
 UAV must be contained within
this carry on bag
 No single dimension can be
more than 22 inches
 Entire disassembled aircraft
and tools must fit in suitcase
(no transmitter)
Flight Course
Governing Equations
Mission One
Dash to critical target
 Mission description
 4 minute time limit
 Goal
 Achieve maximum number of laps in specified time
 Time starts during first hand launch attempt
M1: Path to Goal
 Aerodynamic Body
 Low Drag
 Lightweight
 High Thrust
 Battery Longevity
 High Maneuverability
Mission Two
Ammo Re-Supply
 Mission description
 Payload flight

Team selected/supplied steel bar(s)
 Goal
 Complete 3 laps
 Maximize payload-to-weight ratio
M2: Path to Goal
 High Lift Airfoil Design
 Adequate Structural Integrity
 Lightweight Aircraft
 Good Flight Stability Under Heavy Load
Mission Three
Medical Supply Mission
 Mission description
 Payload flight

Team selected quantity of golf balls
 Goal
 Complete 3 laps
 Transport maximum number of golf balls
M3: Path to Goal
 Maximize Cargo Bay Volume
 High Payload Capacity
 Lightweight Payload Stabilizer
Overall Flight Score Analysis
Projected Maximum Score
Mission 1 = 1
Mission 2 = 1.5
Mission 3 = 2
Mission Priority
1. Mission 3
2. Mission 2
3. Mission 1
UAV Team Specializations
 Matthew Martin – Overall Aircraft Layout
 Josiah Shearon – Materials Selection & Fabrication
 TJ Worden – Wing Design
 David Neira – Power & Propulsion
 Josh Mellen – Electronics & Control (Hardware)
 Ona Okonkwo – Electronics & Control (Software)
Electronics & Controls Design
Desired Characteristics
 Battery
 High Energy Density
 Greater Longevity
 Less Volatile
 Low Recharge Time
 Transmitter
 Long Distance
 No Signal Interference
 FCC Requirement
 72.01-72.99MHz
 Control Board
 Lightweight/Efficient
 Minimum One DC Motor
(Propeller), Two Servos
(Rudder/Elevator)
 Gyroscopic Feature
 Radio Fail-Safe Maneuver

Kill Throttle, Roll Right, Yaw
Right, Nose Up
Electronics & Controls Design
Options/Selection
 Battery Selection
 NiMH
 Long Lasting
 Chemically Stable
 Quick Charge
 Transmitter Selection
 Spektrum DX6i
 No Signal Interference
 Meets all FCC
Requirements
Power & Propulsion Systems
Desired Characteristics
 Motor
 Propulsion
 Efficient
 Optimal RPM/Torque
 Optimal Power Generation
 High Thrust
 Light Weight
 Light Weight
 Low Current Draw
 Low Drag
Power & Propulsion Systems
Options/Selection
 Motor
 Brushless



Low Weight
High Efficiency
Ideal RPM/Torque
 Gear/Belt Reduction


Increases Output RPM
Maintains High Torque
 Propulsion
 Ducted Fan


High Thrust, Low Drag
Heavy Weight
 Propeller


Light Weight
Drag Due To Vortex Generation
Wing Design
Desired Characteristics
 High Aerodynamic Efficiency (L/D)
 Moderate Wing Loading
 High Lift At Low Speeds
 Low Stall Speed
 Hand Launched
 Stable Flight
 Moderate Maneuverability
Wing Design
Options/Selection
 Wing Parameters
 Wing Span
 Planform Area
 Aspect Ratio
 CL/CD
 Wing Section
 Control Surfaces
 Wing Layout
 Sweep
 Diahedral
 Wing Configuration
 Twist
 Taper
 Wingtip Design
Materials Selection & Fabrication
Desired Characteristics
 Light Weight
 Ideal Yield Strength
 Stiff in Bending
 Simple To Manufacture
Materials Selection & Fabrication
Chosen Materials:
1. CFRP
• Loading
• Tension
2. Wood
• Loading
• Longitudinal
Materials Selection & Fabrication
Options/Selection
 Hybrid Structures
 Sandwich
 Light Weight
 Resistant to Bending
 Resistant to Buckling
 Shape Factors
 I-Beam
 Rectangle
 Hollow Shape
Overall Layout
Desired Characteristics
 High Storage Volume Capacity
 Low Drag
 Optimal Center of Gravity
 Adequate Maneuverability
 Fulfillment of Design Requirements
 Safety and Size
 Ease of Assembly
Overall Layout
Options/Selection
 Fuselage
 Lowest Drag Coefficient
 Body Lines
 Smooth/Sharp
 Landing Gear

Retractable/Fixed
 Weight Distribution
 Compact/Dispersed
 Subsystem Integration
 Propulsion Configuration


Single/Multiple Motors
Front/Back Driven
 Wing Configuration
 Main/Tail Spacing
 Wing Location
Summary
 Develop aircraft with the following features:
 High Storage Capacity
 Lightweight
 Heavy Payload Capacity
 Adequate Speed/Maneuverability
 February 20, 2011
 Finish Fabrication of UAV
 Submit Design Report
 Competition: April 15-17, 2011
Questions?