10/14: Conceptual Design Review
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Transcript 10/14: Conceptual Design Review
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?