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Team 6: “Soldier Portable UAV”• David Neira• TJ Worden• Matthew Martin• Joshua Mellen• Ona Okonkwo• Josiah Shearon
AIR HERCULES
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Develop a UAV to compete in the 2011 AIAA Design/Build/Fly Competition◦ Location: Tucson, AZ◦ Date: April 15-17, 2011
Primary requirements:◦ Assembly◦ Hand launched◦ Design Limitations
Power/Electronics Sizing Configuration
Project Overview
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Mission Profile
Mission 1: Dash to Critical Target• Maximum laps in 4 minutes
Mission 2: Ammo Re-supply• 3 laps with steel bar payload
Mission 3: Medical supply Mission• 3 laps with golf ball payload
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Overall Scoring Equation
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RAC
MMMeReportScorTotalScore 321
Project ManagementFaculty AdvisorsDr. Chiang Shih
Dr. Joe Yeol
Project LeadMatthew Martin (ME)
Materials/FabricationJosiah Shearon (ME)
Electronics/ControlJoshua Mellen (EE)
Onachukwu Okonkwo (EE)
PropulsionDavid Neira (ME)
AerodynamicsTJ Worden (ME)
Materials/FabricationRyan Jantzen
Electronics/ControlRicardo Ascencio
PropulsionMyles BeanJohn Edgar
AerodynamicsEric Sloan
Walker Carr
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Project Schedule
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Conceptual Design Phase
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Specification Value
Empty Weight < 1.6 lbs
Payload to Weight Ratio > 1.5
Propulsion Battery Weight < 0.75 lbs
Maximum Current Draw 20 amps
Maximum Linear Dimension 22 in
Assembly Time < 5 min
• Design Process• Scoring Analysis• Product Specifications• Aircraft Configuration
Propulsion / Control Systems
Aerodynamics
Materials / Fabrication
Subsystem Development
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Competition Requirement:◦ 20 Amp maximum draw◦ ¾ lb. maximum battery weight◦ Separate propulsion and control system
Research/Analyze Major Components◦ Batteries◦ Motor / ESC◦ Propeller◦ Transmitter / Receiver◦ Servos
Propulsion / Control Systems
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Propulsion / Control Systems
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Propulsion / Control Selection
Electrical System Motor
Transmitter Aurora 9 Type Himax HA2025-4200
Receiver Optima 7 Ch Receiver Weight 2.82 oz
Servos 4 Power HD D65 Kv 4200 rpm/v
Motor Controller Castle Creations Phoenix 25A Io 0.75 A
Batteries R 0.75 Ω
Type Receiver Propulsion Power 175 W
Brand KAN 180 Elite 1500 Thrust 2.23 lb
Capacity 180 mAh 1500 mAh Current Draw 15 A
Cell Voltage 1.2 V 1.2 V Gear Ratio 6.6:1
Max Current 20 A 20 A Propeller 12 x 10
Number of Cells 5 10
Pack Voltage 6 V 12 V
Weight 1.48 oz 8.10 oz
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Wing◦ Airfoil comparisons◦ Wing sizing tradeoffs
Stability ◦ Control surface sizing◦ Empennage sizing
Fuselage ◦ Streamlining
Aerodynamics
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Aerodynamics
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Airfoil Selection
Main Wing: Eppler 422
Tail Wing: NACA 0012
Aerodynamics Initial Sizing
Specification Value
Fuselage Volume 46.3 in3
Wing Area 406 in2
Effective Wing Span 44 in
Aspect Ratio 4.55
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Property Comparison◦ Weight◦ Strength◦ Stiffness
Considered Materials◦ Wood – Balsa, Bass, Plywood◦ Carbon Fiber / Composites◦ High Density Foam◦ Adhesive
Materials & Structures
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Primary structures◦ Wing spar
Uni-directional 1k CFRP/foam
◦ Wing ribs Balsa wood & aircraft ply
◦ Bulkhead CFRP & balsa ply
◦ Upper & lower spine CFRP
◦ Nose & tail fairing Single ply 1k plain weave CFRP
Materials Selection
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System Integration Ground Testing
◦ Assembly Time◦ Propulsion and
Controls◦ Structural Integrity
Flight Testing◦ Hand Launch◦ Control Handling◦ Flight Endurance◦ Payload Testing◦ Landing
Performance
Final Design
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Aircraft Specifications
Overall Aircraft Fuselage
Total Length 29.83 in Length 15.56 in
Total Width 47.98 in Width 5.02 in
Total Height 10.24 in Height 3.08 in
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M2: Steel Bar Configuration
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M3: Golf Ball Configuration
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Payload configurations
Mission 3:Golf Ball Storage
Qty: 16
Mission 2:Steel Bar Storage
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Electronics Layout
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System Component Breakdown
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Assembly Demonstration
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Suitcase Configuration
Disassembled Aircraft
Competition Risk Assessment Potential Risks
◦ Harsh landing / propeller-ground interference◦ High wind speed◦ Inexperienced pilot
Prototype◦ Novice aircraft designers / builders
Robust 1st design: Over-engineered Multiple flight tests
Final Design ◦ Much lighter, competitive design
Component supply redundancy◦ Recruited professional pilot
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Video
Flight Demonstration
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Questions?
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