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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