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:March 1, 2011 Competition Date:April 15-17, 2011

Aircraft Design Requirements SystemConstraint 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 Mission Priority 1. Mission 3 2. Mission 2 3. Mission 1 Projected Maximum Score Mission 1 = 1 Mission 2 = 1.5 Mission 3 = 2

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 Battery High Energy Density Greater Longevity Less Volatile Low Recharge Time Transmitter Long Distance No Signal Interference FCC Requirement MHz 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 Desired Characteristics

Electronics & Controls Design Battery Selection NiMH Long Lasting Chemically Stable Quick Charge Transmitter Selection Spektrum DX6i No Signal Interference Meets all FCC Requirements Options/Selection

Power & Propulsion Systems Motor Efficient Optimal Power Generation Light Weight Low Current Draw Propulsion Optimal RPM/Torque High Thrust Light Weight Low Drag Desired Characteristics

Power & Propulsion Systems 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 Options/Selection

Wing Design High Aerodynamic Efficiency (L/D) Moderate Wing Loading High Lift At Low Speeds Low Stall Speed Hand Launched Stable Flight Moderate Maneuverability Desired Characteristics

Wing Design Wing Parameters Wing Span Planform Area Aspect Ratio C L /C D Wing Section Control Surfaces Wing Layout Sweep Diahedral Wing Configuration Twist Taper Wingtip Design Options/Selection

Materials Selection & Fabrication Light Weight Ideal Yield Strength Stiff in Bending Simple To Manufacture Desired Characteristics

Materials Selection & Fabrication Chosen Materials: 1.CFRP Loading Tension 2.Wood Loading Longitudinal

Materials Selection & Fabrication Hybrid Structures Sandwich Light Weight Resistant to Bending Resistant to Buckling Shape Factors I-Beam Rectangle Hollow Shape Options/Selection

Overall Layout High Storage Volume Capacity Low Drag Optimal Center of Gravity Adequate Maneuverability Fulfillment of Design Requirements Safety and Size Ease of Assembly Desired Characteristics

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?