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?