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Presentation OutlineTeam IntroductionProject OverviewCompetition SpecificationsMission ProfileScore AnalysisSubsystem BreakdownProject TimelineSummary
UAV TeamMatthew Martin – Project Manager, MEJosiah Shearon – Mechanical Technical Lead, METJ Worden – Design Req. Specialist, MEDavid Neira – Treasurer, MEJosh Mellen – Electrical Technical Lead, ECEOna Okonkwo – Secretary, ECE
OverviewDevelop a UAV which will satisfy the AIAA
Design/Build/Fly Competition mission profileCompetition Details
Sponsors: Cessna, Raytheon
Location: Tucson, AZ
Design Report Submission Date: March 1, 2011
Competition Date: April 15-17, 2011
Aircraft Design RequirementsSystem 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 ContainerUAV 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)
Mission OneDash to critical target
Mission description4 minute time limit
GoalAchieve maximum number of laps in specified
timeTime starts during first hand launch attempt
M1: Path to GoalAerodynamic BodyLow Drag Lightweight High ThrustBattery LongevityHigh Maneuverability
Mission TwoAmmo Re-Supply
Mission descriptionPayload flight
Team selected/supplied steel bar(s)
GoalComplete 3 lapsMaximize payload-to-weight ratio
M2: Path to GoalHigh Lift Airfoil DesignAdequate Structural IntegrityLightweight AircraftGood Flight Stability Under Heavy Load
Mission ThreeMedical Supply Mission
Mission descriptionPayload flight
Team selected quantity of golf balls
GoalComplete 3 lapsTransport maximum number of golf balls
Overall Flight Score Analysis
Mission Priority1. Mission 32. Mission 23. Mission 1
Projected Maximum ScoreMission 1 = 1Mission 2 = 1.5Mission 3 = 2
UAV Team SpecializationsMatthew Martin – Overall Aircraft LayoutJosiah Shearon – Materials Selection & FabricationTJ Worden – Wing DesignDavid Neira – Power & PropulsionJosh Mellen – Electronics & Control (Hardware)Ona Okonkwo – Electronics & Control (Software)
Electronics & Controls Design
BatteryHigh Energy DensityGreater LongevityLess VolatileLow Recharge Time
TransmitterLong DistanceNo Signal InterferenceFCC Requirement
72.01-72.99MHz
Control BoardLightweight/EfficientMinimum One DC Motor
(Propeller), Two Servos (Rudder/Elevator)
Gyroscopic FeatureRadio Fail-Safe Maneuver
Kill Throttle, Roll Right, Yaw Right, Nose Up
Desired Characteristics
Electronics & Controls Design
Battery SelectionNiMH
Long LastingChemically StableQuick Charge
Transmitter SelectionSpektrum DX6i
No Signal InterferenceMeets all FCC
Requirements
Options/Selection
Power & Propulsion Systems
MotorEfficientOptimal Power GenerationLight WeightLow Current Draw
PropulsionOptimal RPM/TorqueHigh ThrustLight WeightLow Drag
Desired Characteristics
Power & Propulsion Systems
MotorBrushless
Low Weight High Efficiency Ideal RPM/Torque
Gear/Belt Reduction Increases Output RPM Maintains High Torque
PropulsionDucted 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 LoadingHigh Lift At Low SpeedsLow Stall Speed
Hand LaunchedStable FlightModerate Maneuverability
Desired Characteristics
Wing Design
Wing ParametersWing SpanPlanform AreaAspect RatioCL/CD
Wing SectionControl Surfaces
Wing LayoutSweepDiahedralWing ConfigurationTwistTaperWingtip Design
Options/Selection
Materials Selection & Fabrication
Light WeightIdeal Yield StrengthStiff in BendingSimple To Manufacture
Desired Characteristics
Materials Selection & Fabrication
Chosen Materials:1.CFRP• Loading• Tension
2.Wood• Loading• Longitudinal
Materials Selection & Fabrication
Hybrid StructuresSandwich
Light WeightResistant to BendingResistant to Buckling
Shape FactorsI-BeamRectangleHollow Shape
Options/Selection
Overall Layout
High Storage Volume CapacityLow DragOptimal Center of GravityAdequate ManeuverabilityFulfillment of Design Requirements
Safety and SizeEase of Assembly
Desired Characteristics
Overall LayoutOptions/Selection
FuselageLowest Drag CoefficientBody Lines
Smooth/Sharp Landing Gear
Retractable/FixedWeight Distribution
Compact/Dispersed
Subsystem IntegrationPropulsion Configuration
Single/Multiple MotorsFront/Back Driven
Wing ConfigurationMain/Tail SpacingWing Location
SummaryDevelop aircraft with the following features:
High Storage CapacityLightweightHeavy Payload CapacityAdequate Speed/Maneuverability
February 20, 2011Finish Fabrication of UAVSubmit Design Report
Competition: April 15-17, 2011