Project Specifications and Scope

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)

Flight Course

Governing Equations

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

M3: Path to GoalMaximize Cargo Bay VolumeHigh Payload CapacityLightweight Payload Stabilizer

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

Questions?