Wing Configuration

Presented by:Jason Cantrell, James Lasater, Kevin Rausch, Jason Rue

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University of FloridaSenior Design - Spring 2011

Airborne Research Engineering Systems

Restrictions and Requirements

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• Commercially available propulsion system• Propeller driven• Electric powered, 20 A limit• Batteries: 0.75 lbs, NiCad or NiMH• Hand launched• Box size 22’’ x 9’’ x 14.5’’ (45.5 total)

(half inch tolerance on each dimension)

Missions

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Mission 1: Dash to Critical Target•4 minute flight with no payload•Completed ½ mile laps normalized to best overall

Mission 2: Ammo Resupply•1.5 mile flight•Team determine payload size•Ammunition weight normalized to plane weight

Mission 3: Medical Supply•1.5 mile flight•Team determines payload quantity•Medical supply quantity normalized by highest overall

Aircraft Configuration

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Conventional Body

Rectangular Wings

V-Tail

Single Tractor Motor

Material Selection

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Fuselage: Carbon Fiber/ Kevlar(Impact Resistant)

Tail Boom: Carbon Fiber Rod(Rigid structure, Disassembles)

Wing+Tail: Balsa and Microlite(Light Weight)

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Aircraft Design Parameters

X 20

2.75 lb empty 1.68 oz each

4.75 lbmax weight

52 inchwingspan

520 inch2 wing area

10 inchchord

21 oz/ft2 wing loading

Aircraft Cost Analysis

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Propulsion ($310, 40%)

Avionics($230, 29.7%)

Materials($235, 30.3%)

Total: $775

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System Components and Weight Breakdown

Component Selection

Battery Pack 13 Elite 1500s

Propeller Mission 1 Graupner 10x6

Propeller Mission 2 & 3 Graupner 11x6

Motor (Gear Ratio) NEU 1105/3Y (4.4:1)

Speed Controller CC Phoenix 25

Transmitter Futaba 6EXP

Transmitter Battery 8 KAN 400

Receiver CC Berg 7P

Receiver Battery 5 KAN 400

Aileron Servos Qty 2: HS-65

Ruddervator Servos Qty 2: HS-65Total Weight Breakdown

Wing Assembly Solution

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• 2 carbon fiber spars are mounted in wings and are taped at seams for flight

Tail and Boom Assembly Solution

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•Boom is a carbon fiber rod telescoping from 0.608”-0.5” in diameter

•Held in place by ¼” steel pin at fuselage and 3/32” pin midway down boom

•Tail is clipped onto release buckles

Static Testing

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Parameter Tested Data Calculated Data Percent Error

Graupner 11x6

Thrust (lb) 3.01 2.25 25.3%

Voltage (V) 11.91 10.41 12.6%

Amperage (A) 17.7 19.3 9.04%

RPMs 7839 7656 2.33%

Thrust Testing

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Vibration Testing

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First Bending Mode Substructure Mode

Carbon Fiber Spars Substructure Mode

Systems Testing

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24 golf ball flight attempt

Weight limitations exceeded

Materials SelectionSimulation System

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Materials SelectionGround Station

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Materials SelectionControl System Testing

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Materials SelectionControl System Testing

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Materials SelectionWaypoint Tracking

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Materials SelectionThrottle Variation

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Materials SelectionAltitude Correction

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Materials SelectionUndemanding Course

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Materials SelectionDemanding Course

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Materials SelectionLow Control Effort

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Materials SelectionMinimal Course Deviation

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Materials SelectionPrecise Location Tracking

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Materials SelectionDynamic Performance

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Materials SelectionVariable Environment

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Materials SelectionRapid Course Correction

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Materials SelectionRapid Altitude Adjustment

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Materials SelectionIntelligent Throttle and Altitude Control

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Materials SelectionRobust Control System

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Materials SelectionLive Simulation

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Materials SelectionDiscussion

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