University of Florida Wing Configuration Senior Design - Spring 2011
Airborne Research Engineering Systems
Presented by: Jason Cantrell, James Lasater, Kevin Rausch, Jason Rue 1
Restrictions and Requirements • • • • • •
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)
2
Missions 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
3
Aircraft Configuration Rectangular Wings
V-Tail
Single Tractor Motor
Conventional Body 4
Material Selection Wing+Tail: Balsa and Microlite (Light Weight)
Tail Boom: Carbon Fiber Rod (Rigid structure, Disassembles)
Fuselage: Carbon Fiber/ Kevlar (Impact Resistant) 5
Aircraft Design Parameters 21 oz/ft2 wing loading
52 inch wingspan
2.75 lb empty
520 inch2 wing area
10 inch chord
1.68 oz each
4.75 lb max weight
X 20 6
Aircraft Cost Analysis Propulsion ($310, 40%)
Avionics ($230, 29.7%)
Total: $775 Materials ($235, 30.3%)
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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 Transmitter
CC Phoenix 25 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-65
Total Weight Breakdown 8
Wing Assembly Solution • 2 carbon fiber spars are mounted in wings and are taped at seams for flight
9
Tail and Boom Assembly Solution • 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
10
Static Testing
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%
11
Thrust Testing
12
Vibration Testing
First Bending Mode
Substructure Mode
Carbon Fiber Spars
Substructure Mode
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Systems Testing
24 golf ball flight attempt
Weight limitations exceeded 14
Materials Simulation Selection System
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Materials Ground Selection Station
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Control Materials System Selection Testing
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Control Materials System Selection Testing
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Materials WaypointSelection Tracking
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Materials Throttle Variation Selection
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Materials Altitude Correction Selection
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Undemanding Materials Selection Course
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Materials Demanding Selection Course
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Materials Low Control Selection Effort
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Minimal Materials Course Selection Deviation
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Precise Materials Location Selection Tracking
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Dynamic Materials Performance Selection
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Variable Materials Environment Selection
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Rapid Materials CourseSelection Correction
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Rapid Materials AltitudeSelection Adjustment
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IntelligentMaterials Throttle and Selection Altitude Control
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Robust Materials Control Selection System
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Materials Live Simulation Selection
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Materials Discussion Selection
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