Blue Grass Chemical Agent-Destruction Pilot Plant Quarterly Update June 11, 2014
Agent Blue Presentation (2 of 2)
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Transcript of Agent Blue Presentation (2 of 2)
Wing Configuration
Presented by:Jason Cantrell, James Lasater, Kevin Rausch, Jason Rue
1
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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