Fhi 360 Aids2012 Traditional Initiation Presentation 19 July 2012 Final
Final presentation 4 19
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MIDTERM PRESENTATIONAEROSPACE 402B
The Flyin’ LionELECTRIC LIGHT SPORT AIRCRAFT
ALEX KARNSHARSHAD KAPOORSTEVE BARRDAVID BAVERMIKE DISORICHRIS GUMKE
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3-VIEW
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FRONT VIEW
4.5 ft.
3
2°
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TOP VIEW
4
7 ft.
10 ft.
3 ft.
46 ft.
3.5 ft.
2 ft.
8 ft.
1 ft.
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SIDE VIEW
5CG. Location .35c and Neutral Point location at .44c
3 ft.
13.3 ft.
4 ft.
6.5 ft.6.25
ft. 2 ft.2.5 ft.
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STABILITY AND CONTROL
• FWD CG LIMIT: -0.17c–Based on CLmax
in Ground Effect
• AFT CG LIMIT: 0.44c–Based on Neutral Point Location
• MAX STATIC MARGIN: 9%
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SIDE VIEW
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STABILITY AND CONTROL
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Component Weight of Part (lb.) CG location from nose (ft.)Passengers 400 8.2Batteries 400 3.5
Motor 42 12Controller 30 2Propeller 15 10
Seats 40 0.5Tail 60 8.2
Fuselage + Wing 313 7.5
Forward limit CG location Aft limit Static Margin6.40 8.21 8.61 9%
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SPECIFICATIONS
Parameters Value
Power Available (hp) 80.0
Engine Efficiency 0.90
Max Propeller Efficiency 0.87
Cabin Width (ft) 5.00
Vertical Tail Height (ft) 4.50
Base Vertical Tail Chord (ft) 4.00
Tail Chord (ft) 2.00Tail Span (ft) 8.00
Span Efficiency of Tail 0.95
Parameters Value
Weight (lbs) 1300
Span (ft) 46.0
Root Chord (ft) 3.50
Tip Chord (ft) 3.00
Wing Area (ft^2) 156
Wing Loading (lb/ft^2) 8.30
Aspect Ratio 13.6
Taper Length (ft) 10.0
Taper Ratio 0.94
Span Efficiency 0.969
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AILERON SIZING
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Aileron Sizey2 22 ft
y1 12 ft
Roll Rate 45 deg/sec
y2
y1
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Vertical Tail SizingEstimated Side Wash
Parameter * 0.17
Effective Tail Parameter 0.7
Vertical Tail Lift Slope 6.25/rad
Vertical Tail Volume 0.026
Weathercock Stability -0.04
Rudder Power -0.051Rudder Deflection @ Max Sideslip ** 9.12°
* Ideal Side Wash Parameter from Morelli Paper** IAW FAR Section 23 – Max sideslip for crosswinds is 11.5°
VERTICAL TAIL
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TURN PERFORMANCE(BASED ON AERODYNAMIC PARAMETERS)
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FAR Allowable Range: -1.5G to 3.8G
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CABIN DRAWING
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POWERPLANT AND BATTERIES
ENGINE:YUNEEC POWER DRIVE 60
POWER:81 HP
OPTIMUM RPM:2,400
WEIGHT:66 LBS
BATTERY ENERGY DENSITY: 240 WHr/Kg
BATTERY WEIGHT: 400 LBS
BATTERY EFFICIENCY: 0.90
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WING AIRFOILNLF 0115
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HORIZONTAL & VERTICAL TAIL AIRFOIL
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EPPLER 521
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TOTAL DRAG BUILD-UP
Airspeed (kts)
Landing Gear (lbs)
Fuselage Drag (lbs)
Wing Drag (lb)
Empennage Drag (lbs)
Total Drag(lbs)
40 0.64 4.20 53.17 0.29 58.30
43 0.74 4.78 47.11 0.32 52.96
45 0.81 5.19 43.80 0.34 50.15
50 1.00 6.28 37.44 0.40 45.11
75 2.25 13.03 26.19 0.76 42.23
100 4.00 21.86 28.45 1.24 55.55
120 5.76 30.35 34.33 1.72 72.15
140 7.84 40.05 42.57 2.29 92.75
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TOTAL DRAG BUILD-UP
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TotalInducedProfile
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LIFT TO DRAG RATIO
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MAX L/D = 32@ 65 KNOTS
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POWER REQUIRED AND AVAILABLE VS. VELOCITY
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ftft
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RATE OF CLIMB AND TIME TO CLIMB(INCLUDING SERVICE AND ABSOLUTE CEILINGS)
NOTE: Because the Flyin’ Lion cannot carry oxygen, the highest altitude it can fly is at 12,000 ft. The cruise altitude can be reached in approximately 4.3 minutes assuming constant rate-of-climb and flying at maximum rate-of-climb velocity. 21
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STALL SPEED
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LIFT CURVE
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ENDURANCE AND RANGE
• C = BATTERY ENERGY DENSITY• WB = BATTERY WEIGHT
• ηB = BATTERY EFFICIENCY
• ηC = CONTROLLER EFFICIENCY
• ηB = PROPELLER EFFICIENCY
• Preq = POWER REQUIRED• V = VELOCITY
ENDURANCE: RANGE:
E = 2.5 HOURS & R = 220 MILES@ SEA LEVEL, CRUISE SPEED
E = 3.5 HOURS & R = 360 MILES@ SEA LEVEL, CRUISE SPEED WITH
EXTENDED BATTERY PACK
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TAKE-OFF AND LANDING DISTANCES
GROUND ROLL:
SGROUND ROLL = 315.61 FT
LANDING DISTANCE:
SLANDING = 1341.85 FT
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V-n Diagram
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WEIGHT AND COST ESTIMATION
Engine, Motor, and Battery SystemComponent Weight (lbs) Cost ($) # of Parts Total Weight(lb) Total Cost ($)
Propeller 15 2500 1 15 2500Electric Engine (80HP) 42 8200 1 42 8200Battery Pack (Li Ion) 191 900 2 382 1800Power Block 40 Controller 15.5 1789 1 15.5 1789
E Charger 15.4 900 1 15.4 900Electric Wiring System 1.9 400 4 7.6 1600Engine Cowling 20 1300 1 20 1300Spinner Cover 1 340 1 1 340Section Total: 498.5 18429
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WEIGHT AND COST ESTIMATION
Cockpit Fuselage, Instruments and Controls
Component Weight (lbs) Cost ($) # of Parts Total Weight (lbs) Total Cost ($)
Aircraft Seats 20 100 2 40 200Instrument Panel 19.5 6138 1 19.5 6138Flight Controls 2 140 2 4 280Canopy 10 1469 1 10 1469Restrain Belts 4 80 2 8 160Rudder Pedals 2 229 2 4 458Flight Control Linkages 25 1900 1 25 1900Composite Skin/ Fuselage 45 2800 1 45 2800Passengers 200 0 2 400 0Section Total: 555.5 13405
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WEIGHT AND COST ESTIMATION
Wing, Ailerons, and Structure
Component Weight (lbs) Cost ($) # of Parts Total Weight (lbs)
Total Cost ($)
Composite Wing, Aileron, and Skin Structures 146 9100 1 146 9100
Aifrcraft Lights 0.5 120 4 2 480Section Totals: 148 9580
Empennage and Tail Boom
Component Weight (lbs)
Cost ($)
# of Parts
Total Weight (lbs)
Total Cost ($)
Composite Tail Boom, Horizontal and Vertical Tail, and Skin/ Structure
60 3800 1 60 3800
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WEIGHT AND COST ESTIMATION
Forward and Main Landing Gear, Tires, and Wheel Pants
Component Weight (lbs)
Cost ($)
# of Parts
Total Weight (lbs)
Total Cost ($)
Landing Gear Struts 3 140 3 9 420Tires 4 114.95 3 12 344.85Wheel Pant Composite Skin 1 70 3 3 210Section Totals: 24 974.85
Overall System Totals:
Cost ($) 46k
Weight (lbs) 1286
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• Environmentally Friendly• Cost Effective– Low Operating Costs– Low Unit Cost
• iPad integrated• Quiet• Trainer Aircraft– Easy Learning Curve
• Excellent Maneuverability
KEY POINTS
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• Modern Instrument Panel• LSA Certifiable• Lightweight Composite Design• Laminar Flow Airfoil– Low Drag
• FUN
KEY POINTS
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QUESTIONS