1. Team 5 Final Design Review
Trent Lobdell Ross May Maria Mullins
Christian Naylor Eamonn Needler Charles Reyzer
James Roesch Charles Stangle Nick White

2. Outline Mission Requirements Team Design Aerodynamics
Dynamics & Control
Propulsion Necessary / Predicted Necessity
Structures / Landing Gear
Manufacturing
Vehicle Performance / Predictions
Lessons Learned
Proof of Flight
April 28, 2005
AAE 451 – Team 5

3. Requirements Design Requirements & Objectives
Take-Off and landing distance: 100 ft*
Take-Off with minimum climb angle: 20°
Endurance: 15 min*
Typical descent angle of: 5.5°
Stall Speed: 20 ft/s
Loiter Speed: 28 ft/s*
Minimum Turn speed: ft/s*
Turn Radius: 35 ft*
Operating Altitude: 18 ft*
Operational Airspace: 360x150 ft
*Changed Requirements from Mission Specification
April 28, 2005
AAE 451 – Team 5

4. Design Features / Unique Aspects
Stealth Theme
Multi-Sweep Wing
Twin Booms
Pusher Prop
Sweet “Paint” Job
April 28, 2005
AAE 451 – Team 5

5. Sizing and Constraints
Weight Estimation Using Historical Data
Constraint Diagram
Power Loading [lbf/Bhp]
W-WE [lbf]
Takeoff Weight [lbf]
Wing Loading [lbf/ft2]
Initial Weight : 0.84 pounds
Final Weight : pounds
April 28, 2005
AAE 451 – Team 5

6. Design Properties Wing Horizontal Tail Overall Aircraft Vertical Tail
Fuselage
April 28, 2005
AAE 451 – Team 5

7. Design - Dimensions
April 28, 2005
AAE 451 – Team 5

8. Aerodynamics - Airfoils
Low Re Number
91903 (Stall) (Cruise)
Wing
Eppler E212
Tail
Eppler E169
Horizontal Tail
NACA 0010
Vertical Tail
NASG:
UIUC:
April 28, 2005
AAE 451 – Team 5

9. Aerodynamics – Geometry
Defined Sweep Angles (Λ)
Defined taper ratio (λ) of 1st segment
Defined Span Ratio of 2 segments
Adjust to balance
Style
Aspect Ratio
Tip Chord feasibility
April 28, 2005
AAE 451 – Team 5

10. Aerodynamics - Lift Sweep Corrected Hembold Equation1
Lift Coefficients vs. α
Prandtl Lifting Line Theory1
CL and Cl
CLmax (Hembold) : 0.74
Max Lift (Hembold) : 1.10 lbf
α (deg)
1 Anderson, J.D., Fundamentals of Aerodynamics, New York, 2001, pp
April 28, 2005
AAE 451 – Team 5

11. Aerodynamics - Drag Parasite Drag Buildup Sref = reference area [ft2]
Cf = skin friction coefficient
K = form factor
Q = interference factor
April 28, 2005
AAE 451 – Team 5

12. Aerodynamics – L/D L/Dmax=13.21 Loiter at α = 0.71°,4.46°
L/D vs. α
L/Dmax=13.21
Loiter at α = 0.71°,4.46°
Loiter at 0.866*L/Dmax2
Wing Incidence: 0°
Tail Incidence: -3°
L/D=4.7
L/D
α (deg)
2 Raymer, D.P., Aircraft Design: A Conceptual Approach, Virginia, 1999, pp 27
April 28, 2005
AAE 451 – Team 5

13. Class 2 Tail Sizing (X-plot)
Static Margin: 17°
Final Xn: 0.77 ft
Tail Area: 0.24 ft2
April 28, 2005
AAE 451 – Team 5

14. Trim Diagram δe Trim Diagram for Cf/C = 0.5 αplane Cmcg CLtotal
April 28, 2005
AAE 451 – Team 5

15. Control Surface Sizing
Aileron size / dimension:
Area:0.18 ft2 (each)
Length: 1.06 ft
Root Chord: 0.24 ft
Tip Chord: 0.10 ft
Elevator size / dimension:
Area: 0.10 ft2
Span: 0.50 ft
Chord: 0.21 ft
Rudder size / dimension:
Area: 0.07 ft2 (each)
Base 1: 0.25 ft
Base 2: 0.12 ft
Height: 0.35 ft
April 28, 2005
AAE 451 – Team 5

16. Class 2 Vertical Tail Sizing (X-plot)
0.218 ft2
April 28, 2005
AAE 451 – Team 5

17. Feedback Controller Pitch Rate Feedback to Elevator
April 28, 2005
AAE 451 – Team 5

18. Feedback Controller April 28, 2005 AAE 451 – Team 5
Damping Ratio w/o Feedback = 0.72
Desired Damping Ratio = 0.35 – 1.3
We chose a Damping Ratio = 0.99
Feedback Gain Required = 0.091
April 28, 2005
AAE 451 – Team 5

19. Propeller Take-Off Characteristics
Type
2-Bladed
3-Bladed
Propeller Diameter
6 in
5 in
Pitch
4 in
3 in
Operating RPM
14300 RPM
16400 RPM
Efficiency
0.43
0.60
April 28, 2005
AAE 451 – Team 5

20. Propeller Plots – 6 inch prop
Take-Off
Loiter
CT = 0.076
CP = 0.042
CT = 0.025
CP = 0.023
April 28, 2005
AAE 451 – Team 5

21. Motor Selection - Graupner Speed 400 6V (Direct Drive) Characteristics
Engine Characteristics
Propeller Shaft Diameter
0.091 in
Engine Diameter
1.08 in
Engine Length
1.5 in
Weight
2.55 oz
Rated Horsepower
0.12 hp
Rated Loaded RPM
15500 RPM
Operating Conditions
Operating RPM (Take Off)
14300 RPM
Input Voltage
8.34 Volts  11.1 Volts
Input Current
11.7 Amps
Output Power
0.078 hp
April 28, 2005
AAE 451 – Team 5

22. Battery & Speed Controller Selection
Thunder Power 3 Cell Li-Po
Rated for Amps
2100 mAh
Allows for extended endurance as specified in the DR&O
4.6 oz.
JETI 12 Amp Microprocessor Motor Controller
For 2-3 Cell LiPo
Weight = 0.53 oz.
1x0.75x0.3 in.
NiCd
4 Cells
4.8 Volts
300 mAh
2.3 oz.
April 28, 2005
AAE 451 – Team 5

23. Landing Gear Main gear (2) Tail Gear (2) Single beam, t = 0.0052 ft
30° angle for lateral stability
20° in front of CG for longitudinal stability
Absorb impact
Gear deform instead of break
Easy to change
Tail Gear (2)
Heavy duty control horns
Prevent prop and tail strike
Parameters
θ = 30°
Material = Al
ngear = 3 (Gen. Av.)
April 28, 2005
AAE 451 – Team 5

24. Structures - CG
April 28, 2005
AAE 451 – Team 5

25. Structures - Load Analysis
Structural loads from code – basic equations used
τ max = lbf/ft2
Mroot = 0.26 ft-lbf
σmax = lbf/ft2
April 28, 2005
AAE 451 – Team 5

26. Structures - Load Analysis
Torsion Loads
T = 0.1 ft-lbf. at high maneuver
Failure of wing (most likely due to buckling) occurs at
ncr = 38 or at σcr = 32 psf.
April 28, 2005
AAE 451 – Team 5

27. Predicted Flight Performance
Max. Turning Radius: 35 ft (DR&O)
Bank Angle: 34.82°
Turn Rate: 0.8 rad/s
Min. Turning Radius: ft (Limit)
Bank Angle: 65.85°
Turn Rate: 2.57 rad/s
Maximum Climb Angle: 26.77°
Take-Off Distance: ft
Landing Distance: ft
Add Roll Rate
Adjust Max Climb angle
April 28, 2005
AAE 451 – Team 5

28. Strength Testing
Failure at 26 lbf
April 28, 2005
AAE 451 – Team 5

29. Strength Testing Failure due to buckling April 28, 2005
AAE 451 – Team 5

30. Manufacturing – Milling
Wing/fuselage and tails milled using CNC
Wet lay-up with 0.6 oz. bidirectional s-glass
April 28, 2005
AAE 451 – Team 5

31. Manufacturing – “Surgery”
Circular holes cut for boom insertion
Boom Inserted and bonded with Epoxy
Hatch cut and tapped for component placement
April 28, 2005
AAE 451 – Team 5

32. Manufacturing – Component Placement
Batteries
Soldered Motor
Installed Servos
Connected all components to radio receiver
Connected Batteries
Rate Gyro
Speed Controller
Radio Receiver
Motor
April 28, 2005
AAE 451 – Team 5

33. Ground Testing Control Surfaces Servos Static Endurance
Pitch-Rate Gyro
Two-Foot Drop Test
April 28, 2005
AAE 451 – Team 5

34. Flight Testing Four Days Nine Tests One Flight Repairs Problem Solving
More Repairs
Accomplishment
April 28, 2005
AAE 451 – Team 5

35. Lessons Learned Weight code was not accurate
Historical data needs to be updated with R/C aircraft
Lack of understanding of speed controller and battery configuration
Weight always goes up
CG always goes back
Cost always goes up
April 28, 2005
AAE 451 – Team 5

36. COMPONENT PROPERTIES
UNITS
AS DESIGNED
AS FLOWN
Weight
lbf
0.84
1.88
Horsepower Hp
0.073
0.100
Wing Area
ft2
4.95
Horizontal Tail Size (Including Elevator)
0.48
Elevator Area
0.10 
Propeller Efficiency
Non-Dimensional
43%
40%
Propeller Size in
6.00
Vertical Tail Size (Including Rudder)
0.23
Rudder Area
0.07 
Aileron Area
 0.18
0.18 
Horsepower from Voltage
Volts
8.4
11.1
Wheel Diameter
1.25
3.00
Horizontal Tail A/C Distance from the Wing Quarter Chord ft
2.29
Vertical Tail A/C Distance from the Wing Quarter Chord
2.31
2.39
Wing Chord
0.72
Distance from Centerline to Inboard Aileron
0.58
Distance from Centerline to Outboard Aileron
0.27
Chord of Aileron
0.18
Maximum Surface Deflection
deg
30.00
35.00
Chord of Elevator
0.21
Chord of Rudder
CG Distance to Nose
0.65
0.75
CG Distance to Wing Quarter Chord
0.13
0.00

37. A Success Story of the Ages
April 28, 2005
AAE 451 – Team 5

38. Questions?
April 28, 2005
AAE 451 – Team 5