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
Movie
March 24, 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
March 24, 2005
AAE 451 – Team 5

4. Design Features Features / Unique Aspects Stealth Theme Twin Booms
Pusher Prop
Multi-Sweep Wing
Predicted Weight: 0.84 lbf
March 24, 2005
AAE 451 – Team 5

5. Design Properties Wing Horizontal Tail Overall Aircraft Vertical Tail
Fuselage
March 24, 2005
AAE 451 – Team 5

6. Design - Dimensions
March 24, 2005
AAE 451 – Team 5

7. Aerodynamics - Airfoils
Low Re Number
91903 (Stall) (Cruise)
Wing
Eppler E212
Tail
Eppler E169
Horizontal Tail
NACA 0010
Vertical Tail
NASG:
UIUC:
March 24, 2005
AAE 451 – Team 5

8. 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
March 24, 2005
AAE 451 – Team 5

9. 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
March 24, 2005
AAE 451 – Team 5

10. Aerodynamics - Drag Parasite Drag Buildup Sref = reference area [ft2]
Cf = skin friction coefficient
K = form factor
Q = interference factor
March 24, 2005
AAE 451 – Team 5

11. Aerodynamics – L/D L/Dmax=13.21 Loiter at α=.71°,4.46°
Loiter at 0.866*L/Dmax2
Wing Incidence: 0°
Tail Incidence: -3°
L/D vs. α
L/D=4.7
L/D
α (deg)
2 Raymer, D.P., Aircraft Design: A Conceptual Approach, Virginia, 1999, pp 27
March 24, 2005
AAE 451 – Team 5

12. Class 2 Tail Sizing (X-plot)
March 24, 2005
AAE 451 – Team 5

13. Trim Diagram
March 24, 2005
AAE 451 – Team 5

14. 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
March 24, 2005
AAE 451 – Team 5

15. Class 2 Vertical Tail Sizing (X-plot)
0.218 ft2
March 24, 2005
AAE 451 – Team 5

16. Feedback Controller Pitch Rate Feedback to Elevator
March 24, 2005
AAE 451 – Team 5

17. Feedback Controller Damping Ratio w/o Feedback = 0.74
Desired Damping Ratio = 0.35 – 1.3
We chose a Damping Ratio = 0.95
Feedback Gain Required = 0.07
March 24, 2005
AAE 451 – Team 5

18. 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
0.61
0.60
March 24, 2005
AAE 451 – Team 5

19. Propeller Plots – 6 inch prop
Take-Off
Loiter
CT = 0.076
CP = 0.042
η = .61
CT = 0.025
CP = 0.023
η = .83
March 24, 2005
AAE 451 – Team 5

20. 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
Input Current
11.7 Amps
Output Power
0.078 hp
March 24, 2005
AAE 451 – Team 5

21. 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.
March 24, 2005
AAE 451 – Team 5

22. Landing Gear Main gear (2) Tail Gear (2) Single beam, t = 0.0017 ft
Stroke = ft
Weight = lbf
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)
18 gauge steel wire
Prevent prop and tail strike
Parameters
θ = 30°
Material = Al
Ngear = 3 (Gen. Av.)
March 24, 2005
AAE 451 – Team 5

23. Structures - CG
March 24, 2005
AAE 451 – Team 5

24. Structures - Load Analysis
Structural loads from code – basic equations used
τ max = lbf/ft2
Mroot = 0.26 ft-lbf
σmax = lbf/ft2
Deflections
δy = 9.1e-11 ft
δΦ = 1.1e-4 degrees
March 24, 2005
AAE 451 – Team 5

25. 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.
March 24, 2005
AAE 451 – Team 5

26. Scheduled Tests Drop Test Wing Load Test Flight Test Height of 2.5 ft
Tests landing gear and crash survivability
Wing Load Test
Test maximum load of wing
Flight Test
Propeller test
Feedback gain test
Control surface test
March 24, 2005
AAE 451 – Team 5

27. Strength Testing
Failure at 26 lbf
March 24, 2005
AAE 451 – Team 5

28. Strength Testing Failure due to buckling March 24, 2005
AAE 451 – Team 5

29. Manufacturing Wing/fuselage and tails milled using CNC
Wet lay-up with 0.6 oz. bidirectional s-glass
Holes cut and tapped for component placement
Epoxy bonding of tails and booms
Mechanical attachment of landing gear, motor, etc.
March 24, 2005
AAE 451 – Team 5

30. Manufacturing - Booms Circular holes cut for boom insertion
Foam is bonded inside and out to tube
Boom pinned into place with wire
March 24, 2005
AAE 451 – Team 5

31. Overall Schedule To be accomplished before 1st flight
Order parts – March 10
Build prototype wing – March 11
Test prototype strength – March 22
CDR – March 24
CNC Parts – by March 28
Fiberglass Parts – by April 3
Build – by April 7
Test and modify – until flight date
March 24, 2005
AAE 451 – Team 5

32. 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
March 24, 2005
AAE 451 – Team 5

33. Current Issues Propeller air flow Engine heating Manufacturability
Boom attachments
CG movement
March 24, 2005
AAE 451 – Team 5