1. CDR: Aether “Angry Mosquito”
AAE 451, Team 3
October 26, 2006
Mark Davis Ashley Gordon
Hank Kneitz Ryan Mulligan
Joshua Rodewald Brandon Wampler
Mathieu Hautier Samantha Pearcy

2. Presentation Outline Mission Overview & Initial Sizing Aerodynamics
Structures and Weights
Propulsion System
Dynamics & Controls
Cost Analysis & Remaining Work
April 5, 2019
AAE 451, Aether Aerospace

3. Design Mission Overview
Take-off and landing distance ≤120 ft
Take-off at minimum climb angle 35º
Climb to 20 ft
High-speed ¼ mile dash
Loiter for 5 minutes
VStall < 30 ft/sec
Return home at the most economical speed
Carry payload of 1 lb
Cost < $250 to build
April 5, 2019
AAE 451, Aether Aerospace

4. Aircraft Concept The Angry Mosquito Low wing V-tail
Tail dragger, fixed racing gear
Streamlined fuselage
11 in
3.5 ft
4 ft
April 5, 2019
AAE 451, Aether Aerospace

5. CDR: Aether Angry Mosquito
Mission Overview
Aerodynamics
Structures and Weights
Propulsion System
Dynamics & Controls
Cost Analysis
April 5, 2019
AAE 451, Aether Aerospace

6. Wing Airfoil Section – MH 32
Used on electric powered pylon racers
Designed for low Re
April 5, 2019
AAE 451, Aether Aerospace

7. Aspect Ratio Trade Study
Results
ARopt < 2
Solution
ARdesign = 5 for D&C
CDmin =
(Cf = )
Other Trends:
ARopt Inversely proportional to Vmax
ARopt Directly proportional to Wo
ARopt < 2
ARdesign = 5
April 5, 2019
AAE 451, Aether Aerospace

8. Wing and Tail Geometry Wing V-Tail Airfoil MH 32 NACA 0009 Area
Quarter chord line
Wing
V-Tail
Airfoil
MH 32
NACA 0009
Area
3.25 ft2
1.1 ft2 AR 5
3.25
Span
4.03 ft
1.88 ft
Taper Ratio
0.45
LE Sweep 0º
25°
c/4 Sweep
-4.34º
12.7°
TE Sweep
-16.88º 0°
Dihedral 4º
29°
Incidence
-2º -
Leading Edge
.5 ft
1.11 ft
2.02 ft
Quarter chord line
Leading Edge
0.80 ft
0.36 ft
0.94 ft
April 5, 2019
AAE 451, Aether Aerospace

9. Fuselage Length Sizing
Goals:
Minimize Weight
Minimize Drag
Considerations:
Minimum build-able fuselage length
Class 1 tail sizing
April 5, 2019
AAE 451, Aether Aerospace

10. Drag Build-Up Analysis
Total CDo =
April 5, 2019
AAE 451, Aether Aerospace

11. Aircraft Drag Polar
April 5, 2019
AAE 451, Aether Aerospace

12. Lift Coefficient Curve
*a in radians
3-D coefficients converted from 2-D experimental data
April 5, 2019
AAE 451, Aether Aerospace

13. CDR: Aether Angry Mosquito
Mission Overview
Aerodynamics
Structures and Weights
Propulsion System
Dynamics & Controls
Cost Analysis & Remaining Work
April 5, 2019
AAE 451, Aether Aerospace

14. Structures and Weights
April 5, 2019
AAE 451, Aether Aerospace

15. Weight and Balance Overall weight: 5.5lbs CG : 0.965 ft from nose
Moments/Products of Inertia
April 5, 2019
AAE 451, Aether Aerospace

16. Weight and position of the main parts
April 5, 2019
AAE 451, Aether Aerospace

17. Wing Structure Polyurethane Foam 1 Carbon Fiber Spar
Fiberglass/Epoxy skin
April 5, 2019
AAE 451, Aether Aerospace

18. Internal Layout Payload Receiver Servos Battery Motor April 5, 2019
AAE 451, Aether Aerospace

19. Wing-Fuselage Attachment
Wing attachment will be access point for payload bay and batteries
Attach landing gear with same nylon screws which attach leading edge of wing
April 5, 2019
AAE 451, Aether Aerospace

20. Geometric Layout
V-Tail
April 5, 2019
AAE 451, Aether Aerospace

21. V-n Diagram Clmax= 1,5 ; Clmin= -0.3 ; nmax= 10
Maximum dive speed = 1,3*top speed
April 5, 2019
AAE 451, Aether Aerospace

22. Assumptions Maximum load factor: 10
Rectangular airfoil simplification for inertia calculations
Payload shape
Flaperon/ Ruddervator weight estimate
10 in. propeller
Weights for:
Servos
Battery
Motor
Receiver
April 5, 2019
AAE 451, Aether Aerospace

23. CDR: Aether Angry Mosquito
Mission Overview
Aerodynamics
Structures and Weights
Propulsion System
Dynamics & Controls
Cost Analysis & Remaining Work
April 5, 2019
AAE 451, Aether Aerospace

24. Propulsion System – Motor Selection
Large database of motors and batteries was created
Excel spreadsheet calculates motor output torque and power
Check for compatibility in operating ranges
Example Output (with our chosen battery):
Not Compatible!
Motor
Kv (RPM/V)
Kt (in*oz/amp)
R (ohm)
Io (amp)
Imax (A)
V motor
RPM
T (in*oz)
Pout (hp)
Price
Ammo Kv
2600
0.520
0.04
3.9 55
34112
19.8
0.67
$79.99
Ammo Kv
1800
0.751
1.9 50
23616
30.1
0.71
Ammo Kv
1200
1.127
1.2 40
15744
46.0 NC
Ammo Kv
3300
0.410
4.4 45
43296
15.4
0.66
Ammo Kv
2300
0.588 2 60
30176
23.5
0.70
Ammo Kv
3900
0.347
4.5 32
51168
13.0
$69.99
Ammo Kv
2900
0.466
2.7
38048
18.3
0.69
April 5, 2019
AAE 451, Aether Aerospace

25. Battery selection
Must match current and voltage to motor operating range
Must have enough capacity for mission endurances
Motor and battery must leave enough room in propulsion system budget
Battery
mAh
Cells per pack
Volts
Current
Amps
Weight (lbs)
Total Energy (J)
Total Cost
Energy Density
(J/lb)
Cost J/$
PQ18004
1800 4
14.8 36
0.425
383616
$83.90
902626
4,572.30
PQ21004
2100 42
0.494
447552
$87.90
906434
5,091.60
PQ40003
4000 3
11.1 64
0.594
479520
$91.90
807613
5,217.85
PQ40004
0.769
852480
$119.90
7,109.92
PQ44003
4400 70
0.669
527472
$103.90
788743
5,076.73
PQ44004
0.875
937728
$135.90
6,900.13
April 5, 2019
AAE 451, Aether Aerospace

26. Propulsion System – Battery and Motor
Poly-Quest LiPo PQ21004
Capacity =2100 mAh
Cells = 4 cells
Voltage = 14.8 V
Current = 42 Amps
Weight = lbs
Cost = $87.90
Great Planes Electrifly Ammo Kv
Kv = 2900 RPM/V
Kt = in*oz/amp
R = 0.04 ohm (est.)
No load current Io = 2.7 Amp
Continous Max Current I = 45 Amp
Voltage Range V
Pmax = watts
Weight = 6.5 oz (185 g)
Suggested Prop Size: 10x7E-14x7E
Cost = $69.99
April 5, 2019
AAE 451, Aether Aerospace

27. Propulsion System - Propeller and Gearbox Selection
Prop selection – utilized Main_System_Design.m for many different P/D ratios and diameters, using gear ratio for max eff.
Tabulated data and compared top speeds:
Gear ratio given for maximum efficiency is not necessarily the gearbox for maximum speed
Chose 10x7 propeller (also recommended by the motor manufacturer)
tau = 0.7
Vel (ft/s)
Dia (in)
Gear Ratio
(max eff.)
Preq (hp)
Volt
Amp
End (min)
100 10
2.8
0.32
11.5
25.1
1.6
110
3.1
0.43
13.7
27.4
1.24
120
3.3
0.55
16.1
28.5
1.1
April 5, 2019
AAE 451, Aether Aerospace

28. Propulsion System – Speed Controller, Gear Drive, and Propeller
APC 10x7E Propeller
Thin for Electric Motors
Weight = lbs
Cost = $2.93
Castle Creations Phoenix-80
Continuous Amperage – 80 Amps
Resistance = ohms
Weight = 2.1 oz
Battery Eliminator Circuit (BEC)
Cost = $159.99
GP Gear Drive for 36 mm Motors (2.8:1)
Includes Prop Adapter
Many gear ratios available
Cost = $21.99
April 5, 2019
AAE 451, Aether Aerospace

29. Propulsion System Cost
Component
Product Name
Weight (lbs)
Price
Battery
Poly-Quest LiPo PQ21004
0.494
$87.90
Motor
GP Electrifly Ammo Kv
0.406
$69.99
Speed Controller
Castle Creations Phoenix-80
0.131
$159.95
Geardrive
Gear Drive 36mm Motors (2.8:1)
0.125
$21.99
Propeller
APC 10x7E Thin Electric Props
0.035
$2.93
Total (excludes speed controller)
1.192
$182.81
April 5, 2019
AAE 451, Aether Aerospace

30. Propulsion System - Propeller and Gearbox Selection
Manually changed gearbox ratio in Main_System_Design.m to utilize available amperage
Ratio of 2.8:1 yielded highest predicted top speed while not exceeding continuous operating ratings of the motor or battery
Top Speed Operation:
Vmax = ft/s
Motor Input Voltage = 14.8 V
Motor Input Current = 39 Amps
Flat Out Endurance = 1 minute
Propeller RPM = 13,700 RPM
Tip Mach = 0.53
Endurance Operation:
Speed for Minimum
Power Required = 31 ft/s
Speed for Endurance Mission = 35 ft/s
Endurance = 10.7 minutes
April 5, 2019
AAE 451, Aether Aerospace

31. CDR: Aether Angry Mosquito
Mission Overview
Aerodynamics
Structures and Weights
Propulsion System
Dynamics & Controls
Cost Analysis & Remaining Work
April 5, 2019
AAE 451, Aether Aerospace

32. D&C Overview Tail Sizing Control Surface Sizing Trim Considerations
Feedback System
Dynamic Simulation
April 5, 2019
AAE 451, Aether Aerospace

33. Tail Sizing - Class II Tail sized based on stability consideration
Longitudinal Stability
Plot of CG and AC as a function of tail area
Static Margin ≥ 0.15
Lateral Stability
Plot of weathercock stability derivative vs. tail area
Desire stability derivative
Stroke the Goose
April 5, 2019
AAE 451, Aether Aerospace

34. X - Plots SM=0.15 Class I Class II Sh (ft2) 0.82 0.7 Sv (ft2) 0.22
0.39
April 5, 2019
AAE 451, Aether Aerospace

35. V-tail considerations / Sizing of control Surfaces
Sized for conventional tail
Converted from conventional to V
Total tail surface area is the same as conventional tail with dihedral shown below
Class I
Class II Sa
0.26 Se
0.34
0.29 Sr
0.079
0.14
April 5, 2019
AAE 451, Aether Aerospace

36. Trimability
Trim Diagram
April 5, 2019
AAE 451, Aether Aerospace

37. Closed Loop Feedback - Root Locus
Feedback Gain of -0.14
A final Dutch-Roll dampening of 0.81
April 5, 2019
AAE 451, Aether Aerospace

38. Dynamic Simulation Use Flat Earth to create a transfer function
April 5, 2019
AAE 451, Aether Aerospace

39. Summary Inherently stable in all directions
Dutch-Roll dampening: 0.12 to 0.8
Mode
Pole Location
Damping
Frequency
Time Constant
Short Period i
0.826
17.7
Phugoid i
0.249
0.272
Roll
-6.91 1
6.91
0.14
Spiral
0.0956 -1
10.46
Dutch Roll i
0.12
5.07
Dutch Roll (feedback) i
0.81
5.7
April 5, 2019
AAE 451, Aether Aerospace

40. CDR: Aether Angry Mosquito
Mission Overview
Aerodynamics
Structures and Weights
Propulsion System
Dynamics & Controls
Cost Analysis & Remaining Work
April 5, 2019
AAE 451, Aether Aerospace

41. Economic Plan – Parts and Materials
April 5, 2019
AAE 451, Aether Aerospace

42. Remaining Work - Prototype Fabrication Schedule
Week 1
Oct. 30 – Nov. 5
Week 2
Nov. 5 – Nov. 12
Week 3
Nov. 13 – Nov. 16
Component collection and testing – propulsion system and electronic parts, etc.
Build foam fuselage using CNC, sand and finish
Build foam wing and v-tail using the hotwire, sand and finish
Fiberglass the fuselage shell and remove some of the foam
Cut out space in the fuselage for the wings and re-fiberglass
Affix the tail spars to the fuselage and the rear gear system
Insert the structural rods into the wing
Create the wing control surfaces
Create the tail control surfaces
Assemble the wings, landing gear, fuselage and tail
Insert the propulsion system
Assemble the wiring system
April 5, 2019
AAE 451, Aether Aerospace

43. Remaining Work - Flight Test Plan
Flight tests will begin Thursday, Nov. 16
All tests will be performed outside
Flight #
Objective
Static Ground Tests and High Speed Taxi 1
Takeoff & Climb, Landing or Durability 2
Takeoff & Climb, Unpowered Glide 3
Maneuverability and Control 4
Turning and Loiter, Endurance 5
Straight Line High Speed 6
Straight Line High Speed Optimization
April 5, 2019
AAE 451, Aether Aerospace

44. Conclusion Meets all DR&O requirements
Competitive top speed of 126 ft/sec
Stylish design for maximum marketability
April 5, 2019
AAE 451, Aether Aerospace

45. Questions?
April 5, 2019
AAE 451, Aether Aerospace

46. Appendix
The Angry Mosquito
April 5, 2019
AAE 451, Aether Aerospace

47. Wing/Tail Geometry Equations
Span
Root chord
Tip chord
TE sweep
c/4 sweep
April 5, 2019
AAE 451, Aether Aerospace

48. Tail Geometry Design Process
Calculate required tail areas
Tail size coefficients for proper control size
cHT = 0.5
cVT = 0.04
SVT = ft2
SHT = 0.49 ft2
April 5, 2019
AAE 451, Aether Aerospace

49. Aircraft 3-D Lift Curve Cla = 5.6936 (2-D) Clo = 0.293 (2-D)
From wind tunnel data & XFOIL
Clo = (2-D)
From wind tunnel data & XFOIL
Raymer “90% est”
2-D to 3-D
CLo = 0.9 Clo
CLo = (3-D)
CLa = (3-D)
April 5, 2019
AAE 451, Aether Aerospace

50. Flap Sizing At Vstall=30ft/sec, the necessary cL=1.6
cL requirement not met without flaps
Flapperons will be employed to satisfy stall constraint
A wing area of 2.5 ft2 is needed in front of flaps
A hinge point at .78c is optimal for airfoil
April 5, 2019
AAE 451, Aether Aerospace