CDR Aether Angry Mosquito AAE 451 Team 3

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

Presentation Outline n n n Mission Overview & Initial Sizing Aerodynamics Structures and Weights Propulsion System Dynamics & Controls Cost Analysis & Remaining Work 03 March 2021 AAE 451, Aether Aerospace 2

Design Mission Overview n n n n n 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 03 March 2021 AAE 451, Aether Aerospace 3

Aircraft Concept n n Low wing V-tail Tail dragger, fixed racing gear Streamlined fuselage 11 in 3. 5 ft 4 ft 03 March 2021 AAE 451, Aether Aerospace 4

CDR: Aether Angry Mosquito n n n Mission Overview Aerodynamics Structures and Weights Propulsion System Dynamics & Controls Cost Analysis 03 March 2021 AAE 451, Aether Aerospace 5

Wing Airfoil Section – MH 32 ¡ ¡ Used on electric powered pylon racers Designed for low Re 03 March 2021 AAE 451, Aether Aerospace 6

Aspect Ratio Trade Study n Results ¡ n ARdesign = 5 Solution ¡ ¡ ¡ n ARopt < 2 ARdesign = 5 for D&C CDmin = 0. 0159 (Cf = 0. 0049) ARopt < 2 Other Trends: ¡ ¡ ARopt Inversely proportional to Vmax ARopt Directly proportional to Wo 03 March 2021 AAE 451, Aether Aerospace 7

Wing and Tail Geometry Quarter chord line Leading Edge Wing V-Tail Airfoil MH 32 NACA 0009 Area 3. 25 ft 2 1. 1 ft 2 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 - 03 March 2021 . 5 ft 1. 11 ft 2. 02 ft Quarter chord line Lead ing E dge 0. 80 ft 0. 36 ft 0. 94 ft AAE 451, Aether Aerospace 8

Fuselage Length Sizing n Goals: ¡ ¡ n Minimize Weight Minimize Drag Considerations: ¡ ¡ Minimum build-able fuselage length Class 1 tail sizing 03 March 2021 AAE 451, Aether Aerospace 9

Drag Build-Up Analysis Total CDo = 0. 0356 03 March 2021 AAE 451, Aether Aerospace 10

Aircraft Drag Polar 03 March 2021 AAE 451, Aether Aerospace 11

Lift Coefficient Curve *a in radians n 03 March 2021 AAE 451, Aether Aerospace 3 -D coefficients converted from 2 -D experimental data 12

CDR: Aether Angry Mosquito n n n Mission Overview Aerodynamics Structures and Weights Propulsion System Dynamics & Controls Cost Analysis & Remaining Work 03 March 2021 AAE 451, Aether Aerospace 13

Structures and Weights 03 March 2021 AAE 451, Aether Aerospace 14

Weight and Balance n n n 03 March 2021 AAE 451, Aether Aerospace Overall weight: 5. 5 lbs CG : 0. 965 ft from nose Moments/Products of Inertia 15

Weight and position of the main parts 03 March 2021 AAE 451, Aether Aerospace 16

Wing Structure n n n Polyurethane Foam 1 Carbon Fiber Spar Fiberglass/Epoxy skin 03 March 2021 AAE 451, Aether Aerospace 17

Internal Layout Payload Receiver Servos Battery Motor 03 March 2021 AAE 451, Aether Aerospace 18

Wing-Fuselage Attachment n n 03 March 2021 AAE 451, Aether Aerospace Wing attachment will be access point for payload bay and batteries Attach landing gear with same nylon screws which attach leading edge of wing 19

Geometric Layout n V-Tail 03 March 2021 AAE 451, Aether Aerospace 20

V-n Diagram n n Clmax= 1, 5 ; Clmin= -0. 3 ; nmax= 10 Maximum dive speed = 1, 3*top speed 03 March 2021 AAE 451, Aether Aerospace 21

Assumptions n n Maximum load factor: 10 Rectangular airfoil simplification for inertia calculations n n Payload shape Flaperon/ Ruddervator weight estimate 10 in. propeller Weights for: ¡ ¡ 03 March 2021 AAE 451, Aether Aerospace Servos Battery Motor Receiver 22

CDR: Aether Angry Mosquito n n n Mission Overview Aerodynamics Structures and Weights Propulsion System Dynamics & Controls Cost Analysis & Remaining Work 03 March 2021 AAE 451, Aether Aerospace 23

Propulsion System – Motor Selection n Large database of motors and batteries was created Excel spreadsheet calculates motor output torque and power Check for compatibility in operating ranges Not Compatible! Example Output (with our chosen battery): Motor Kv Kt R Io Imax (RPM/V) (in*oz/amp) (ohm) (amp) (A) V motor RPM T Pout (in*oz) (hp) Price Ammo 36 -56 -2600 Kv 2600 0. 520 0. 04 3. 9 55 11. 1 -14. 8 34112 19. 8 0. 67 $79. 99 Ammo 36 -56 -1800 Kv 1800 0. 751 0. 04 1. 9 50 14. 8 -22. 2 23616 30. 1 0. 71 $79. 99 Ammo 36 -56 -1200 Kv 1200 1. 127 0. 04 1. 2 40 18. 5 -25. 9 15744 46. 0 NC $79. 99 Ammo 36 -50 -3300 Kv 3300 0. 410 0. 04 4. 4 45 14. 8 -18. 5 43296 15. 4 0. 66 $79. 99 Ammo 36 -50 -2300 Kv 2300 0. 588 0. 04 2 60 14. 8 -18. 5 30176 23. 5 0. 70 $79. 99 Ammo 36 -40 -3900 Kv 3900 0. 347 0. 04 4. 5 32 14. 8 -18. 5 51168 13. 0 NC $69. 99 Ammo 36 -40 -2900 Kv 2900 0. 466 0. 04 2. 7 45 14. 8 -18. 5 38048 18. 3 0. 69 $69. 99 03 March 2021 AAE 451, Aether Aerospace 24

Battery selection n 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 m. Ah Cells per pack Volts Current Amps Weight (lbs) Total Energy (J) Total Cost Energy Density (J/lb) Cost J/$ PQ 18004 1800 4 14. 8 36 0. 425 383616 $83. 90 902626 4, 572. 30 PQ 21004 2100 4 14. 8 42 0. 494 447552 $87. 90 906434 5, 091. 60 PQ 40003 4000 3 11. 1 64 0. 594 479520 $91. 90 807613 5, 217. 85 PQ 40004 4000 4 14. 8 64 0. 769 852480 $119. 90 1108917 7, 109. 92 PQ 44003 4400 3 11. 1 70 0. 669 527472 $103. 90 788743 5, 076. 73 PQ 44004 4400 4 14. 8 70 0. 875 937728 $135. 90 1071689 6, 900. 13 03 March 2021 AAE 451, Aether Aerospace 25

Propulsion System – Battery and Motor n n Poly-Quest Li. Po PQ 21004 ¡ Capacity =2100 m. Ah ¡ Cells = 4 cells ¡ Voltage = 14. 8 V ¡ Current = 42 Amps ¡ Weight = 0. 494 lbs Cost = $87. 90 03 March 2021 n Great Planes Electrifly Ammo 36 -40 -2900 Kv ¡ Kv = 2900 RPM/V ¡ Kt = 0. 466 in*oz/amp ¡ R = 0. 04 ohm (est. ) ¡ No load current Io = 2. 7 Amp ¡ Continous Max Current I = 45 Amp ¡ Voltage Range 14. 8 -18. 5 V ¡ Pmax = 832. 5 watts ¡ Weight = 6. 5 oz (185 g) ¡ Suggested Prop Size: 10 x 7 E-14 x 7 E n Cost = $69. 99 AAE 451, Aether Aerospace 26

Propulsion System - Propeller and Gearbox Selection n n 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: tau = 0. 7 n n 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 10 3. 1 0. 43 13. 7 27. 4 1. 24 120 10 3. 3 0. 55 16. 1 28. 5 1. 1 Gear ratio given for maximum efficiency is not necessarily the gearbox for maximum speed Chose 10 x 7 propeller (also recommended by the motor manufacturer) 03 March 2021 AAE 451, Aether Aerospace 27

Propulsion System – Speed Controller, Gear Drive, and Propeller n n Castle Creations Phoenix-80 ¡ ¡ n ¡ n n Cost = $2. 93 GP Gear Drive for 36 mm Motors (2. 8: 1) ¡ n n 03 March 2021 Thin for Electric Motors Weight = 0. 035 lbs ¡ Continuous Amperage – 80 Amps Resistance = 0. 001 ohms Weight = 2. 1 oz Battery Eliminator Circuit (BEC) Cost = $159. 99 APC 10 x 7 E Propeller Includes Prop Adapter Many gear ratios available Cost = $21. 99 AAE 451, Aether Aerospace 28

Propulsion System Cost Weight (lbs) Component Product Name Battery Poly-Quest Li. Po PQ 21004 0. 494 $87. 90 Motor GP Electrifly Ammo 36 -40 -2900 Kv 0. 406 $69. 99 Speed Controller Castle Creations Phoenix-80 0. 131 $159. 95 Geardrive Gear Drive 36 mm Motors (2. 8: 1) 0. 125 $21. 99 Propeller APC 10 x 7 E Thin Electric Props 0. 035 $2. 93 1. 192 $182. 81 Total (excludes speed controller) 03 March 2021 AAE 451, Aether Aerospace Price 29

Propulsion System - Propeller and Gearbox Selection n n 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 operatings of the motor or battery Top Speed Operation: ¡ Vmax = 131. 3 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 03 March 2021 AAE 451, Aether Aerospace 30

CDR: Aether Angry Mosquito n n n Mission Overview Aerodynamics Structures and Weights Propulsion System Dynamics & Controls Cost Analysis & Remaining Work 03 March 2021 AAE 451, Aether Aerospace 31

D&C Overview n n n Tail Sizing Control Surface Sizing Trim Considerations Feedback System Dynamic Simulation 03 March 2021 AAE 451, Aether Aerospace 32

Tail Sizing - Class II n n Tail sized based on stability consideration Longitudinal Stability ¡ ¡ n Plot of CG and AC as a function of tail area Static Margin ≥ 0. 15 Lateral Stability ¡ ¡ 03 March 2021 Plot of weathercock stability derivative vs. tail area Desire stability derivative AAE 451, Aether Aerospace 33

X - Plots SM=0. 15 Class I 03 March 2021 Class II Sh (ft 2) 0. 82 0. 7 Sv (ft 2) 0. 22 0. 39 AAE 451, Aether Aerospace 34

V-tail considerations / Sizing of control Surfaces n Sized for conventional tail n Converted from conventional to V ¡ Total tail surface area is the same as conventional tail with dihedral shown below Class I 03 March 2021 Class II Sa 0. 26 Se 0. 34 0. 29 Sr 0. 079 0. 14 AAE 451, Aether Aerospace 35

Trimability Trim Diagram 03 March 2021 AAE 451, Aether Aerospace 36

Closed Loop Feedback - Root Locus n Feedback Gain of -0. 14 n A final Dutch. Roll dampening of 0. 81 03 March 2021 AAE 451, Aether Aerospace 37

Dynamic Simulation n Use Flat Earth to create a transfer function 03 March 2021 AAE 451, Aether Aerospace 38

Summary n n Inherently stable in all directions Dutch-Roll dampening: 0. 12 to 0. 8 Pole Damp Freque Time Mode Location ing ncy Constant Short Period -14. 6 + 9. 99 i 0. 826 17. 7 Phugoid -. 0679 + 0. 264 i 0. 249 0. 272 -6. 91 1 6. 91 0. 14 0. 0956 -1 0. 0956 10. 46 Dutch Roll -0. 598 + 5. 03 i 0. 12 5. 07 Dutch Roll (feedback) -4. 62 + 3. 35 i 0. 81 5. 7 Roll Spiral 03 March 2021 AAE 451, Aether Aerospace 39

CDR: Aether Angry Mosquito n n n Mission Overview Aerodynamics Structures and Weights Propulsion System Dynamics & Controls Cost Analysis & Remaining Work 03 March 2021 AAE 451, Aether Aerospace 40

Economic Plan – Parts and Materials 03 March 2021 AAE 451, Aether Aerospace 41

Remaining Work - Prototype Fabrication Schedule Week 1 Component collection and testing – propulsion system and Oct. 30 – Nov. 5 electronic parts, etc. Build foam fuselage using CNC, sand finish Build foam wing and v-tail using the hotwire, sand finish Week 2 Fiberglass the fuselage shell and remove some of the foam Nov. 5 – Nov. 12 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 Week 3 Create the tail control surfaces Nov. 13 – Nov. 16 Assemble the wings, landing gear, fuselage and tail Insert the propulsion system Assemble the wiring system 03 March 2021 AAE 451, Aether Aerospace 42

Remaining Work - Flight Test Plan n n Flight tests will begin Thursday, Nov. 16 All tests will be performed outside Flight # Objective 0 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 03 March 2021 AAE 451, Aether Aerospace 43

Conclusion n Meets all DR&O requirements Competitive top speed of 126 ft/sec Stylish design for maximum marketability 03 March 2021 AAE 451, Aether Aerospace 44

Questions? 03 March 2021 AAE 451, Aether Aerospace 45

Appendix 03 March 2021 AAE 451, Aether Aerospace 46

Wing/Tail Geometry Equations n Span n Root chord n Tip chord n TE sweep n c/4 sweep 03 March 2021 AAE 451, Aether Aerospace 47

Tail Geometry Design Process n Calculate required tail areas n Tail size coefficients for proper control size ¡ ¡ n n c. HT = 0. 5 c. VT = 0. 04 SVT = 0. 285 ft 2 SHT = 0. 49 ft 2 03 March 2021 AAE 451, Aether Aerospace 48

Aircraft 3 -D Lift Curve n n Clo = 0. 293 (2 -D) ¡ n ¡ From wind tunnel data & XFOIL Raymer “ 90% est” ¡ ¡ n From wind tunnel data & XFOIL Cla = 5. 6936 (2 -D) 0 2 -D to 3 -D CLo = 0. 9 Clo CLo = 0. 2632 (3 -D) 03 March 2021 n CLa = 5. 575 (3 -D) AAE 451, Aether Aerospace 49

Flap Sizing n At Vstall=30 ft/sec, the necessary c. L=1. 6 ¡ ¡ c. L requirement not met without flaps Flapperons will be employed to satisfy stall constraint A wing area of 2. 5 ft 2 is needed in front of flaps A hinge point at. 78 c is optimal for airfoil 03 March 2021 AAE 451, Aether Aerospace 50