The document summarizes the design of an electric RC aircraft called Poseidon's Fury. Key features include carrying a 4 liter payload, draining within 30 seconds, lifting around 25 lbs, and having a low rated aircraft cost. The aircraft uses carbon fiber spars and booms, has a tricycle landing gear configuration, and modified Eppler 216 airfoils. Flight testing showed good longitudinal and directional stability. The propulsion system uses 32 NiCad batteries providing over 4 lbs of thrust and a pitch speed of 47 mph, meeting requirements. The aircraft design satisfies competition rules and successfully completed test missions.

1. P oseidon’s F ury Kristina Morace * Jonathan Moore * Ryan Holmes University of Central Florida AIAA Student Design Build Fly Electric Airplane

2. Outline 1. Required and Desired Features 2. General Design Overview 3. Drain and Structural Analysis 4. Aerodynamics and Flight Performance 5. Propulsion System 6. Summary

3. Aircraft Features Required R/C Electric powered 5 lbs max NiCad batteries 4 liters max payload 0.5" max drain orifice Complete 2 missions Pass wing tip tests 4' x 2' x 1' box Desired Carry 4 liters Drain Time ~ 30 sec Lift capacity ~ 25 lb Flight Stability Battery weight ~ 3 lb High pitch speed Low RAC

4. Rated Aircraft Cost RAC = (300*MEW + 1500*REP + 20*MFHR)/1000 where: MEW = Empty Weight REP = Battery Weight MFHR = Component Summation Total Score = Written Report * Flight Score RAC

5. - Wing span = 9.5 ft - Length = 5 ft - Height = 28 in Aircraft Overview

6. Drain System - Custom 4 liter tank - Custom ball valve

7. Main Fuselage - 7 Bulkheads - Inner-wing - 5th bulkhead 5th Bulkhead Inner-wing

8. Landing Gear - Tricycle Configuration - Carbon Fiber - Detachable

9. Twin Booms - Carbon Fiber - Detachable

10. Wing Sections - Secure booms - Bolt to inner wing - Detachable

11. Inverted V-tail - Pins into booms - Detachable

12. Powerplant - Motor - Batteries - Spinner - Propeller

13. Aft Cone - Twists on/off - Access to electronics

15. Drain System

16. Valve Design Good seal Actuate in flight True ½ inch orifice Manufactured using stereolithography Drain Coefficient Between 0.6 - 1.0 Actual ~ 0.8 Drain time = 55 sec

17. Holds 4 liters Baffles Modified Geometry Predicted drain time ~ 32 seconds Actual Drain time ~ 30 seconds 45% reduction! Tank Design

18. Wing Spar 5th Bulkhead

19. Laminate ply 2 layers of carbon fiber 4 attach points Built to support full load ~ 20 lbs Wing Spar

20. Wing Tip Test Symmetric 10 lb load at tip Max stress = 27.9 ksi Spar Analysis Max Stress = 27.9 ksi

21. Landing Gear Analysis Aluminum Gear (661-T6) 3g load Max Von Mises 20.6 ksi FOS = 1.9 Weighs 0.75 lbs Carbon Fiber Gear 3g load Max Tensile Stress 22.2 ksi FOS = 2.0 Weighs 0.43 lbs

22. Aerodynamics and Flight Performance

23. Aerodynamics – Goals Low Reynolds Number (10 5 ) Lift Coefficient > 1.2 Lift to Drag Ratio > 5 Low Camber Low RAC

24. Aerodynamics –Test Verification Predicted Test

25. Aerodynamics – Airfoil Exceeds Needs C L,max = 1.4 ( L / D ) max = 22 Problem Thickness to Chord Ratio Too Small Design: 10.4% Need: 12.5% Eppler 216

26. Aerodynamics – Airfoil Eppler 216 Modified Modified E216

27. Aerodynamics – Airfoil Eppler 216 Modified

28. Aerodynamics – Wing 9.5 ’ 10.5 ” AC = 25% of Chord CG = 25% of Chord

29. Aerodynamics – Empennage Inverted “V” Configuration Pro-verse Yaw Characteristics Aircraft Score Rewards Actual Path Ideal Turn

30. Aerodynamics – Empennage Twin Boom Configuration No Ground Strike Robust and Modular Inverted “V” Configuration Pro-verse Yaw Characteristics Aircraft Score Rewards

31. Aerodynamics – Empennage 28” 7.5” Angle Between Panels = 110 deg.

32. Flight Performance The Difference: Longitudinal Stability

33. Performance – Phugoid Stability Period = 14 minutes Flight Characteristics = Level 2

34. Performance – Short Period Stability Period = 21.5 s Flight Characteristics = Level 1

35. Performance – Stability 1 st Flight resulted in a “5” Poor Roll control from Adverse Yaw Aileron Differential Added Poor Ground Handling Corrected Steering Control Pilot Rating (Cooper-Harper Scale) Remaining Flights are a “1”

36. Performance – Flight Testing

37. Performance – Flight Testing

38. Performance – Flight Testing

39. Propulsion System

40. Nomenclature System Requirements Predicting Outputs Testing System Integration Safety Features Propulsion System

41. Energy Density Nomenclature Sanyo 1700 mA-hr “ A” size Ni-Cad battery Sanyo 2400 mA-hr “ C” size Ni-Cad battery Rated Aircraft Cost (RAC) Rated Engine Power (REP) Manufacturer's Empty Weight (MEW) 3 lb 36 cells 5 lb 32 cells

42. Take-Off Thrust > 4 lbf Speed > 30 mph Distance < 150 ft Steady Level Flight Thrust > 1 lbf Minimize RAC System Requirements

43. ThrustHP Calculator Software Inputs Propeller Diameter Pitch RPM Outputs Pitch Speed Static Thrust Predicting Outputs Diameter Pitch RPM Pitch Speed Static Thrust

44. Testing Schematic Multimeter (Voltage) Multimeter (Current) External Power Source Radio Transmitter Spring Scale Current Divider Speed Controller Stroboscope Battery Pack Cobalt 60 Motor (Geared)

45. Testing Thrust Sled Spring Scale Drawer Glides Motor Mount

46. Test Results Minimum Thrust 32 “C” batteries 36 “A” batteries

47. Test Results 32 “C” batteries Minimum Pitch Speed 36 “A” batteries

48. 33% reduction in MEW and REP First 3 minutes 6 lbf Static Thrust 47 mph Pitch Speed Propulsion Results Summary Meets Design Requirements

49. Propulsion Integration

50. Kill Switches 40 Amp Fuse PCM Receiver Air Scoops Propulsion Safety Features Forward Scoops Nose Compartment Air Flow Motor Battery Pack Bulkheads Aft

51. Satisfies all competition requirements carries 3 lbs of batteries passes loaded wing tip test takes off in 132 ft easily fits into box Contains all desired features carries 4 liter payload drains in 30 seconds minimized RAC Successfully completes loaded and unloaded missions Summary

52. Team Members Michael Denton Craig Daniels Underclassmen Advisor Dr. Eric Petersen Acknowledgements

53. Questions?