Senior capstone design of a PEM fuel cell propulsion trainer aircraft.

1. Aviridis H2 Senior Capstone Design Parks College Spring 2009 Final Presentation Nicholas Reder Paul Gucwa Sean Copenhaver Mathew Janda

3. Mission Statement The Aviridis H 2 ’s mission is to provide an inexpensive means for the general public to pursue flight training. By using an alternate fuel source, the airplane will not rely on the production of oil and gasoline in the modern era of skyrocketing oil prices. The Aviridis H 2 provides a cheap learning platform for anyone to pursue the clouds.

5. Mission Profile V stall = 45 knots Range = 250 NM Take off distance over obstacle <1500 ft V cruise = 90 knots Duration : 120 min flight time, 60 min reserve Rate of Climb = 200 ft/NM (FAR) V lift off = 54 knots

7. Energy Source Tradeoff Specific Power Available Chart Operating Cost Per Hour

8. Cost Tradeoff Study

9. Fuel Cell System Proton Exchange Membrane Fuel Cell - Environmentally Friendly

11. Powerplant Specifications Motor Fuel Cell 9.5 Length (in) 16 Diameter (in) 190 Weight (lbs) 74 Continuous Power (Hp) 133 Max Power (Hp) PowerPhase 100 Designation UQM Technologies Company 180 Weight (lbs) 2.02 Volume (ft^3) 250-380 Voltage Range 136 Max Power (Hp) Stack2001 Designation GM Company

14. Conceptual Design Data 0.060 HP/W 133 HP 2200 Max Gross Weight (lbs) 54 Hydrogen Fuel (lbs) 50 Baggage (lbs) 400 Pilot and Passenger (lbs) 1696 Empty Weight (lbs) 805 Power Plant Weight (lbs) 891 Avg Weight W/Out Powerplant 805 total: 180 Fuel Cell (lbs) 405 Hydrogen Fuel Tank (lbs) 30 Inverter/Controller (lbs) 190 Electric Motor (lbs) Power Plant Weights

15. Constraint Analysis Aviridis H 2

16. Weights & Balance *All individual component’s stations and moments shown in back-up slides Moment (in-lbs) Station (in) Weight (lbs) Summary* 217074 98.67 2200 Takeoff Weight: 7992 148 54 Hydrogen 6000 120 50 Baggage 18000 90 200 Passenger 18000 90 200 Pilot 167082 98.52 1696 Total Empty Weight:

18. Drag Polar

22. Center of Gravity Range Datum Plane 99.1 Aft (in aft of datum) 95.5 Forward (in aft of datum) Center of Gravity Range: l t N.P. L w L T W D T M acw M F acw

23. V-n Diagram Vstall 47 kts V maneuver 96 kts V D 130.5 kts n = 4.4 n = -1.7 Gust Load Factors : 25 fps gust : 2.77 50 fps gust : 2.00

24. Empennage Structural Analysis 2.69E-02 strain_energy -1.51E+03 min_stress_prin (psi) 2.22E+03 max_stress_vm (psi) 3.05E-04 max_disp_z (in) 5.77E-05 max_disp_y (in) 4.30E-05 max_disp_x (in) 3.05E-04 max_disp_mag (in) ProMechanica Output

27. Computer Aided Design Model

28. Wind Tunnel Model

29. Wind Tunnel Data

30. Wind Tunnel Data

31. Wind Tunnel Data

33. Risk Analysis 3 3 Failures Due to Cold Ambient Temperatures 10 5 2 Hydrogen Igniting 9 3 2 Hydrogen Leak into Cabin 8 4 1 Control Surface Failure 7 2 4 Turbulence 6 2 1 Bird Strike 5 2 4 Hard Landing 4 4 2 High Impact to Hydrogen Tank (Wing) 3 3 3 Fuel Cell Failure 2 3 3 External Leak of Hydrogen Tank (Wing) 1 CONSEQUENCE LIKELIHOOD RISK # (1-5) (1-5) RISK CHART

34. Risk Analysis Cont. Consequence 1 2 3 4 5 5 4 3 2 1 Likelihood 4, 6 1, 2, 10 8 3 9 5 7 Likelihood Consequence 1 Not Likely Minimal or no impact 2 Low Likelihood Minor performance shortfall 3 Likely Moderate Performance shortfall 4 Highly Likely Unacceptable, but workarounds Available 5 Near Certainty Unacceptable, no alternatives exist

35. Cost Analysis 21.4 8.3 1.8 1.6 12.7 Price per 100 aircraft (million $) 294400 113000 25000 22000 175000 Unit Price ($) Aviridis H2 SportStar PA-38 C152 DA20

36. Final Comparisons 180 510 310 204 261 Duration (Minutes) 273 700 471 477 547 Range (NM) 90 110 104 107 138 Normal Cruising Speed (kts) 47 45 48 49 45 Stall Speed, Landing (kts) 1885 1020 720 715 1000 Rate of Climb SL (fpm) 1275 660 1462 1200 1360 Landing Distance, 50 ft 672 720 1440 1340 1640 TO Distance over 50 ft Aviridis H2 SportStar PA-38 C152 DA20

38. Questions

41. Back-up Slides Drag Decomposition Summary Data 24 Best L/D, SL 68 Best Glide Airspeed 70 Minimum Drag, SL Velocity (knots) Description

42. Constraint Analysis

43. Mission Breakdown Energy Remaining = 60 min Total Flight Time= 120 min 60 15 Taxi 75 2 Landing 77 7 Approach 84 5 Descent 89 11 Cruise 100 40 Maneuver 140 11 Cruise 151 10 Cruise Climb 161 3 Climb Out 164 1 Takeoff 165 15 Taxi Remaining Energy (min) Time (min) Phase of Flight

44. Similar Aircraft Comparison

45. Electric Motor Selection 1.86 90.00 167 125 8000 300-420 221 PowerPhase 125 UQM Tech 0.71 190.00 134 100 250-400 405 PowerPhase 100 UQM Tech 1.149 87.000 100 75 8000 25-420 240 Powerphase 75 UQM 0.401 202 81 60.39 12000 250-380 158 HydroGen 3 GM 0.544 149 81 60.39 250-380 185-224 HydroGen 1 GM 0.652 132 86 64.12 300 460 300 Symetron P-2 Raser Technologies 0.692 92.5 64 47.72 2000 300 170 Symetron P-50 Raser Technologies Power/Weight (Hp/lbs) Weight (lbs) Hp Power (kW) RPM (max torque) Voltage Max Torque (lbs*ft) Motor Designation Company

46. Fuel Cell Selection 0.244 0.40 113.90 466.4 212 85 280 C902 Ballard 0.119 0.19 201.00 1694 770 150 550-960 B902 Ballard 0.758 1.24 136.68 180.4 82 102 250-380 Stack2001 GM 0.658 1.08 125.96 191.4 87 94 250-380 Stack2000 GM 0.132 0.22 32.16 244.2 111 24 200 Demonstrator Boeing Demonstrator Power/Weight (Hp/lbs) Power/Weight (kW/kg) Power (Hp) Weight (lbs) Weight (kg) Power Rating (kW) Voltage Designation Company