Presentation
- 1. The Conceptual Design of a Two Seater Electrically Powered Aircraft
- 2. The aim of this project is to: ◦ Research and Design a Concept, Two Seat, Electrically Powered Aircraft ◦ Create a Technical Report on all Work Done ◦ Final presentation on the aircraft
- 3. European Commissions FlightPath 2050 ◦ 75% Reduction in CO2 ◦ 90% Reduction in NOx ◦ 60% Reduction in Noise ◦ Emission Free Taxi ◦ Recyclable Aircraft
- 4. Oil Prices up 1250% in 15 Years Jet Fuel up 100% in 7 Years Petrol Prices up 40% in 7 Years
- 5. Airbus E-FAN 2.0 and 4.0 Battery Powered Aircraft 45 min Cruise
- 6. Comparison of Similar Aircraft Cessna 152 Identified as Competitor
- 7. 12 Initial Concepts Generated 1 Chosen to Take Through Design
- 8. First Estimate •MTOW •Wing Area •Drag Estimate •Thrust at Cruise Fuselage Design Wing Design First Layout Sketch Second Estimate •Drag •Thrust Centre of Gravity Analysis Tail Design Second Layout Sketch Third Estimate •Drag •Thrust Landing Gear Design Structural Design Drag and Thrust Analysis Control Surface Design Third Layout Sketch Final Weight and Centre of Gravity Final Performance Analysis Final Stability and Control Analysis Final Specification Fianl Assembly
- 9. Stall Speed Max Speed Take-Off Run Rate of Climb Ceiling 0 0.05 0.1 0.15 0.2 0.25 0 100 200 300 400 500 600 PowerLoading(N/W) Wing Loading (N/m2) Stall Speed Max Speed Take-off Run Rate of Climb Ceiling
- 10. NACA Profile 652-415 0.00000 0.01000 0.02000 0.03000 0.04000 -1 -0.5 0 0.5 1 1.5 Cd Cl -0.200 -0.150 -0.100 -0.050 0.000 -0.5 0 0.5 1 1.5 Cm Cl 0.00 50.00 100.00 150.00 -5.00 0.00 5.00 10.00 15.00 Cl/Cd Alpha (°) -2 0 2 4 -10 0 10 20 30 Cl Alpha (°) Cl FLAPS 60° Cl FLAPS 0°
- 11. 0 0.1 0.2 0.3 0.4 0.5 0.6 0.7 0 0.5 1 1.5 2 2.5 3 3.5 4 4.5 5 CL y/S 3D Wing Lift Distribution Modified Wing Base Wing
- 12. Two seats Side by Side Storage for Baggage Storage for Removable Fuel Source Good Fore and Lateral View High Wing Tricycle Undercarriage Fore Mounted Motor
- 13. Cruise Fuselage Wing Nose Gear Main Gear Horizontal Stabaliser Vertical Stabaliser Take-Off Fuselage Wing Nose Gear Main Gear Horizontal Stabaliser Vertical Stabaliser
- 14. 4000m Altitude 47 Knots 0 500 1000 1500 2000 2500 3000 3500 4000 4500 5000 0 20 40 60 80 100 DragForce(N) Aircraft Speed (knots) Parasitic Drag Induced Drag Total Drag
- 15. Integrity Efficiency Safety
- 16. Fore Mounted Tractor Propeller Battery Powered UHQ PowerPhase Select 145
- 17. 6 Hour Endurance 2500Ah 430VDC 77.492 MJ/kg 30kg Common Form Factor
- 18. Cruise 110 knots Max 121 knots Stall 45 knots Take-Off 54 knots 348m Take-Off Run 127 m/min Rate of Climb 31min to Cruise Altitude 0 50 100 150 200 250 300 350 400 0 5 10 15 Distance(m) Time (s) Two Pilots Full Baggage One Pilot No Baggage
- 19. Stage 1 in All Flight Phases Excellent Flight Characteristics Reduced Workload on Pilot
- 20. Part Modelling Surface Modelling Product Assembly Drafting Rendering
- 23. UH 145-T Cessna 152 110 knot Cruise 107 knot Cruise 121 knot Max 110 knot Max 45 knot Stall 48 knot Stall 20 knot Crosswind 12 knot Crosswind 348m Take-Off Run 408m Take-Off Run 4000m Cruise Altitude 2438.4m Cruise Altitude 6 Hour Cruise Endurance 3.4 Hour Cruise Endurance 127.17 m/min Rate of Climb 218 m/min Rate of Climb
- 24. Concept Development Concept Simluation Testing Model Testing Prototype Creation Prototype Testing and Development Aircraft Certification Aircraft Manufacture Aircraft Sale Further Aircraft Development
- 25. Requires New Battery Technology Energy Density of 38746.25 Wh/kg 6 Hour Cruise