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Pardalote Design for High Efficiency Flight Missions

Explore the design, performance, and mission requirements of the Pardalote aircraft, optimized for maximum efficiency and range in Australian conditions. Propulsion, aerodynamics, fuel system, and more detailed for advanced aeronautics.

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Pardalote Design for High Efficiency Flight Missions

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  1. Pardalote “Small, light and all Australian. From the Greek word ‘spotted’.” tb Aeronautics Andrew Kilazoglou Chief Design Officer

  2. TBA Team • Tony Denham • Carl Fester • Sarah FitzGerald • Derrick Ho • Jeremy Sequeira • Nick Thompson • Chak Yu

  3. Mission Requirements

  4. Pardalote

  5. Pardalote Design

  6. Internal Layout

  7. Weight

  8. Performance

  9. Performance • Normal Mission • Take Off Weight= 660kg (MTOW); 90kg Pilot, 90kg Observer, 50kg payload, Full Fuel. • Range Covered= 251.53 km, Elapsed Time= 2.19hrs • Fuel Consumed= 46.23kg

  10. Propulsion • Jabiru 2200 H/O 4 Cylinder • 80 HP @ 3300 RPM • 59 kg • Clockwise Rotation • Maximum Torque 210 Nm @ 2500 RPM

  11. Custom Fixed Pitch Propeller • 1.2 m diameter • Laminated Wood Construction • 8.5 kg (over estimated) • Blade Twist: 70°-26° (Root to Tip) • Pitch: 0° • Ideal Max Operating Speed imposed: 2700 RPM • Aerofoil Section: Clark Y

  12. Idealisation and Criteria • Idealised for Cruise Conditions: • Reach Search Area faster and with less fuel • Loiter flight is still relatively fuel efficient • Enables more fuel for loiter and or better range

  13. Critical Conditions • Mt Hotham Aerodrome at 4260ft • Loiter Observation Flight at 1500ft AGL

  14. Drag Estimates

  15. Propeller Results

  16. Best Range Condition • Best range speed • Low RPM: 13L/hr • T ≈ D (ideal for cruise) • Qprop< Qengine • Operates at near ideal J • High efficiency • Idealised successfully

  17. Flight Conditions • Cruise flight = high efficiency • Takeoff/Climb conditions have high excess thrust • Flight possible at high altitude (Mt Hotham) • Powered descent (hence glide descent) possible • Sufficient loiter excess thrust = manoeuvring possible • Highest RPM = 2700 RPM (15L/hr)

  18. Engine Torque and Required Propeller Torque Comparison

  19. Fuel System • AVGAS100/130LL (ρ = 0.7) or MOGAS (ρ =0.73) • Fuel: 74 kg (104 L) in 0.10404 m3 • Fuel to be stored within the central wing cavity, above and aft of the cockpit, forward of the engine

  20. Fuel Cell • 0.17 x 0.7 x 0.848 m • 2.5mm nitrile rubber fuel cell • Autoclave cured seams for durability and strength • Externally reinforced nitrile rubber nipples • Aluminium retaining shell 0.201 x 0.76 x 0.95 m

  21. Fuel tank • Fuel sump 0.25% of fuel cell volume • Drainage nozzle • Fuel engine line

  22. Fuel Inlet • 0.05 m diameter • Also acts as ventilation shaft

  23. Engine Feed • Mechanical fuel pump • Fuel intake nozzle fitted with a weighted flop tube

  24. Fuel System Layout

  25. THE MODEL

  26. Any Questions?

  27. Extra Mission • High Altitude, payload drop • Take Off Weight= 660kg MTOW; 90kg Pilot, 90kg Observer, 100kg payload, Full Fuel. • Range Covered= 519.34 km, Elapsed Time= 3.96hrs

  28. Folding Wing

  29. Mission Contours • Specific Excess Power

  30. Mission Contours • Range

  31. Mission Contours • Endurance

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