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|FLYING CARS}byShashishekarayya.R.Hiremath 1MJ09MAE12 M.Tech. 2nd semester Dept. Aeronautical Engg., MVJCE-Bangalore
OVERVIEWIntroduction Design Approach Design Consideration Design Concepts Conclusion
INTRODUCTION What is a Flying car ?
Why do we need flying Car ?
What is special in designing a flying car ?
DESIGN APPROACH Roadable Aircraft
CONTINUEDu. Dual Mode Design
DESIGN CONSIDERATIONS Range Endurance Rate of climb Cruise speed in air Cruise speed in land Airworthiness standards Automobile safety and Emissions
CONTINUEDu. Acceptable in flight wing aerodynamics while able to
retract , fold or detached and stow the wing for road travel. Need to rotate on take off. To find engine/transmission which could meet the conflicting demand of ground and air. Dual mode control systems. Stability and performance requirements in both modes of travel.
DESIGN CONCEPTS Glenn Curtiss in 1917 exhibited his design of flying
automobile in Pan- American Aeronautic exposition in New York.
Waldo waterman was the first person to be granted a
patent on roadable aircraft Arrowbile in 1937.
CONTINUEDu.. Robert E. Fulton in 1946 designed a new concept his
Convair Air car in 1947
CONTINUEDu. Moulton Taylor designed and built Taylor Aerocar in
Characteristics of Aerocar
Crew: One pilot Capacity: One Passenger (2 total) Length: 6.55 m Wingspan: 10.36m Height: 2.18 m Wing area: 15.6 m Empty: 590 kg Loaded: 955 kg Power plant: 1x Lycoming O-290, 135 hp (100 kW)
Performance of Aerocar Maximum speed: 112 mph (172 km/h) Range: 300 mi (480 km) Service ceiling: 12,000 ft (3,658 m) Rate of climb: 550 ft/min (168 m/min) Wing loading: 12.5 lb/ft (61 kg/m) Power/Mass: 0.06 hp/lb (100 W/kg)
Moller sky car a VTOL prototype invented by Paul
General characteristicsy Capacity: Four passengers y Length: 19.5 ft (5.9 m) y Wingspan: 8.5 ft (2.6 m) y Height: 7.5 ft (2.3 m) y Empty weight: 2,400 lbs (1088 kg) y Useful load: 750 lbs (340 kg) y Power plant: 4 'Rotapower' Wankel engines with ducted fans, 180 hp (134
y y y
Performance Maximum speed: 330 mph (531 km/h) at 25,000 ft (7620 m) Cruise speed: 305 mph (491 km/h) at 25,000 ft (7620 m) Service ceiling: 36,000 ft (10973 m) y Rate of climb: 4,800 ft/min (1463 m/min)
Terrafugia-TransitionThe Transition is a light sport, roadable aircraft under development by Terrafugia, a small start-up company based in Woburn, Massachusetts
General characteristicsy Crew: 1 pilot y Capacity: 2, pilot and passenger y Payload: 430 lb (200 kg) y Length: 19 ft 2 in (5.8 m) y Wingspan: 27 ft 6 in (8.4 m) y Height: 6 ft 3 in (1.9 m) y Empty weight: 890 lb (400 kg) y Useful load: 430 lb (200 kg) y Max takeoff weight: 1,320 lb (600 kg) y Power plant: 1 Rotax 912S, 100 hp (75 kW) @ 5800 rpm (max. 5 minutes), 95 hp
(71 kW) @ 5500 rpm (continuous)
yy y y y y y
Propellers: Prince Aircraft Company, four-bladed "P-Tip" propeller, 1 per engine Cockpit width: 51 in (1.3 m) at the shoulder Fuel capacity: 20 US gal (76 L; 17 imp gal) Length on road: 18 ft 9 in (5.7 m) with elevator up Width on road: 80 in (2.0 m) with wings folded Height on road: 6 ft 9 in (2.1 m) Front wheel drive on road
Continued .. Performancey Cruise speed: 100 kts (115 mph or 185 km/h) y Stall speed: 45 kts (51 mph or 82 km/h) y Range: In flight 400 nmi (460 mi; 740 km); on road 600 mi (520 nmi;
970 km) y Maximum speed on road: 65 mph (105 km/h) y Fuel economy in cruise flight: 5 US gal (19 L) per hour y Fuel economy on road: 30 mpg (7.8 L/100 km; 36 mpg)
Avionics Glass panel; the proof-of-concept airplane includes: y Dynon Avionics EFIS-D100 Electronic Flight Information System with HS34 Nav and GPS Connectivity y Dynon Avionics EMS-D120 Engine Monitoring System y Garmin SL30 Nav/comm transceiver y Garmin GTX 327 digital transponder y Garmin GPSMAP 496 portable GPS.
CONCLUSION The flying car concepts will require some more time to be
in reality. Roadable aircrafts design and development are feasible. Cost of roadable aircrafts play a vital role in their success. The success of roadable aircrafts will end uncertain
weather, rising costs, and ground transportation hassles on each end of the flight.