Aircraft of compact dimensions

• US 20070018037A1
• Filed: 02/14/2006
• Published: 01/25/2007
• Est. Priority Date: 02/15/2005
• Status: Abandoned Application

• Current Assignee: Cefla Societa' Cooperativa
• Original Assignee: Cefla Societa' Cooperativa
• Inventors: Perlo, Pietro, Bollea, Denis
• Application Number:
  US11/353,053
• Publication Number:
  US 20070018037A1
• Time in Patent Office: Days
• US Class Current: 244/45.R
• CPC Class Codes: B64C 29/0041 the lift during taking-off being created by jet motors
• CPC Class Codes: B64C 39/04 having multiple fuselages or tail booms
• CPC Class Codes: B64C 39/06 having disc- or ring-shaped wings
• CPC Class Codes: B64C 39/08 having multiple wings
• CPC Class Codes: B64C 39/12 Canard-type aircraft

Abstract

The aircraft comprises a fuselage, a main wing substantially of disc-like shape positioned above the fuselage, and a secondary wing which intersects the fuselage and is provided with movable control parts. The aircraft further comprises a main propulsion system including an internal combustion engine intended to drive a propeller positioned at the rear of the fuselage and a secondary propulsion system for the propulsion of the aircraft in a direction perpendicular to the ground. The secondary propulsion system includes a matrix of nozzles positioned on the lower surface of the secondary wing and arranged to emit the exhaust gases coming from the main engine in the form of micro-jets. The main propeller propulsion system and the secondary nozzle propulsion system are selectively controllable in such a way that the aircraft is able to perform three different take-off modes, that is to say a first, conventional take-off mode in which only the main propulsion system is used, a second (STOL) take-off mode in which both the main propulsion system and the secondary propulsion system are used, and a third (VTOL) take-off mode in which only the secondary propulsion system is used.

Claims

1. An aircraft of compact dimensions, comprising a fuselage, a main wing substantially of disc-like shape positioned above the fuselage, and a secondary wing which intersects the fuselage and is provided with movable parts for control of the aircraft.

2. An aircraft according to claim 1, further comprising a pair of front horizontal surfaces each comprising a fixed part secured to the front part of the fuselage and a movable part for control of the aircraft.

3. An aircraft according to claim 1, further comprising a pair of rear horizontal surfaces fixed to the rear part of the fuselage (12) and connected to the main wing by means of vertical surfaces having the function of rudders.

4. An aircraft according to claim 1, further comprising a pair of winglets positioned at the ends of the secondary wing.

5. An aircraft according to claim 1, comprising a main propulsion system having a propeller positioned at the rear of the fuselage.

6. An aircraft according to claim 1, comprising a front landing gear and a pair of rear landing gears.

7. An aircraft according to claim 1, in which the profile of the leading edge of the main wing and/or of the secondary wing has, in plan view, at least two discontinuities intended to make the air flow locally more turbulent.

8. An aircraft according to claim 3, in which both the rear horizontal surfaces and the rear vertical surfaces have a symmetrical aerofoil.

9. An aircraft according to claim 3, in which both the rear horizontal surfaces have an angle of attack such as to generate lift.

10. An aircraft according to claim 5, in which the main propulsion system comprises an internal combustion system intended to drive the propeller.

11. An aircraft according to claim 5, in which the propeller is ducted in a rigid housing structure.

12. An aircraft according to claim 10, further comprising a secondary propulsion system for the propulsion of the aircraft in a direction perpendicular to the ground, the said secondary propulsion system including a matrix of nozzles positioned on the lower surface of the secondary wing and arranged to emit the exhaust gases coming from the main engine in the form of micro-jets.

13. An aircraft according to claim 12, in which the secondary propulsion system is arranged to function also as an aircraft attitude stabilisation system during conventional flight.

14. An aircraft according to claim 12, in which the main propeller propulsion system and the secondary nozzle propulsion system are selectively controllable in a manner such that the aircraft is able to perform three different take-off modes, that is to say a first, conventional take-off mode, in which only the main propulsion system is used, a second (STOL) take-off mode, in which both the main propulsion system and the secondary propulsion system are used, and a third (VTOL) take-off mode, in which only the secondary propulsion system is used.

15. An aircraft according to claim 12, in which the secondary propulsion system is arranged to allow the aircraft to hover at a predetermined height.