CONVERTIBLE AIRCRAFT PROVIDED WITH TWO DUCTED ROTORS AT THE WING TIPS AND WITH A HORIZONTAL FAN IN THE FUSELAGE

• US 20150314865A1
• Filed: 12/09/2013
• Published: 11/05/2015
• Est. Priority Date: 12/10/2012
• Status: Abandoned Application

• Current Assignee: Gerome Bermond
• Original Assignee: Gerome Bermond
• Inventors: BERMOND, Grome, VANDAME, Etienne
• Application Number:
  US14/650,231
• Publication Number:
  US 20150314865A1
• Time in Patent Office: Days
• US Class Current: 1/1
• CPC Class Codes: B64C 2027/8254 Shrouded tail rotors, e.g. "Fenestron" fans
• CPC Class Codes: B64C 2027/8272 comprising fins, or movable rudders
• CPC Class Codes: B64C 2027/8281 comprising horizontal tail planes
• CPC Class Codes: B64C 27/22 Compound rotorcraft, i.e. aircraft using in flight the features of both aeroplane and rotorcraft
• CPC Class Codes: B64C 27/28 with forward-propulsion propellers pivotable to act as lifting rotors
• CPC Class Codes: B64C 27/52 Tilting of rotor bodily relative to fuselage of see-saw type construction B64C27/43
• CPC Class Codes: B64C 27/82 characterised by the provision of an auxiliary rotor or fluid-jet device for counter-balancing lifting rotor torque or changing direction of rotorcraft
• CPC Class Codes: B64C 29/0033 the propellers being tiltable relative to the fuselage
• CPC Class Codes: B64D 27/02 Aircraft characterised by the type or position of power plants fuselages specially adapted for mounting power plants B64C1/16; wings specially adapted for power plants B64C3/32

Abstract

The invention relates to a convertible aircraft comprising a fuselage (F), a pair of wings (A1, A2) arranged one on each side of the fuselage (F), at least one ducted rotor (1) installed in a horizontal position at one of the ends of the fuselage (F) and a first and a second nacelle (N1, N2) arranged respectively at the tip of each wing (A1, A2) and each comprising a ducted rotor (R1, R2) and being pivotably mounted relative to the fuselage (F). The nacelles comprise at least a first and a second movable flap (V1, V2), which flaps are arranged respectively at the outlet of the ducted rotor (R1) of the first nacelle (N1) and at the outlet of the ducted rotor (R2) of the second nacelle (N2). The aircraft according to the invention thus represents an advantageous solution to any applications involving helicopters and airplanes, particularly emergency preparedness missions, rescue missions, and public or private transport.

Claims

1. A convertible aircraft comprising a fuselage, and a pair of wings on each side of the fuselage, and a first and a second nacelles respectively located at each wingtip, each comprising a ducted rotor, and pivotally mounted with respect to the fuselage in that it comprises a first and a second movable flap respectively located at the outlet of the ducted rotor of the first nacelle and at the outlet of the ducted rotor of the second nacelle characterized in that it comprises a at ducted rotor installed in horizontal position at any end of the fuselage, and includes a at Vast one combustion engine installed in the fuselage, which is air supplied through the top of the fuselage by means of a first opening, and whose exhaust gas are ejected on top of the fuselage through a second opening.

2. A convertible aircraft in accordance with claim 1, wherein the said wings are in upper position.

3. A convertible aircraft in accordance with claim 1, including two canard wings located on each side of the fuselage.

4. A convertible aircraft in accordance with claim 1, including an empennage provided with a stabilizer and a vertical fin, equipped with an elevator and a rudder.

5. A convertible aircraft in accordance with claim 1, wherein a combustion engine drives, through a mechanical transmission, the rotors located in the nacelles.

6. A convertible aircraft in accordance with claim 1, wherein each nacelle comprises a housing, which accommodates a power bevel gearbox as well as means to vary the pitch of each rotor.

7. A convertible aircraft in accordance with claim 6, wherein an electric generator is coupled with a combustion engine and an electricity storage system, and has means to supply electricity to the electric motors integrated in the housings.

8. A convertible aircraft in accordance with claim 1, wherein each flap extends over substantially the entire inner section of the nacelle where it is installed.