Airplane with configuration changing in flight

Patent metadata

Field	Value
Publication number	US-11084567-B2
Application number	US-201816209353-A
Country	US
Kind code	B2
Filing date	Dec 4, 2018
Priority date	Dec 6, 2017
Publication date	Aug 10, 2021
Grant date	Aug 10, 2021

Abstract

An airplane comprising a fuselage, two wings, a rear tail unit comprising a horizontal tail provided with two tail ends, and at least two engines arranged on the fuselage on either side of a vertical plane of symmetry of the airplane, the airplane having a longitudinal axis, the engines being mounted so as to be able to be displaced, at least in flight, on the fuselage, substantially parallel to the longitudinal axis, and the tail ends being mounted so as to be able to be pivoted, at least in flight, relative to the horizontal tail, the airplane thus having a configuration that changes in flight.

First claim

The invention claimed is:

1. An airplane comprising:
a fuselage having a longitudinal axis,
two wings,
a rear tail unit comprising a horizontal tail provided with two tail ends, and
at least two engines arranged on the fuselage on either side of a vertical plane of symmetry of the airplane,
said engines are displaceably mounted, at least in flight, on said fuselage, substantially parallel to the longitudinal axis, and
said tail ends are pivotably mounted, at least in flight, relative to said horizontal tail,
wherein said engines are displaceable into a forward position, and said two tail ends are pivotable to a folded position in which said two tail ends are arranged substantially orthogonally to a plane formed by the horizontal tail, and
wherein said engines are displaceable into an aft position towards a rear of the airplane relative to said forward position, and said two tail ends are pivotable into a deployed position in which said two tail ends are arranged substantially in the plane formed by said horizontal tail.

2. The airplane according to claim 1 , said airplane further having a center of gravity and a center of lift, and comprising at least one controllable displacement mechanism configured to bring each of said engines, at least in flight, alternately into one or another of two stable positions on the fuselage:
the forward position, in which the center of gravity of the airplane is situated towards the front of the airplane relative to the center of lift; and
the aft position, positioned towards the rear of the airplane relative to said forward position and in which the center of gravity of the airplane is situated towards the rear of the airplane relative to the center of lift.

3. The airplane according to claim 1 , further comprising at least one controllable pivoting mechanism configured to bring each of the two tail ends, at least in flight, alternately into one or another of two stable positions:
the folded position, in which the two tail ends are arranged substantially orthogonally to the plane formed by said horizontal tail so as to form a vertical tail; and
the deployed position, in which the two tail ends are arranged substantially in the plane formed by said horizontal tail so as to form, with the horizontal tail, an augmented horizontal tail surface.

4. The airplane according to claim 2 , wherein the displacement mechanism comprises a sliding system.

5. The airplane according to claim 2 , wherein the displacement mechanism comprises an articulation system.

6. The airplane according to claim 1 , further comprising mobile control surfaces configured to act on a yaw of the airplane.

7. The airplane according to claim 1 , wherein the engines are jet engines or turboprop engines.

8. The airplane according to claim 1 , wherein said engines are propfan or open rotor engines.

9. A method for modifying a configuration of an airplane in flight, said airplane comprising a fuselage, two wings, a rear tail unit comprising a horizontal tail provided with two tail ends, and at least two engines arranged on the fuselage on either side of a vertical plane of symmetry of the airplane, said engines are displaceably mounted on said fuselage, substantially parallel to a longitudinal axis of the airplane, and said tail ends are pivotably mounted relative to said horizontal tail, the method comprising:
a first step comprising bringing said engines into a forward position and in bringing said tail ends into a folded position in which said tail ends are arranged substantially orthogonally to a plane formed by said horizontal tail; and
a second step comprising bringing said engines into an aft position, displaced towards the rear of the airplane relative to said forward position and in bringing said tail ends into a deployed position in which said tail ends are arranged substantially in the plane formed by said horizontal tail,
said first and second steps are implemented alternately at least during a flight of the airplane.

10. The method according to claim 9 , wherein said first step is implemented, at least, during at least one of a take-off phase of the airplane or during a landing phase of the airplane, and wherein said second step is implemented, at least, during a cruising flight phase of the airplane.

Assignees

• Airbus Operations Sas

Inventors

• Farouz-Fouquet Mathias

Classifications

• B64D27/02

  Aircraft characterised by the type or position of power plants · CPC title

• B64C3/48 Primary

  by relatively-movable parts of wing structures · CPC title

• B64C5/12 Primary

  for retraction against or within fuselage or nacelle · CPC title

• B64C39/008

  about a longitudinal axis · CPC title