Vertical take-off and/or landing aircraft and method for controlling a flow of a fluid along a fluidic line of a vertical take-off and/or landing aircraft

Patent metadata

Field	Value
Publication number	US-11643201-B2
Application number	US-201917312301-A
Country	US
Kind code	B2
Filing date	Oct 31, 2019
Priority date	Dec 20, 2018
Publication date	May 9, 2023
Grant date	May 9, 2023

Abstract

A vertical take-off and/or landing aircraft comprising: a fuselage having a longitudinal axis; a pair of semi-wings protruding from the fuselage in a transversal direction with respect to the longitudinal axis; a pair of a predetermined breaking areas of the semi-wings defining respective preferred rupture sections at which the respective semi-wings are designed to break, during operation, in a controlled way moving along a preferred collapse trajectory in the event of impact; and at least one fluidic line configured to convey at least one service fluid from and/or towards at least one said semi-wing and crossing at least one of said preferred rupture sections; the aircraft comprises a self-sealing coupling movable between a first configuration in which it enables the flow of said service fluid from and/or towards the semi-wing, and a second configuration in which it prevents the above-mentioned flow and the spilling of the service fluid from the fluidic line; the self-sealing coupling is movable from the first to the second configuration via the movement of the semi-wing along the preferred collapse trajectory.

First claim

The invention claimed is:

1. A vertical take-off and/or landing aircraft ( 1 ) comprising:
a fuselage ( 2 ) having a longitudinal axis (D);
a pair of semi-wings ( 3 ) protruding from said fuselage ( 2 ) in a transversal direction with respect to said longitudinal axis (D);
a pair of predetermined breaking areas ( 11 ) of said semi-wings ( 3 ) defining respective preferred rupture sections ( 12 ) at which the respective semi-wings ( 3 ) are designed to break, in use, in a controlled way moving, in use, along a preferred collapse trajectory in the event of impact; and
at least one fluidic line ( 13 ) configured to convey at least one service fluid from and/or towards at least one said semi-wing ( 3 ) and crossing at least one of said preferred rupture sections ( 12 );
a self-sealing coupling ( 15 ) movable between a first configuration in which it enables the flow of said service fluid from and/or towards said at least one semi-wing ( 3 ), and a second configuration in which it prevents said flow and the spilling of said service fluid from said fluidic line ( 13 );
said self-sealing coupling ( 15 ) being movable from said first configuration to said second configuration through the movement of said semi-wing ( 3 ) along said preferred collapse trajectory; and
a driving device ( 20 ), configured to transmit said movement of said at least one semi-wing ( 3 ) along said preferred collapse trajectory to said self-sealing coupling ( 15 ), so as to control the movement of said self-sealing coupling ( 15 ) from said first configuration to said second configuration.

2. The aircraft according to claim 1 , wherein said driving device ( 20 ) comprises:
a control appendix ( 21 ) fixed to said self-sealing coupling ( 15 ) and movable to cause the movement of said self-sealing coupling ( 15 ) from said first configuration to said second configuration; and
a connection element ( 22 ) operationally interposed between said at least one semi-wing ( 3 ) and said control appendix ( 21 ) and configured to transform said movement of said at least one semi-wing ( 3 ) along said preferred collapse trajectory into the movement of said control appendix ( 21 ).

3. The aircraft according to claim 2 , wherein said movement of said at least one semi-wing ( 3 ) comprises a substantially rotational motion of said at least one semi-wing ( 3 ) about an axis lying on said preferred rupture section ( 12 );
said connection element ( 22 ) being configured to transform said substantially rotational motion of said semi-wing ( 3 ) into a substantially translational motion of said control appendix ( 21 ) to move said self-sealing coupling ( 15 ) from said first configuration to said second configuration.

4. The aircraft according to claim 2 , wherein said connection element ( 22 ) is fixed to said at least one semi-wing ( 3 ) at its first end portion ( 22 a ), and is hinged to said control appendix ( 21 ) at its second end portion ( 22 b ).

5. The aircraft according to claim 2 , wherein said connection element ( 22 ) is a rigid element or a flexible element.

6. The aircraft according to claim 1 , wherein said fluidic line ( 13 ) comprises a first segment ( 14 a ) extending at said semi-wing ( 3 ) and a second segment ( 14 b ) extending at said fuselage ( 2 );
said self-sealing coupling ( 15 ) comprising a valve device ( 16 ) movable between:
an open position, in which it allows said flow of said service fluid between said first segment ( 14 a ) and said second segment ( 14 b ); and
a closed position, in which it prevents said flow of said service fluid between said first segment ( 14 a ) and said second segment ( 14 b );

said valve device ( 16 ) being arranged in said open position when said self-sealing coupling ( 15 ) is in said first configuration, and being arranged in said closed position when said self-sealing coupling ( 15 ) is in said second configuration.

7. The aircraft according to claim 6 , wherein said self-sealing coupling ( 15 ) further comprises a coupling device ( 17 ) configured to fluidly connect said first segment ( 14 a ) to said second segment ( 14 b ) and comprising a first coupling element ( 18 ) carried by said first segment ( 14 a ) and a second coupling element ( 19 ) carried by said second segment ( 14 b );
said coupling device ( 17 ) being movable between:
an operating position, in which said first coupling element ( 18 ) is coupled with said second coupling element ( 19 ); and
a rest position, in which said first coupling element ( 18 ) is decoupled from said second coupling element ( 19 );

said coupling device ( 17 ) being arranged in said operating position when said self-sealing coupling ( 15 ) is in said first configuration, and being arranged in said rest position when said self-sealing coupling ( 15 ) is in said second configuration.

8. The aircraft according to claim 2 , wherein said control appendix ( 21 ) is fixed to one of said first coupling element ( 18 ) and second coupling element ( 19 ) and can be actuated by said connection element ( 22 ) to determine the removal of said one of said first coupling element ( 18 ) and second coupling element ( 19 ) from the other of said first coupling element ( 18 ) and second coupling element ( 19 ) and thus moving said self-sealing coupling ( 15 ) from said first configuration to said second configuration.

9. The aircraft according to claim 1 , wherein each preferred rupture section ( 12 ) is arranged in an intersection area between the related semi-wing ( 3 ) and said fuselage ( 2 );
said semi-wing ( 3 ) being configured to separate from said fuselage ( 2 ) along said preferred rupture section ( 12 ) moving along said preferred collapse trajectory.

10. The aircraft according to claim 1 , wherein said aircraft ( 1 ) is a convertiplane or a helicoplane.

11. A method for controlling a flow of a service fluid inside a fluidic line ( 13 ) of a vertical take-off and/or landing aircraft ( 1 );
said aircraft ( 1 ) comprising:
a fuselage ( 2 ) having a longitudinal axis (D);
a pair of semi-wings ( 3 ) protruding from said fuselage ( 2 ) in a transversal direction with respect to said longitudinal axis (D);
a pair of a predetermined breaking areas ( 11 ) of said semi-wings ( 3 ) defining respective preferred rupture sections ( 12 ) at which the respective semi-wings ( 3 ) are designed to break, in use, in a controlled way moving along a preferred collapse trajectory in the event of impact; and
at least one fluidic line ( 13 ) configured to convey at least one service fluid from and/or towards at least one said semi-wing ( 3 ) and crossing at least one of said preferred rupture sections ( 12 );
wherein the method comprises the steps of:
moving a self-sealing coupling ( 15 ) between a first configuration, in which it enables the flow of said service fluid from and/or towards said at least one semi-wing ( 3 ), and a second configuration, in which it prevents said flow and the spilling of said service fluid from said fluidic line ( 13 ), through said movement of said at least one semi-wing ( 3 ) along said preferred collapse trajectory; and
transmitting said movement of said at least one semi-wing ( 3 ) along said preferred collapse trajectory to said self-sealing coupling ( 15 ) through a driving device ( 20 ).

12. The method according to claim 11 , wherein said driving device ( 20 ) comprises:
a control appendix ( 21 ) fixed to said self-sealing coupling ( 15 ); and
a connection element ( 22 ) operationally interposed between said at least one semi-wing ( 3 ) and said control appendix ( 21 );
wherein the method further comprises the steps of:
translating said control appendix ( 21 ) to cause

Assignees

• Leonardo Spa

Inventors

• Vanni Roberto
• Antoni Andrea

Classifications

• B64C1/26

  Attaching the wing or tail units or stabilising surfaces · CPC title

• B64C29/0033 Primary

  the propellers being tiltable relative to the fuselage · CPC title

• B64C13/40

  using fluid pressure · CPC title

• B64C29/02

  having its flight directional axis vertical when grounded · CPC title

• B64C27/006 Primary

  Safety devices · CPC title