Landing-gear assembly for an aircraft, the landing-gear assembly including a secondary shimmy damper

Patent metadata

Field	Value
Publication number	US-10589848-B2
Application number	US-201615395058-A
Country	US
Kind code	B2
Filing date	Dec 30, 2016
Priority date	Jan 5, 2016
Publication date	Mar 17, 2020
Grant date	Mar 17, 2020

Abstract

A landing-gear assembly ( 1 ) for an aircraft, the landing-gear assembly comprising:
an axle shaft ( 2 ); a leg ( 3 ) presenting a first portion ( 3 a ) carrying said axle shaft ( 2 ) and a second portion ( 3 b ) connected to a carrier structure of the aircraft; a main damper ( 5 ); and a first secondary damper ( 6 a ) distinct from the main damper ( 5 ).

The first secondary damper ( 6 a ) is carried by the axle shaft ( 2 ) and comprises:
an inertial mass (M); and connection means ( 7 a ) between the inertial mass (M) and the axle shaft ( 2 ) damping movements of the inertial mass (M) along a first axis (X 1 ) of movement of the inertial mass (M) relative to the axle shaft ( 2 ), said first axis of movement (X 1 ) extending in a plane (P) perpendicular to said steering axis (Z).

First claim

The invention claimed is:

1. A landing-gear assembly ( 1 ) for an aircraft, the landing-gear assembly comprising:
an axle shaft ( 2 ) arranged to carry wheels for enabling the aircraft to run on the ground;
a leg ( 3 ) presenting a first portion ( 3 a ) carrying said axle shaft ( 2 ) and a second portion ( 3 b ) adapted to be connected to a carrier structure of the aircraft, said leg extending along a main axis of the leg passing via said first and second leg portions;
a main damper ( 5 ) arranged to damp axial movements of the first leg portion ( 3 a ) relative to the second leg portion ( 3 b );
a first secondary damper ( 6 a ) distinct from the main damper ( 5 ), characterized in that said first secondary damper ( 6 a ) is carried by said axle shaft ( 2 ), said first secondary damper ( 6 a ) comprising:
an inertial mass (M); and
first connector ( 7 a ) connecting said inertial mass (M) to said axle shaft ( 2 ) in order to enable said inertial mass (M) to move about at least one first axis of movement (X 1 ) of said inertial mass (M) relative to the axle shaft ( 2 ) and in order to enable said inertial mass (M) to oscillate along said at least one first axis of movement (X 1 ) on either side of a stationary rest position relative to the axle shaft ( 2 ), said first connector ( 7 a ) being adapted to damp said movements of said inertial mass (M) relative to said axle shaft ( 2 ) about said at least one first axis of movement (X 1 ), said first axis of movement (X 1 ) extending in a plane (P) perpendicular to said main axis (Z).

2. The landing-gear assembly according to claim 1 , wherein said first axis of movement (X 1 ) of the inertial mass (M) of the first secondary damper lies at a distance from the main leg axis.

3. The landing-gear assembly according to claim 1 , further comprising a steering mechanism ( 4 ) adapted to steering the first portion ( 3 a ) of the leg relative to the second portion ( 3 b ) of the leg by turning the first leg portion about a steering axis that is parallel to said main leg axis (Z).

4. The landing-gear assembly according to claim 1 , wherein said first connector ( 7 a ) connecting said inertial mass (M) to said axle shaft ( 2 ) comprise:
resilient return means ( 8 a ) for returning the inertial mass (M) towards said stationary rest position of the inertial mass relative to the axle shaft ( 2 ); and
a damper ( 9 a ) that present a damping coefficient of predetermined value.

5. The landing-gear assembly according to claim 4 , wherein said resilient return means ( 8 a ) present a stiffness constant value along the first axis of movement (X 1 ) of the inertial mass (M) relative to the axle shaft ( 2 ).

6. The landing-gear assembly according to claim 1 , wherein said first axis of movement (X 1 ) of the inertial mass (M) of the first secondary damper ( 7 a ) extends along the axle shaft ( 2 ).

7. The landing-gear assembly according to claim 6 , wherein said axle shaft ( 2 ) is tubular, the first secondary damper ( 6 a ) being placed inside said tubular axle ( 2 ).

8. The landing-gear assembly, according to claim 1 , wherein said axle shaft ( 2 ) carries a second secondary damper ( 6 b ) comprising:
a second inertial mass (M); and
second connector connecting said second inertial mass to said axle in order to enable said second inertial mass to move along at least one second axis of movement (X 2 ) of said second inertial mass (M) relative to the axle shaft ( 2 ) and in order to enable said second inertial mass to oscillate along said at least one second axis of movement (X 2 ) on either side of a stationary rest position of said second inertial mass (M) relative to the axle shaft ( 2 ), said second connector being adapted to damp said movements of said second inertial mass (M) relative to said axle along said at least one second axis of movement (X 2 ), said second axis of movement (X 2 ) extending in a plane perpendicular to said main leg axis (Z) and at a distance from said main axis (Z), the axle shaft extending between first and second ends ( 2 a , 2 b ) of the axle shaft ( 2 ), the first secondary damper ( 6 a ) being carried by the first end ( 2 a ) of the axle shaft ( 2 ) and the second secondary damper ( 6 b ) being carried by the second end ( 2 b ) of the axle shaft ( 2 ).

9. The landing-gear assembly according to claim 8 , wherein the first and second dampers ( 6 a , 6 b ) are linear dampers, the first axis of movement (X 1 ) of the inertial mass (M) of the first secondary damper ( 6 a ) being parallel to the second axis of movement (X 2 ) of the second inertial mass (M) of the second secondary damper ( 6 b ).

10. The landing-gear assembly according to claim 8 , further comprising a first rim ( 10 ) for supporting a first wheel for enabling the aircraft to run on the ground and a second rim for supporting a second wheel for enabling the aircraft to run on the ground, said first and second rims being mounted to rotate about the axle shaft ( 2 ), the first secondary damper ( 6 a ) being arranged at least in part inside a hollow zone ( 10 a ) of the first rim ( 10 ) and the second secondary damper ( 6 b ) being arranged at least in part inside a hollow zone of the second rim.

11. The landing-gear assembly, according to claim 10 , wherein the inertial mass (M) of the first secondary damper ( 6 a ) is in the form of a ring ( 11 ) and extends around the first end ( 2 a ) of said axle shaft, the second inertial mass of the second secondary damper ( 6 b ) also being in the form of a ring ( 14 ) and extending around the second end ( 2 b ) of said axle shaft ( 2 ).

12. The landing-gear assembly according to claim 11 , wherein said connection means ( 7 a ) adapted to connect said inertial mass (M) of said first secondary damper ( 6 a ) to said axle shaft ( 2 ) comprise a first fastener ring ( 12 ) fastened to the axle shaft ( 2 ) and a resilient annular sleeve ( 13 ) coaxial with the inertial mass (M) of said first secondary damper ( 6 a ), said resilient annular sleeve ( 13 ) being placed between the first fastener ring ( 12 ) and the inertial mass (M) of the first secondary damper ( 6 a ).

Assignees

• Safran Landing Systems

Inventors

• Dauphin Florent
• Fortier Florent
• DUBOIS Sébastien

Classifications

• B64C25/50

  Steerable undercarriages; Shimmy-damping · CPC title

• B64C25/62 Primary

  Spring shock-absorbers; Springs · CPC title

• B64C25/34

  wheeled type, e.g. multi-wheeled bogies · CPC title

• B64C25/505 Primary

  Shimmy damping · CPC title