MAIN LANDING GEAR OF AN AIRCRAFT, COMPRISING TWO WALKING BEAMS JOINED TO THE STRUCTURE OF THE AIRCRAFT IN AN ARTICULATED MANNER

• US 20130068884A1
• Filed: 06/16/2011
• Published: 03/21/2013
• Est. Priority Date: 06/16/2010
• Status: Active Grant

• Current Assignee: Safran Landing Systems
• Original Assignee: Messier-Bugatti-Dowty
• Inventors: Ducos, Dominique
• Granted Patent: US 9,073,629 B2
• Time in Patent Office: Days
• US Class Current: 244/102.A
• CPC Class Codes: B64C 2025/125 into the fuselage, e.g. main landing gear pivotally retracting into or extending out of the fuselage
• CPC Class Codes: B64C 25/10 retractable, foldable, or the like
• CPC Class Codes: B64C 25/14 fore-and-aft
• CPC Class Codes: B64C 25/34 wheeled type, e.g. multi-wheeled bogies

Abstract

An aircraft undercarriage comprising two rocker beams (1, 2) carrying wheels and mounted to pivot on a common pivot (Y1), the undercarriage including a shock-absorber device comprising two connecting rods (5, 6), each coupled to a respective one of the rocker beams, at least one of the connecting rods being telescopic and forming a shock absorber, the two connecting rods also being coupled to a rocker (7) pivotally mounted on a central pivot (8). The common pivot of the rocker beams is secured to the structure of the aircraft and is mounted in a fixed position thereon, while the central pivot of the rocker is movable between a first position in which the rocker beams are in a landing position, and a second position in which the rocker has pulled on the connecting rods to cause the rocker beams to pivot towards a retracted position.

Claims

1. An aircraft undercarriage comprising two rocker beams (1, 2) carrying wheels and mounted to pivot on a common pivot (Y1), the undercarriage including a shock-absorber device comprising two connecting rods (5, 6), each coupled to a respective one of the rocker beams, at least one of the connecting rods being telescopic and forming a shock absorber, the two connecting rods also being coupled to a rocker (7) pivotally mounted on a central pivot (8), wherein the common pivot of the rocker beams is secured to the structure of the aircraft and is mounted in a fixed position thereon, while the central pivot of the rocker is movable between a first position in which the rocker beams are in a landing position, and a second position in which the rocker has pulled on the connecting rods to cause the rocker beams to pivot towards a retracted position.

2. The aircraft undercarriage according to claim 1, wherein the pivot of the rocker is mounted at the end of a panel (9) that is pivotally mounted on the structure of the aircraft to pivot between an active position in which the pivot of the rocker is substantially vertically in register with the common pivot of the rocker beams, this position corresponding to the landing position of the rocker beams, and a retracted position in which the rocker has pulled on the connecting rods in order to cause the rocker beams to pivot towards their retracted position.

3. The aircraft undercarriage according to claim 2, wherein a threshold positioner (29) is coupled between the rocker and the structure of the aircraft to co-operate with the panel and the rocker to form a deformable parallelogram system.

4. The undercarriage according to claim 2, wherein a driving actuator (10) is coupled between the panel and the structure of the aircraft to cause the panel to pivot selectively between the active position and the retracted position.

5. The undercarriage according to claim 2, wherein an alignment stabilizer device (20) is coupled between the panel and the structure of the aircraft in order to stabilize the panel in the active position.