# US 10,479,486 B2 · Aircraft undercarriage with a rotary drive actuator

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- Number: US 10,479,486 B2
- Document ID: US10479486B2
- Status: Granted
- Kind: B2
- Application number: 15/633,884
- Filed: 2017-06-27
- Published: 2018-01-04
- Granted: 2019-11-19
- Earliest claimed: 2016-07-01
- Assignees: Safran Landing Systems
- Applicants: Safran Landing Systems
- Inventors: Dominique Ducos; Philippe Henrion
- Web page: https://patentgrep.com/patent/US10479486B2

## CPC

- B64C 25/10: retractable, foldable, or the like
- B64C 25/14: fore-and-aft
- B64C 25/26: Control or locking systems therefor
- B64C 25/34: wheeled type, e.g. multi-wheeled bogies
- B64C: AEROPLANES; HELICOPTERS

## Abstract

The invention relates to an aircraft undercarriage having a leg (2) pivotally mounted on a structure of the aircraft to pivot about a pivot axis (X1) between a deployed position and a retracted position, the undercarriage including a foldable brace (3a, 3b) comprising two hinged-together elements, one of which is hinged to the leg and the other of which is hinged to the structure of the aircraft, in such a manner that when the leg is in the deployed position, the two brace elements are locked together in a substantially aligned position, the undercarriage also being provided with a rotary drive actuator (10) having an outlet shaft acting on one of the elements of the foldable brace in order to cause the leg to pivot between its two positions. The drive actuator is pivotally mounted on the structure of the aircraft to pivot about an axis of rotation (X3) of the outlet shaft, the drive actuator having a casing (12) connected by a reaction rod (13) to the leg in order to take up the torque developed by the drive actuator when driving the undercarriage.

## Claims

### Claim 1

An aircraft undercarriage having a leg (2; 102) pivotally mounted on a structure of the aircraft to pivot about a pivot axis (X1) between a deployed position and a retracted position, the undercarriage including a foldable brace (3a, 3b; 103a, 103b) comprising two hinged-together elements, one of which is hinged to the leg and the other of which is hinged to the structure of the aircraft, in such a manner that when the leg is in the deployed position, the two brace elements are locked together in a substantially aligned position, the undercarriage also being provided with a rotary drive actuator (10; 110) having an outlet shaft acting on one of the elements of the foldable brace in order to cause the leg to pivot between its two positions, the undercarriage being characterized in that the drive actuator is pivotally mounted on the structure of the aircraft to pivot about an axis of rotation (X3) of the outlet shaft, the drive actuator having a casing (12; 112) connected by a reaction rod (13; 113) to the leg in order to take up the force developed by the drive actuator when driving the undercarriage.

### Claim 2 (depends on 1)

An undercarriage according to claim 1, wherein the outlet shaft of the drive actuator (12) is connected directly to one of the brace elements (3a, 3b).

### Claim 3 (depends on 2)

An undercarriage according to claim 2, wherein the outlet shaft of the drive actuator (112) is connected to the brace elements via locking elements (120a, 120b) for locking the brace elements in the aligned position when the undercarriage is in the deployed position.

### Claim 4 (depends on 1)

An undercarriage according to claim 1, wherein the axis of rotation of the outlet shaft of the actuator coincides with a pivot axis (X3) of the foldable brace (3) relative to the structure of the aircraft.