- Patent Number:
12157,557
- Appl. No:
17/926344
- Application Filed:
May 19, 2021
- نبذة مختصرة :
An aircraft undercarriage includes a leg for mounting on a structure of the aircraft so as to be movable between a deployed position and a retracted position, the undercarriage being fitted with a breaker strut including two hinged elements that are hinged together at a knee, with a first element for coupling to the structure of the aircraft and a second element for coupling to the undercarriage, a return member being arranged between the two elements to urge them towards a substantially aligned position that is defined by respective abutments. According to the invention, one of the strut elements incorporates a linear actuator having a slidable rod that is coupled to the other strut element by means of a link, the assembly being arranged in such a manner that moving the slidable rod of the actuator in a single direction causes, in succession, the elements of the strut to move out of alignment and the undercarriage to move from the deployed position to the retracted position.
- Inventors:
SAFRAN LANDING SYSTEMS (Velizy Villacoublay, FR)
- Assignees:
SAFRAN LANDING SYSTEMS (Velizy Villacoublay, FR)
- Claim:
1. An aircraft undercarriage including a leg for mounting on a structure of an aircraft so as to be movable between a deployed position and a retracted position, the aircraft undercarriage comprising: a breaker strut that is fitted to the aircraft undercarriage and that comprises: a first element and a second element that are hinged together at a knee, with the first element for coupling to the structure of the aircraft and the second element for coupling to the undercarriage; a return member being arranged between the first element and the second element to urge the first element and the second element towards a substantially aligned position that is defined by respective abutments, wherein one of the first element and the second element incorporates a linear actuator having a slidable rod that is coupled to the other of the first element and the second element by a link, and wherein moving the slidable rod of the actuator in a single direction causes, in succession, the first element and the second element of the breaker strut to move out of alignment and the undercarriage to move from the deployed position to the retracted position, wherein the linear actuator has a body in which the slidable rod slides and that forms the one of the first element and the second element that incorporates the linear actuator.
- Claim:
2. The undercarriage according to claim 1 , wherein the abutments comprise firstly an end of a tab projecting from the one of the first element and the second element carrying the linear actuator, and secondly an end of the link that is hinged to the other of the first element and the second element.
- Claim:
3. The undercarriage according to claim 1 , wherein the linear actuator is incorporated in the one of the first element and the second element that is coupled to the leg of the undercarriage.
- Claim:
4. The undercarriage according to claim 3 , wherein the one of the first element and the second element that does not carry the linear actuator has a panel shape.
- Claim:
5. The undercarriage according to claim 1 , wherein the body carrying coupling members for coupling the one of the first element and the second element that incorporates the linear actuator both to the other of the first element and the second element and also to one of the leg and the structure of the aircraft to which that of the first element and the second element that incorporates the linear actuator is coupled.
- Claim:
6. The undercarriage according to claim 5 , wherein the slidable rod slides along a sliding axis that is contained in a plane defined by hinge axes of the one of the first element and the second element in which the slidable rod is incorporated.
- Claim:
7. The undercarriage according to claim 5 , wherein the slidable rod slides along a sliding axis that does not lie in a plane defined by hinge axes of the one of the first element and the second element in which the slidable rod is incorporated.
- Patent References Cited:
2959381 November 1960 Hartel
20180001997 January 2018 Ducos
20200094950 March 2020 Bennett
414427 April 1936
3263450 January 2018
529460 November 1940
- Other References:
International Search Report for PCT/EP2021/063228 dated Aug. 4, 2021. cited by applicant
- Primary Examiner:
Abell, Tye William
- Attorney, Agent or Firm:
Sughrue Mion, PLLC
- الرقم المعرف:
edspgr.12157557
Processing Request
No Comments.