US 12,377,966 B2
Aircraft landing gear assembly
Ian Robert Bennett, Gloucester (GB)
Assigned to SAFRAN LANDING SYSTEMS UK LTD., Gloucester (GB)
Appl. No. 18/684,605
Filed by SAFRAN LANDING SYSTEMS UK LTD., Gloucester (GB)
PCT Filed Aug. 26, 2022, PCT No. PCT/EP2022/073770
§ 371(c)(1), (2) Date Feb. 16, 2024,
PCT Pub. No. WO2023/031035, PCT Pub. Date Mar. 9, 2023.
Claims priority of application No. 21194061 (EP), filed on Aug. 31, 2021.
Prior Publication US 2025/0121932 A1, Apr. 17, 2025
Int. Cl. B64C 25/12 (2006.01)
CPC B64C 25/12 (2013.01) 14 Claims
OG exemplary drawing
 
1. An aircraft landing gear assembly comprising:
a first structural member;
a second structural member pivotally coupled to the first structural member at an apex pivot point so as to be movable between a first angular condition and a second angular condition distinct from the first angular condition;
a down-lock spring having a first end region pivotally coupled to a mounting structure and being arranged under tension to bias the first and second structural members to assume the first angular condition; and
a linkage assembly, the linkage assembly comprising:
an arm member pivotally coupled to one of the first and second structural members at an arm pivot point, the arm having a first end region pivotally coupled to a second end region of the down-lock spring; and
a control link pivotally coupled to one of the first and second structural members at a first control link pivot point and pivotally coupled to the arm member at a second control link pivot point such that, as the first and second structural members move relative to one another from the first angular condition towards the second angular condition, the first control link pivot point moves over centre, through an axis or plane bisecting the apex pivot point and the second control link pivot point,
wherein one of the first and second structural members is a lock link, and the other of the first and second structural members is a stay arm.