A semi-levered landing gear (200) including a shock strut (210) configured for coupling to an airframe (101) of an aircraft (100), a truck lever (220) being rotatably coupled to the shock strut, a tension link assembly (230) having a tension link assembly first end (230a), a tension link assembly second end (230b), and at least one tension link assembly rotation axis (TLA). The tension link assembly first end is coupled to the shock strut, and the tension link assembly second end is coupled to the truck lever. A positioning mechanism (240) is configured for coupling to one or more of the airframe and the shock strut and is coupled to the tension link assembly, wherein the tension link assembly is configured to rotate the truck lever about a truck pivot axis of rotation (TPA) between a truck lever extended position and a truck lever stowed position. -J C-)N 0 ------- 0\ ';\. VA ___ _ ___ _ ___ _ ------------ __ I _ -----------------
Single axle, semi-levered landing gear with shortening mechanism
2022-10-20
Patent
Electronic Resource
English
IPC: | B64C AEROPLANES , Flugzeuge |
SINGLE AXLE, SEMI-LEVERED LANDING GEAR WITH SHORTENING MECHANISM
European Patent Office | 2019
|SINGLE AXLE, SEMI-LEVERED LANDING GEAR WITH SHORTENING MECHANISM
European Patent Office | 2018
|Single axle, semi-levered landing gear with shortening mechanism
European Patent Office | 2021
|SINGLE AXLE, SEMI-LEVERED LANDING GEAR WITH SHORTENING MECHANISM
European Patent Office | 2018
|Single axle, semi-levered landing gear with shortening mechanism
European Patent Office | 2019
|