Flugzeugfahrwerksbaugruppe

Details

Veröffentlichungs-Nr.

EP4752052

Anmeldetag

26. November 2025

Veröffentlichung

3. Juni 2026

Rechtsraum

EP

Abstract

A landing gear assembly (30) for an aircraft (10), the landing gear assembly comprising: a forward brace (40) having a first end (41) for attachment to an airframe of the aircraft, and a second end (43); an aft brace (50) having a first end (51) for attachment to the airframe of the aircraft, and a second end (53), wherein the second end (53) of the aft brace is coupled to the second end (43) of the forward brace; an actuator piston (70) having a first end (71) and a second end, wherein the first end (71) of the actuator piston is pivotally coupled to the first end (41) of the forward brace; a bellcrank linkage (60) having a first end (62), a second end (64), and a pivot point (63) between the first end and the second end, such that a first portion of the bellcrank linkage extends from the first end (62) to the pivot point (63), and a second portion of the bellcrank linkage extends from the pivot point (63) to the second end (64), wherein the pivot point of the bellcrank linkage is pivotally coupled to the first end (51) of the aft brace, and wherein the first end (62) of the bellcrank linkage is pivotally coupled to the second end of the actuator piston (70); a primary strut (90) having a first end (91) and a second end (96), wherein the first end of the primary strut is pivotally coupled to the second end (43) of the forward brace (40) and the second end (53) of the aft brace (50), and wherein one or more wheels (100) of the aircraft are mounted at the second end (96) of the primary strut (90); and a secondary strut (80, e.g. a shock absorber) having a first end (81) and a second end (83), wherein the first end of the secondary strut is pivotally coupled to the second end (64) of the bellcrank linkage (60), and wherein the second end (83) of the secondary strut (80) is pivotally coupled to a pivot point near to the second end (96) of the primary strut (90); wherein the landing gear assembly is configured to adopt a deployed configuration when the actuator piston (70) is in a retracted configuration, and wherein the landing gear assembly is configured to adopt a retracted configuration when the actuator piston (70) is in an extended configuration. Also provided is an aircraft (such as a blended wing body aircraft BWB) having such a landing gear assembly.

Anmelder

Firma

Airbus Operations Limited

Land

🇬🇧 Großbritannien