AIRCRAFT LANDING GEAR COMPRISING A MAIN DAMPER AND AN ANTI-SHIMMY SECONDARY DAMPER

• Main Authors: FORTIER Florent, DUBOIS Sebastien, DAUPHIN Florent
• Format: Patent
• Language: English
• Published: 15.02.2018
• Subjects: AEROPLANES; AIRCRAFT; AVIATION; COSMONAUTICS; HELICOPTERS; PERFORMING OPERATIONS; TRANSPORTING

An aircraft landing gear (1) comprises: an axle (2), a leg (3) extending along a main axis of the leg (Z) and having a first part (3a) carrying the axle (2) and a second part (3b), a main damper (5) arranged to damp axial displacements of the first leg portion (3a) with respect to the second leg portion (3b), a first secondary damper (6a) separated from the main damper and adapted to damp an angular oscillation movement about the axis (Z). The first secondary shock absorber (6a) is integrally carried by the single first leg portion (3a) and comprises: an inertia mass (M), and means (7a) for connecting the inertial mass to the first leg part (3a) suitable for damping rotational displacements of this mass of inertia around the axis Z. By means of the above structure, the damper effect on shimmy is improved and no parts of the landing gear need modification.