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.
ATTERRISSEUR POUR AÉRONEF COMPORTANT UN AMORTISSEUR PRINCIPAL ET UN AMORTISSEUR SECONDAIRE ANTI SHIMMY
LANDING GEAR FOR AN AIRCRAFT COMPRISING A MAIN SHOCK-ABSORBER AND A SECONDARY ANTI-SHIMMY SHOCK-ABSORBER
FAHRWERK FÜR LUFTFAHRZEUG, DAS EINEN HAUPTSTOSSDÄMPFER UND EINEN SEKUNDÄREN ANTI-SHIMMY-STOSSDÄMPFER UMFASST
2018-12-26
Patent
Electronic Resource
French
IPC: | B64C AEROPLANES , Flugzeuge |
European Patent Office | 2019
|European Patent Office | 2017
|TRAIN D'ATTERRISSAGE POUR AÉRONEF COMPORTANT UN AMORTISSEUR SECONDAIRE ANTI-SHIMMY
European Patent Office | 2017
|TRAIN D'ATTERRISSAGE POUR AERONEF COMPORTANT UN AMORTISSEUR SECONDAIRE ANTI-SHIMMY
European Patent Office | 2017
|