AIRCRAFT LANDING GEAR COMPRISING A MAIN DAMPER AND AN ANTI-SHIMMY SECONDARY DAMPER
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 por...
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Main Authors | , , |
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Format | Patent |
Language | English |
Published |
15.02.2018
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Subjects | |
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Abstract | 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. |
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AbstractList | 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. |
Author | DUBOIS Sebastien DAUPHIN Florent FORTIER Florent |
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RelatedCompanies | SAFRAN LANDING SYSTEMS |
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Snippet | 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)... |
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SubjectTerms | AEROPLANES AIRCRAFT AVIATION COSMONAUTICS HELICOPTERS PERFORMING OPERATIONS TRANSPORTING |
Title | AIRCRAFT LANDING GEAR COMPRISING A MAIN DAMPER AND AN ANTI-SHIMMY SECONDARY DAMPER |
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