Abstract: An aircraft undercarriage comprising a shock absorber further comprising first and second portions that are mounted to slide telescopically relative to each other and that can come into internal abutment in the event of the shock absorber being compressed, the undercarriage being fitted with a detector device for detecting the shock absorber coming into internal abutment, which comprises firstly a punch secured to the first portion of the shock absorber or to a portion of the undercarriage that does not slide relative to the first portion of the shock absorber, and secondly a sacrificial piece secured to the second portion of the shock absorber or to a portion of the undercarriage that does not slide relative to the second portion of the shock absorber, the punch and the sacrificial piece being arranged in such a manner that, in the event of the two portions of the shock absorber coming into internal abutment, the punch strikes the sacrificial piece so as to form an indentation therein.

Abstract: An aircraft undercarriage comprising a shock absorber further comprising first and second portions that are mounted to slide telescopically relative to each other and that can come into internal abutment in the event of the shock absorber being compressed, the undercarriage being fitted with a detector device for detecting the shock absorber coming into internal abutment, which comprises firstly a punch secured to the first portion of the shock absorber or to a portion of the undercarriage that does not slide relative to the first portion of the shock absorber, and secondly a sacrificial piece secured to the second portion of the shock absorber or to a portion of the undercarriage that does not slide relative to the second portion of the shock absorber, the punch and the sacrificial piece being arranged in such a manner that, in the event of the two portions of the shock absorber coming into internal abutment, the punch strikes the sacrificial piece so as to form an indentation therein.

Abstract: The invention relates to a turbomachine module comprising a device to improve radial clearances, comprising an outer casing (22), an inner casing (21) and at least one shock absorbing ring (5) connecting the casings, the module also comprising an annular cavity (43) on the downstream side of the ring (5), with a passage (42) formed in it through which an airflow (4) is drawn off from the primary flow (Fp). According to the invention, the device to improve radial clearances comprises a thermal inertia control device for the shock absorbing ring mounted on the shock absorbing ring (5), downstream from it, this device comprising at least one coat of thermal insulation (8), and at least partly delimiting the annular cavity (43) on the downstream side of it (43).

Abstract: The invention relates to a turbomachine module comprising a device to improve radial clearances, comprising an outer casing (22), an inner casing (21) and at least one shock absorbing ring (5) connecting the casings, the module also comprising an annular cavity (43) on the downstream side of the ring (5), with a passage (42) formed in it through which an airflow (4) is drawn off from the primary flow (Fp). According to the invention, the device to improve radial clearances comprises a thermal inertia control device for the shock absorbing ring mounted on the shock absorbing ring (5), downstream from it, this device comprising at least one coat of thermal insulation (8), and at least partly delimiting the annular cavity (43) on the downstream side of it (43).