B - Operations – Transporting – 64 – C
Patent
B - Operations, Transporting
64
C
B64C 25/58 (2006.01) B64C 25/60 (2006.01)
Patent
CA 2205489
A shock strut assembly (10) for an aircraft landing gear includes a trunnion fitting (12), a compressible oleo strut subassembly (14), a wheel subassembly (16), an energy dissipating subassembly (50), and a mechanical fuze subassembly (60). The oleo strut subassembly (14) includes a cylinder member (24) having an upper end mounted in combination with the trunnion fitting (12) by means of the mechanical fuze subassembly (60). The energy dissipating subassembly (50) includes a cylindrical cutter member (52) secured in combination with the cylinder member (24) and the trunnion fitting (12) and a frangible tube member (58) mounted in concentric combination with the cylinder member (24). The mechanical fuze subassembly (60) includes a shear ring (62). During normal landings, the shear ring (62) prevents movement of the cylinder member (24) with respect to the trunion fitting (12) in a crash landing, the shear flanges (66) shear at a predetermined axial load failure limit, which allows the cylinder member (24) to be displaced relative to the trunnion fitting (12). Displacement of the cylinder member (24) causes the frangible tube member (58) to interact with the cutter member (58) to interact with the cutter member (52), causing fracturing of the frangible tube member (58) for crash landing energy dissipation.
Un ensemble amortisseur (10) pour un train d'atterrissage d'aéronef comprend un manchon de support (12), un sous-ensemble de jambe à amortisseur compressible (14), un sous-ensembe de roues (16), un sous-ensemble dissipateur d'energie (50) et un sous-ensemble de fusible mécanique (60). Le sous-ensemble de jambe à amortisseur (14) comprend un élément cylindrique (24) ayant une extrémité supérieure montée sur le manchon de support (12) au moyen du sous-ensemble de fusible mécanique (60). Le sous-ensemble dissipateur d'énergie (50) comprend un élément coupant cylindrique (52) monté à l'élément cylindrique (24), le manchon de support (12) et un élément tubulaire frangible (58) monté dans une relation concentrique avec l'élément cylindrique (24). Le sous-ensemble de fusible mécanique (60) comporte un anneau de cisaillement (62). Pendant un atterrissage normal, l'anneau de cisaillement (62) empêche un mouvement de l'élément cylindrique (24) par rapport au manchon de support (12). Dans un atterrissage forcé, les brides de cisaillement (66) provoquent un cisaillement à une sollicitation axiale limite prédéterminée, ce qui permet à l'élément cylindrique (24) de se déplacer par rapport au manchon de support (12). Le déplacement de l'élément cylindrique (24) fait que l'élément de tube cassant (58) réagit avec l'élément coupant (52), en provoquant la fracture de l'élément tubulaire frangible (58) pour dissiper l'énergie associée à l'atterrissage forcé.
Barone Ralph P.
Delmonte Berardino
Norton Rose Or S.e.n.c.r.l. S.r.l./llp
United Technologies Corporation Sikorsky Aircraft Division
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