| 摘要 |
A shock strut assembly (10) for an aircraft landing gear includes a trunnio n fitting (12), a compressible oleo strut subassembly (14), a wheel subassembl y (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 she ar ring (62) prevents movement of the cylinder member (24) with respect to the truni on 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) cause s the frangible tube member (58) to interact with the cutter member (58) to intera ct with the cutter member (52), causing fracturing of the frangible tube member (58) for crash landing energy dissipation.
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