http://rdf.ncbi.nlm.nih.gov/pubchem/patent/JP-H10508813-A

Outgoing Links

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classificationCPCInventive http://rdf.ncbi.nlm.nih.gov/pubchem/patentcpc/B64C25-60
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filingDate 1995-11-08-04:00^^<http://www.w3.org/2001/XMLSchema#date>
publicationDate 1998-09-02-04:00^^<http://www.w3.org/2001/XMLSchema#date>
publicationNumber JP-H10508813-A
titleOfInvention Shock resistant landing gear for aircraft
abstract (57) [Summary] The shock strut assembly (10) for an aircraft landing gear is composed of a trunnion fitting (12), a compressible oleo strut auxiliary assembly (14), a wheel auxiliary assembly (16), and an energy dissipation auxiliary assembly (50). , And a mechanical fuze assist assembly (60). The oleo strut assist assembly (14) includes a cylinder member (24) having an upper end attached to the trunnion fitting (12) by a mechanical fuse assist assembly (60). The energy dissipating aid assembly (50) includes a cylindrical cutter member (52) attached to the cylinder member (24) and the trunnion fitting (12), and a fragile tube member (58) attached to the cylinder member (24). Contains. The mechanical fuse (60) includes a shearing (60). During normal landing, the shearing (62) prevents movement of the cylinder member (24) relative to the trunnion fitting (12) during an emergency landing, the shear flange (66) cuts at a predetermined axial load failure limit, Displace the cylinder member (24) with respect to the trunnion fitting (12). Due to the displacement of the cylinder member (24), the fragile flange tube member (58) interacts with the cutter member (58) to interact with the cutter member (52), and the fragile tube member for dissipating accidental landing energy. (58) is destroyed.
isCitedBy http://rdf.ncbi.nlm.nih.gov/pubchem/patent/JP-2012061984-A
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http://rdf.ncbi.nlm.nih.gov/pubchem/patent/JP-2001347997-A
http://rdf.ncbi.nlm.nih.gov/pubchem/patent/US-8690432-B2
priorityDate 1994-11-18-04:00^^<http://www.w3.org/2001/XMLSchema#date>
type http://data.epo.org/linked-data/def/patent/Publication

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