http://rdf.ncbi.nlm.nih.gov/pubchem/patent/CA-2576518-C

Outgoing Links

Predicate Object
assignee http://rdf.ncbi.nlm.nih.gov/pubchem/patentassignee/MD5_e24e13aac66e82998d364543edc18733
classificationCPCAdditional http://rdf.ncbi.nlm.nih.gov/pubchem/patentcpc/B64D2027-264
classificationCPCInventive http://rdf.ncbi.nlm.nih.gov/pubchem/patentcpc/B64D27-26
classificationIPCInventive http://rdf.ncbi.nlm.nih.gov/pubchem/patentipc/B64D27-26
filingDate 2005-08-01^^<http://www.w3.org/2001/XMLSchema#date>
grantDate 2014-02-25^^<http://www.w3.org/2001/XMLSchema#date>
inventor http://rdf.ncbi.nlm.nih.gov/pubchem/patentinventor/MD5_e33fdec8bbadeff5c2538af1b5b80138
http://rdf.ncbi.nlm.nih.gov/pubchem/patentinventor/MD5_ceecd0c7b4d2e0b424a740b387122332
publicationDate 2014-02-25^^<http://www.w3.org/2001/XMLSchema#date>
publicationNumber CA-2576518-C
titleOfInvention Engine assembly for aircraft
abstract The invention relates to an engine assembly for an aircraft comprising a turbojet, a engine mount pylon, and a plurality of engine mounts inserted between the engine mount pylon and the turbojet. According to the invention, the plurality of engine mounts comprises a engine mount (6a) designed so as to uniquely resist forces applied along a direction (Y) transverse to the turbojet, this engine mount (6a) comprising an intermediate fitting (46) assembled onto a first fitting (40) fixed to the pylon through two swivel axes (48) oriented parallel along a vertical direction (Z), and a pin (56) oriented along a longitudinal direction (X) and fixed to the intermediate fitting, the pin being installed on a second fitting (58) fixed to the turbojet, with clearance along the longitudinal direction (X).
priorityDate 2004-08-04^^<http://www.w3.org/2001/XMLSchema#date>
type http://data.epo.org/linked-data/def/patent/Publication

Incoming Links

Predicate Subject
isDiscussedBy http://rdf.ncbi.nlm.nih.gov/pubchem/substance/SID419545405
http://rdf.ncbi.nlm.nih.gov/pubchem/compound/CID91778

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