A de-icing assembly (30) for a surface of an aircraft includes a carcass (38), seams (42), inflation passages (52), a manifold (32), and a reinforcement stitchline (48). The carcass includes a first layer (54), a second layer (46), and a carcass centerline. The seams are sewn into the carcass and join the first and second layers of the carcass together. The inflation passages are formed by the seams and are disposed between the first and second layers of the carcass. The manifold includes a width and a manifold centerline oriented approximately perpendicular to the carcass centerline and is fluidly connected to and is disposed beneath the carcass. The first reinforcement stitchline is sewn into the carcass adjacent to one of the plurality of seams and is disposed at a location on the carcass overlapping with the manifold. The first reinforcement stitchline is disposed approximately perpendicular to the manifold centerline and extends across the width of the manifold.
SEWN REINFORCEMENT FEATURES FOR PREVENTION OF STITCH BREAKAGE IN A PNEUMATIC DE-ICER
GENÄHTE VERSTÄRKUNGSSTRUKTUREN ZUR VERHINDERUNG VON NÄHSTICHBRUCH IN EINEM PNEUMATISCHEN ENTEISER
ÉLÉMENTS DE RENFORT COUSUS POUR LA PRÉVENTION DE LA RUPTURE DE MAILLES DANS UN DÉGIVREUR PNEUMATIQUE
06.11.2019
Patent
Elektronische Ressource
Englisch
IPC: | B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT |
SEWN REINFORCEMENT FEATURES FOR PREVENTION OF STITCH BREAKAGE IN A PNEUMATIC DE-ICER
Europäisches Patentamt | 2018
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