Abstract: A lightweight composite panel, and resisting to impacts and to peeling, comprising: a honeycomb core in poly(p-phenyleneterephthalamide), on either side of which are positioned two skins each comprising: an internal ply comprising: a fabric of glass fiber E in contact with the honeycomb core; and a web of unidirectional carbon fibers oriented along a first direction; an external ply, in contact with the corresponding internal ply, comprising: a web of unidirectional carbon fibers oriented along a second direction different from the first direction, the web of each external ply facing the web of the corresponding internal ply; and a fabric of glass fiber E. The fabrics of glass fiber are impregnated with at least 70% by weight of epoxy resin, and have a mass of less than or equal to 30 g/m2. The webs of carbon fibers have an elastic modulus comprised between 275 and 300 GPa, are pre-impregnated with between 30% and 40% by weight of epoxy resin, and have a mass of less than or equal to 100 g/m2.

Abstract: The aim of the invention is to propose an edging method that is quick, effective, easy to implement and makes it possible to obtain a lightweight panel. To this end, the aim of the invention is a method for sealingly edging a composite panel comprising; *a step (a) of providing a composite panel of redefined thickness having two planar faces and a side to be edged, and of providing a sealing strip made from a polymer material having a width greater than the thickness of the composite panel, and comprising a first face, referred to as the “inner” face, and a second face, referred to as the “outer” face, in reference to the position of use of same: *a step (b) of applying the strip and an adhesive to the side and to a peripheral portion of the planar faces of the composite panel in such a way that the adhesive is located between the composite panel and the inner face of the strip, which sealingly protects the composite panel against dust, foreign bodies and the absorption of moisture.

Abstract: The aim of the invention is to propose an edging method that is quick, effective, easy to implement and makes it possible to obtain a lightweight panel. To this end, the aim of the invention is a method for sealingly edging a composite panel comprising; *a step (a) of providing a composite panel of redefined thickness having two planar faces and a side to be edged, and of providing a sealing strip made from a polymer material having a width greater than the thickness of the composite panel, and comprising a first face, referred to as the “inner” face, and a second face, referred to as the “outer” face, in reference to the position of use of same: *a step (b) of applying the strip and an adhesive to the side and to a peripheral portion of the planar faces of the composite panel in such a way that the adhesive is located between the composite panel and the inner face of the strip, which sealingly protects the composite panel against dust, foreign bodies and the absorption of moisture.

Abstract: A lightweight composite panel, and resisting to impacts and to peeling, comprising: a honeycomb core in poly(p-phenyleneterephthalamide), on either side of which are positioned two skins each comprising: an internal ply comprising: a fabric of glass fiber E in contact with the honeycomb core; and a web of unidirectional carbon fibers oriented along a first direction; an external ply, in contact with the corresponding internal ply, comprising: a web of unidirectional carbon fibers oriented along a second direction different from the first direction, the web of each external ply facing the web of the corresponding internal ply; and a fabric of glass fiber E. The fabrics of glass fiber are impregnated with at least 70% by weight of epoxy resin, and have a mass of less than or equal to 30 g/m2. The webs of carbon fibers have an elastic modulus comprised between 275 and 300 GPa, are pre-impregnated with between 30% and 40% by weight of epoxy resin, and have a mass of less than or equal to 100 g/m2.

Abstract: An apparatus for fixing a member to an aircraft structure including: firstly, fixing device having a shank with a head at one end, an externally machined portion of its peripheral wall at its other end, and a longitudinal interior thread at the same end as its externally machined portion, secondly, a bushing which cooperates with the machined portion of the shank so as to be fixed to the shank; and thirdly, an attachment device for attaching the member and having a threaded shank cooperating with the longitudinal interior thread.

Abstract: A system for fixing a member to an aircraft structure includes, firstly, fixing members comprising a shank with a head at one end, an externally machined portion of its peripheral wall at its other end, and a longitudinal interior thread at the same end as its externally machined portion, secondly, a bush which cooperates with the machined portion of the shank so as to be fixed to the shank, and, thirdly, an attachment for attaching the member and having a threaded shank cooperating with the longitudinal interior thread. Applications include fixing a belly fairing to an aircraft.