Abstract: A method of fabricating a blade. The blade comprises subassemblies made of thermoplastic composite materials, each subassembly comprising an internal arrangement and at least one external arrangement, each internal arrangement comprising a stack of intermediate layers comprising reinforcing fibers impregnated with a semicrystalline thermoplastic matrix, each external arrangement comprising at least one surface layer comprising reinforcing fibers impregnated with an alloy of a semicrystalline thermoplastic polymer and of an amorphous thermoplastic polymer. An assembly film comprising an amorphous thermoplastic material and a ferromagnetic member is interposed between two surface layers of two distinct subassemblies that are to be assembled together by a method of local heating by induction.

Abstract: A structure (10) for aircrafts, includes a part (20) including a metal leading edge (30), the leading edge (30) being covered by a coating (40) having a thickness which is less than or equal to ten micrometers and having a hardness higher than six hundred in the Vickers hardness test (HV). According to a mode of embodiment, the coating (40) is a multilayer stainless steel coating consisting of a superposition of layers with a low nitrogen gradient and layers with a high nitrogen gradient, the layers having a thickness essentially equal to a micrometer. An aircraft including such a structure is also described.

Abstract: A method of fabricating a blade. The blade comprises subassemblies made of thermoplastic composite materials, each subassembly comprising an internal arrangement and at least one external arrangement, each internal arrangement comprising a stack of intermediate layers comprising reinforcing fibers impregnated with a semicrystalline thermoplastic matrix, each external arrangement comprising at least one surface layer comprising reinforcing fibers impregnated with an alloy of a semicrystalline thermoplastic polymer and of an amorphous thermoplastic polymer. An assembly film comprising an amorphous thermoplastic material and a ferromagnetic member is interposed between two surface layers of two distinct subassemblies that are to be assembled together by a method of local heating by induction.

Abstract: The present invention relates to a method and to a device (1) for bonding a metal fairing (6) to protect a leading edge of an aircraft airfoil (7), said metal fairing (6) being designed to be bonded against said airfoil (7) with the help of an adhesive (9). The bonding device (1) is remarkable in that it includes a rigid yoke (2) having inserted therein induction heater means (30) for heating said metal fairing (6).

Abstract: A structure (10) for aircrafts, includes a part (20) including a metal leading edge (30), the leading edge (30) being covered by a coating (40) having a thickness which is less than or equal to ten micrometers and having a hardness higher than six hundred in the Vickers hardness test (HV). According to a mode of embodiment, the coating (40) is a multilayer stainless steel coating consisting of a superposition of layers with a low nitrogen gradient and layers with a high nitrogen gradient, the layers having a thickness essentially equal to a micrometer. An aircraft including such a structure is also described.

Abstract: A stripping composition, and a method of making the stripping composition. The stripping composition including 100 parts by weight of a base ingredient consisting in epoxy polydimethylsiloxane, 0.5 to 10 parts by weight of a polymerization agent for polymerizing the base ingredient and constituted by a diaryliodonium salt, not more than 30 parts by weight of an anti-adhesion modulator constituted by a silicone polymer; and not more than 40 parts by weight of an anti-stick agent making the composition less tacky prior to polymerization and constituted by at least one vinyl ether compound.

Abstract: The present invention relates to a method and to a device (1) for bonding a metal fairing (6) to protect a leading edge of an aircraft airfoil (7), said metal fairing (6) being designed to be bonded against said airfoil (7) with the help of an adhesive (9). The bonding device (1) is remarkable in that it includes a rigid yoke (2) having inserted therein induction heater means (30) for heating said metal fairing (6).

Abstract: A method and a device (1) for bonding a metal fairing (6) to protect a leading edge of an aircraft airfoil (7), the metal fairing (6) is designed to be bonded against the airfoil (7) with the help of an adhesive (9). The bonding device (1) is remarkable in that it includes a rigid yoke (2) having inserted therein induction heater elements (30) for heating the metal fairing (6).

Abstract: A device for de-icing an aircraft wall that comprises a composite structure (47) and layer (41) of electrically conductive material, which device comprises a plurality of thin inductor elements (33 to 35) designed to extend substantially parallel to the layer of conductive material at a distance therefrom that is small enough to ensure that when the inductor is powered by an AC source of appropriate frequency, the layer or skin heats rapidly and uniformly, without significantly heating the composite structure.

Abstract: A stripping composition, and a method of making the stripping composition. The stripping composition including 100 parts by weight of a base ingredient consisting in epoxy polydimethylsiloxane, 0.5 to 10 parts by weight of a polymerization agent for polymerizing the base ingredient and constituted by a diaryliodonium salt, not more than 30 parts by weight of an anti-adhesion modulator constituted by a silicone polymer; and not more than 40 parts by weight of an anti-stick agent making the composition less tacky prior to polymerization and constituted by at least one vinyl ether compound.

Abstract: The invention relates to a mold for making a composite material part, the mold being coated in a stripping composition. The stripping composition comprises: 100 parts by weight of a base ingredient consisting in epoxy polydimethylsiloxane; 0.5 to 10 parts by weight of a polymerization agent for polymerizing the base ingredient and constituted by a diaryliodonium salt; not more than 30 parts by weight of an anti-adhesion modulator constituted by a silicone polymer; and not more than 40 parts by weight of an anti-stick agent making the composition less tacky prior to polymerization and constituted by at least one vinyl ether compound.

Abstract: The present invention relates to a method and to a device (1) for bonding a metal fairing (6) to protect a leading edge of an aircraft airfoil (7), said metal fairing (6) being designed to be bonded against said airfoil (7) with the help of an adhesive (9) The bonding device (1) is remarkable in that it includes a rigid yoke (2) having inserted therein induction heater means (30) for heating said metal fairing (6).

Abstract: A device for de-icing an aircraft wall that comprises a composite structure (47) and layer (41) of electrically conductive material, which device comprises a plurality of thin inductor elements (33 to 35) designed to extend substantially parallel to the layer of conductive material at a distance therefrom that is small enough to ensure that when the inductor is powered by an AC source of appropriate frequency, the layer or skin heats rapidly and uniformly, without significantly heating the composite structure.

Abstract: The invention relates to a mold for making a composite material part, the mold being coated in a stripping composition. The stripping composition comprises: 100 parts by weight of a base ingredient consisting in epoxy polydimethylsiloxane; 0.5 to 10 parts by weight of a polymerization agent for polymerizing the base ingredient and constituted by a diaryliodonium salt; not more than 30 parts by weight of an anti-adhesion modulator constituted by a silicone polymer; and not more than 40 parts by weight of an anti-stick agent making the composition less tacky prior to polymerization and constituted by at least one vinyl ether compound.

Abstract: In order to remove a plate made from a material that can be heated by electromagnetic induction and retained on a supporting member by a heat-fusible adhesive, an inductor is displaced facing at least one strip of the plate in order to heat the strip by induction and heat the adhesive by conduction until the adhesive softens, and a tearing tool is driven so as to tear out the heated strip by hot-peeling. The inductor and the tearing tool are displaced jointly relative to the plate and the supporting member by means of a mobile frame, which is displaced on a stationary frame on which the supporting member and the plate are fixed.

Abstract: In order to remove a plate made from a material that can be heated by electromagnetic induction and retained on a supporting member by a heat-fusible adhesive, an inductor is displaced facing at least one strip of the plate in order to heat the strip by induction and heat the adhesive by conduction until the adhesive softens, and a tearing tool is driven so as to tear out the heated strip by hot-peeling. The inductor and the tearing tool are displaced jointly relative to the plate and the supporting member by means of a mobile frame, which is displaced on a stationary frame on which the supporting member and the plate are fixed.

Abstract: In order to remove a plate made from a material that can be heated by electromagnetic induction and retained on a supporting member by a heat-fusible adhesive, an inductor is displaced facing at least one strip of the plate in order to heat the strip by induction and heat the adhesive by conduction until the adhesive softens, and a tearing tool is driven so as to tear out the heated strip by hot-peeling. The inductor and the tearing tool are displaced jointly relative to the plate and the supporting member by means of a mobile frame, which is displaced on a stationary frame on which the supporting member and the plate are fixed.