708results about "Aircraft lighting protectors" patented technology

Surface films, paints, or primers can be used in preparing aircraft structural composites that may be exposed to lightning strikes. Methods for making and using these films, paints or primers are also disclosed. The surface film can include a thermoset resin or polymer, e.g., an epoxy resin and / or a thermoplastic polymer, which can be cured, bonded, or painted on the composite structure. Low-density electrically conductive materials are disclosed, such as carbon nanofiber, copper powder, metal coated microspheres, metal-coated carbon nanotubes, single wall carbon nanotubes, graphite nanoplatelets and the like, that can be uniformly dispersed throughout or on the film. Low density conductive materials can include metal screens, optionally in combination with carbon nanofibers.

The present invention relates to a component, in particular in the field of aviation and spaceflight, having a resin matrix in which carbon nanotubes are embedded for high conductivity of the component.

A lightning protection system for protecting composite structures and a method of protecting composite structures from lightning strikes. A dielectric ply is fixed above and completely covers metal surface features, e.g., skin fasteners through a composite skin to a wing fuel tank. A conductive ply is fixed above and completely covers the dielectric ply and extends to an external connection to a platform ground. The conductive ply directs current from lightning strikes away from metal surface features, e.g., to the platform ground. Both plies may be adhesively backed and sequentially pressed into place.

According to a non-limiting embodiment of the present invention, an appliqué coating is provided for a substrate. The appliqué coating includes a metal foil and a first polymer film underlying the metal foil. A topcoat overlying the metal foil may be provided as a layer of paint or as a second polymer film. An adhesive, such as a pressure sensitive adhesive, underlying the first polymer film may be provided to affix the appliqué coating to the substrate. If desired, fibers may be dispersed throughout the second polymer film to provide anti-static properties. Also, an ink layer may be provided between the metal foil and the second polymer film, if desired, for aesthetic and / or anti-static purposes.

An overlay of patterned metal foil above a substrate to be protected supports development of localized coronas after a lightning strike. The localized coronas transport energy of a lightning strike above the substrate's surface with limited removal of metal foil from the lightning strike attachment point. A first polymer film underlies patterned metal foil. A topcoat overlies the patterned metal foil. An adhesive, underlying the first polymer film affixes the lightning diverter overlay to the substrate. If desired, semiconductor particulates may be dispersed throughout the second polymer film to contribute to instantaneous generation of localized coronas. Also, an ink layer may be provided between the patterned metal foil and the topcoat or on the exterior, if desired, for aesthetic and / or anti-static purposes.

A composite material, the composite material comprising at least one prepreg, said prepreg comprising at least one polymeric resin and at least one fibrous reinforcement; and conducting particles dispersed in the polymeric resin.

A structural joint for the transmission and control of high current flows in a carbon fiber or carbon fiber hybrid composite structure, said joint includingat least two composite structures comprising a multiplicity of resin bonded carbon fiber plies,an adhesive applied there between and capable of conducting high currentssaid adhesive comprising a conductive carrier film comprising carbon fibers,wherein the electrical conductivity of the adhesive is comparable with that of the adjacent composite structures.

The invention is directed to an integrated lightning strike protection system adapted for automated placement on a composite structure comprising a surfacing layer consisting of an organic polymer resin, a conductive layer of an expanded metal foil, an isolation / tack layer, and a carrier paper layer. In another embodiment of the invention, there is provided an integrated lightning strike protection system comprising an integrated lightning strike protection material consisting of an expanded metal foil encapsulated in organic polymer resin mounted on a carrier paper, and an automated placement machine suitable for placing the material on an aircraft composite part for protection of the composite part from lightning strikes. In another embodiment of the invention, there is provided a method for fabricating a composite structure with lightning strike protection.

A lightning protection appliqué incorporates a plurality of conductive plies adhesively affixed to a composite surface, at least a first one of the plies providing conductive characteristics sufficient to divert electrical energy from a lightning strike and at least a second one of the plies comprising operational circuitry. A dielectric ply is fixed to the composite surface over and completely covering at least one metal surface feature between the plurality of conductive plies and the composite surface.

An appliqué for forming a surface coating to a substrate is disclosed. The appliqué contains a sectioned metal foil that provides a large area electrical circuit for connecting electrical devices. The appliqué may provide additional functions including lightning strike protection. The substrate may be an aircraft surface.

A system for protecting a composite-body aircraft from damage caused by lightning strikes includes a Faraday cage defined on the exterior surface of the aircraft body by a continuous, electrically conductive grid that extends to the outermost lateral periphery of the body. In one possible embodiment in which the aircraft's body includes a plurality of composite panels that are joined at their adjacent edges by splice plates, the conductive grid may advantageously be formed by electrically conductive splice plates, e.g., of titanium, that have their respective, adjacent ends electrically connected to each other, e.g., with conductive straps and fasteners. The conductive grid provides preferential attachment points and conductive paths for lightning strikes on the surface of the aircraft, thereby shielding the interior of the grid from lightning damage. The conductive grid can optionally function as a ground return path for the aircraft's electrical system.

A method for reestablishing the electrical continuity of an electrically conductive layer of a composite aircraft wing damaged by a lightning strike or other mechanical event is disclosed in which a copper patch replaced the damaged section of the electrically conductive layer contained. The repair is performed by first removing any surfacers, fasteners, and damaged electrically conductive layer to expose a portion of the underlying composite skin. A copper patch having a copper foil section coupled to an unsupported film adhesive is then introduced onto an underlying composite skin opening contained within an undamaged section of a copper foil grid and covered with resin-impregnated fiberglass material. The film adhesive and resin-impregnated fiberglass material are then cured and fasteners are then reinserted within the fiberglass material, copper patch and underlying composite skin. The surface of the composite wing is then reprimed and repainted to complete the repair.

Lightning strike protection system for aircraft fuel tanks made of low electrical conductivity composite material. The system comprises an electrical conductive thin wire mesh (1) that covers the whole external surface of the tank outer skin (I) made of composite and a thick wire metallic mesh (2) overlapping the mesh (1) at a minimum distance of 50 mm to both sides of a row of fasteners (III) joining the said outer skin (I) to one internal part (II) of either composite or metallic material. Both metallic meshes (1, 2) maintain electrical contact by their installation / assembly and by means of metallic countersunk head washers (3) connected to bonding points and set to the gap existing between the fastener (III) and the outer skin (I). The corresponding fabrication process is also described.

A composite laminate for use on an external part of an aerospace vehicle has improved ultraviolet resistance and resistance to microcracking from thermal cycling. The laminate comprises a nanoreinforcement film, a support veil, and a composite layer. The laminate also can have a lightning strike protection layer and an external paint and primer. The nanoreinforcement film can comprise carbon nanomaterial and a polymer resin, and the composite layer has one or more layers of a reinforcement and a polymer resin. The carbon nanomaterial can be carbon nanofibers, and the nanoreinforcement film can have an areal weight of less than about 100 g / m2. The carbon nanomaterial can also comprise carbon nanofibers and carbon nanotubes.

Embodiments of the invention are directed to metal- or metal alloy-coated sheet materials (hereinafter, “metal-coated sheet material”) including, but not limited to, fabrics and veils which have a metal content of between one (1) and fifty (50) grams per square meter (gsm). The metal-coated sheet materials may be used as-is or in conjunction with prepregs, adhesives or surfacing films to provide lightning strike protection (LSP) and / or bulk conductivity, among other benefits, to the resultant composite article. In one embodiment, the metal-coated sheet material is impregnated with a resin. According to embodiments of the invention, a metal is applied to one or two sides of the fabric or veil by a physical vapor deposition coating process. The resultant metal-coated fabric or veil may be used as a carrier in surfacing films to impart surface conductivity; may be used as a carrier in adhesives to form conductive adhesive-bonded joints; may be interleaved (one or more metal-coated veils) between layers of prepreg to impart surface and / or bulk conductivity as well as toughness; or may be used to fabricate composite articles.

A method and apparatus for lighting protection. In one advantageous embodiment a method forms a lighting protection system on a composite surface of an aircraft. A dielectric coating is formed on the composite surface in which the dielectric coating covers a metal feature exposed on the composite surface. A metal adhesion promoter is applied in a pattern on the dielectric coating and over additional areas of the composite surface, including a grounding feature to form a metal adhesion promoter layer. A metal coating is formed on the metal adhesion promoter layer to create a path from an area including the metal feature to the grounding feature.

A current diverter strip is provided having a dielectric (22) located above a plurality of conductive segments (24). An insulator (30) is also provided among said conductive segments (24) and below said dielectric (22). When RF transparency is required, the conductive segments (24) can have a maximum dimension that is approximately 1 / 6th of a wavelength of the highest operating frequency of an antenna that may be communicating through the current diverter strip. The dielectric (22) may be colored to match the color of the structure to which it is implemented. Upon exposure to a strong electric field, the current diverter strip (20) forms an ionized channel above the dielectric (22). In various implementations, the current diverter strip may be radio frequency transparent, environmentally and chemically resistant, color matched to its surroundings, and / or can withstand repeated uses.

A coupling for connecting fuel pipes in an aircraft is provided. At least one of the fuel pipes is capable of movement with respect to the coupling. The coupling comprises a pipe end fitting and a socket arrangement. The pipe end fitting is located within the socket arrangement. At least one resiliently flexible electrical contact is located between the pipe end fitting and the socket arrangement. The coupling may thus form a flexible coupling electrically connecting two pipes to prevent static electricity build-up whilst permitting movement between the pipes.

An aircraft component having an external surface includes an improved lightning strike protection surface film disposed on or proximate to the external surface. The surface film includes a preform that includes a substrate having a first areal weight density and a plurality of spaced carbon nanotubes grown on the substrate, the nanotubes having a second areal weight density. The sum of the first areal weight density and the second areal weight density is less than about 500 grams per square meter, and the preform has a surface resistance less than about 1 ohm / square.

The electrical connection device (2) comprises: at least one electrically conducting contact part (20), with first and second substantially opposite faces (22, 24), the first face being provided with a shoulder (26) delimiting a peripheral part (28) with a peripheral face (30), and a central part (32) with a central face (34), at least one seal (8), and means of fastening the device on a support (10), capable of maintaining electrical contact between said support (10) and said contact part (20). Application for making a metallisation point by fastening an electrical connection device (2) on a support (10) provided with at least one electrically conducting support face (12).

A de-icing / anti-icing system including at least two conductive structures embedded in an article that includes an outer surface designed as an aerodynamic surface. At least one of the conductive structures is arranged adjacent the outer surface. A control unit adapted to control the energy supply to the conductive structures for generating heat to the outer surface. A first of the conductive structures includes a first conductive nano structure and a second of the conductive structures includes a second conductive nano structure. A conductive property of the first of the conductive structures differs from a conductive property of the second of the conductive structures. The first conductive nano structure serves as a heating conductor and the second conductive nano structure serves as a heating element. The first and second conductive nano structures are embedded in a common plane of a resin layer forming the outer surface.

A washer, a fastening assembly including the washer and a composite structure including the washer sealing the assembly for internal lightning strike protection. The washer includes one or more concentric ribs that are dielectric rings on both sides. When used (e.g., with a nut and bolt) internal to a structure, especially a composite structure, the washer seals the fastener hole (i.e., that the bolt passes through) and contains any sparking and hot gasses that may arise in the fastener hole from entering the structure.

A sealant 34 filled into a cap 30A is caused to overflow through both an opening in a first end portion 30a of the cap 30A and a through-hole 40 of the cap 30A when the cap 30A is pressed against a fastener member 25. With regard to the cap 30A, a ratio between inside diameter D1 of the opening on the side of the first end portion 30a and hole diameter D2 of the through-hole 40 in the second end portion 30b is set as follows: 0.10≦D2 / D1 ≦0.27.

A system for protecting a composite-body aircraft from damage caused by lightning strikes includes a Faraday cage defined on the exterior surface of the aircraft body by a continuous, electrically conductive grid that extends to the outermost lateral periphery of the body. In one possible embodiment in which the aircraft's body includes a plurality of composite panels that are joined at their adjacent edges by splice plates, the conductive grid may advantageously be formed by electrically conductive splice plates, e.g., of titanium, that have their respective, adjacent ends electrically connected to each other, e.g., with conductive straps and fasteners. The conductive grid provides preferential attachment points and conductive paths for lightning strikes on the surface of the aircraft, thereby shielding the interior of the grid from lightning damage. The conductive grid can optionally function as a ground return path for the aircraft's electrical system.

A pre-fabricated article for a composite aircraft component includes a dielectric layer and a pre-fabricated metalized pattern on the dielectric layer. The metalized pattern is fabricated on the dielectric layer prior to integration with the composite aircraft component. The metalized pattern diverts EME current away from EME protection areas of the aircraft component.

A method and apparatus for implementing a return current network that is external to a composite structure, which directs a current along a known path to the aircraft grounding system using appliqués. The appliqués have a dielectric polymer to isolate the return current from the structure, and a metal foil for conducting the current

A lightning protection system for a wind turbine blade or aircraft wing includes a glass-reinforced fiber or carbon-reinforced wind turbine blade or aircraft wing having a tip region, a suction side, a pressure side, a leading edge and a trailing edge. A substantially planar sheet of conductive or semi-conductive material is disposed internal to the blade tip region or wing tip region and between the suction side and pressure side. The sheet operates during a lightning discharge to form an electric field control mechanism causing the lightning discharge to attach to the tip region. The sheet is in electrical communication or galvanic connection with a conductive or semi-conductive path such that the electric field control mechanism and the path together operate to protect the wind turbine blade or aircraft wing from damage caused by the lightning strike in the tip region of the wind turbine blade or aircraft wing by controlling an electric field in the tip region caused by the lightning strike.

A sleeve interference fastener including a conformable sleeve, wherein the conformable sleeve is comprised of at least one first material having a hardness of X, and a pin member, wherein the pin member is comprised of at least one second material having a hardness of Y, wherein X is sufficiently less than Y so that, in an installed position of an interference fit, at least a portion of the at least one first material of the conformable sleeve conforms to a contour of an inner surface of a hole of a composite structure so as to create a continuous electrical contact at an interface between the inner surface of the hole of the composite structure and the conformable sleeve.