Abstract: Tunable thermoplastic polymer powder feedstock formulations and tunable conductive thermoplastic polymer powder feedstock formulations are disclosed for delivery to a high-velocity sprayer, along with tunable coatings made from the disclosed formulations and methods for coating installed fasteners, and fasteners, fastener/substrate interfaces and substrates coated with the tunable thermoplastic polymer coatings.

Abstract: According to one implementation of the present disclosure, a method is disclosed. The method includes: detecting, on or proximate to one or more surfaces of an aircraft, a presence of an electric-field above a predetermined threshold; and in response to the detection, activating one or more beam sources to generate an ionized column of charge away from the aircraft.

Abstract: A method for conditioning to reduce lightning strike effects is provided herein. The method includes positioning a plurality of tabs on a component. The plurality of tabs are electrically conductive. The component includes at least one of a composite material and a metal material having at least one joint. The method includes positioning the component on a support that is electrically insulated, and connecting a plurality of wires between an initial set of the plurality of tabs and a pulse generator. The pulse generator is configured to generate a plurality of current pulses through the plurality of wires. The plurality of current pulses imitate a plurality of lightning strikes. The method further includes striking the component with the plurality of current pulses from the pulse generator, and reconnecting the plurality of wires to one or more different sets of the plurality of tabs between the plurality of current pulses.

Abstract: A lightning current controlling method includes adjusting surface roughness of a surface of an aircraft body of an aircraft, a charged amount of the surface of the aircraft body of the aircraft, or both, to cause a passing path of a lightning current to be controlled when the aircraft is struck by lightning.

Abstract: An electrically conductive patch for a sheet that is part of a skin of an aircraft is disclosed. The sheet includes an outermost surface constructed of an electrically conductive material and one or more electrical discharge points that are conductively coupled to the outermost surface of the sheet. The electrically conductive patch is disposed along the outermost surface of the sheet and is conductively coupled to the outermost surface of the sheet. The electrically conductive patch is constructed of a voltage responsive film configured to change from a first coloration and into a second coloration in response to experiencing a threshold voltage difference, where the first coloration substantially matches a coloration of the skin of the aircraft.

Abstract: A lightning protection device for an aircraft, includes an anti-corona element taking a rounded shape and having an electrically conductive surface, intended for enveloping an area of the airframe of the aircraft that is liable to receive a lightning strike, one or more electric charge dissipators attached to said anti-corona element.

Abstract: A case body of a fan case in a jet engine is formed by use of a composite material of carbon fiber reinforced plastic. Metal rings are respectively attached to a leading edge and a trailing edge of the case body. The metal rings are electrically connected together by a conductive cable. Both of the metal rings and the conductive cable constitute a path of a lightning current.

Abstract: Inter alia an apparatus is disclosed including at least two multi-layer insulation, MLI, blankets, each MLI blanket having a least one bonding point. Therein, a bonding point of a first MLI blanket of the at least two MLI blankets is electrically connected to a bonding point of a second MLI blanket of the at least two MLI blankets. The second MLI blanket further has a grounding point configured to be grounded. Further, a spacecraft comprising such an apparatus is disclosed. Moreover, a method including providing at least two MLI blankets and electrically connecting a bonding point of a first MLI blanket to a bonding point of a second MLI blanket is disclosed.

Abstract: A lightning diverter element having integrated ESD protection, including a support and metallic segments disposed on the support is disclosed, wherein the support has a resistance per unit length in a range from 100 k?/m to 100 M?/m. Furthermore, a high-frequency device is disclosed, wherein such a lightning diverter element is disposed on a surface of a component of the high-frequency device. Finally, a vehicle including such a lightning diverter element and/or such a high-frequency device is disclosed.

Abstract: The present application relates to a static discharger and an aircraft including the static discharger. According to an aspect of the present application, a static discharger is provided which includes: a basement; and a discharger body adapted to be installed to the basement. The static discharger further includes a first fixing mechanism adapted to fix the discharger body to the basement. A pivoting mechanism is provided between the basement and the discharger body, the pivoting mechanism allowing the discharger body to pivot with respect to the basement so as to adjust an installation orientation of the discharger body with respect to the basement during an on-site-installation of the static discharger. According to the present application, for example, installation adaptation and universality of the static discharger can be improved.

Abstract: A spar includes a conductive layer laminated and formed on a carbon-fiber prepreg, and a jumper formed of a conductor which penetrates through the conductive layer and the carbon-fiber prepreg.

Abstract: An electrical protector with a central axis includes a cap defining a top and a downwardly extending cap wall, and insert defining a ring and an upwardly extending insert wall, at least three protrusions extending inwardly from an interior surface of the insert wall toward the central axis, and a sealant disposed at least within the cap. The cap wall engages the insert wall, thereby establishing a connection between the cap and the insert. The protrusions are adapted to engage a structure, thereby securing the electrical protector onto the structure.

Abstract: An electronic device includes a controller and a unit section. The controller is configured to control operation of the electronic device. The unit section is drawable from a main body of the electronic device on which multiple loads and the controller are mounted. The unit section includes a first load, a second load, and a third load. Each of the first load and the second load is connected to a serial communication unit that enables serial communication with the control unit. The third load is connected to a communication line used for communication with the controller, without being connected to the serial communication unit.

Abstract: An aircraft assembly comprising a plurality of structural components and an electrically conductive bonding network, wherein at least one of the structural components is formed of material of low electrical conductivity, and the bonding network includes either: at least one substantially planar strip of highly electrically conductive material attached to at least the one structural component, and wherein the strip includes a substantially omega-shaped loop extending out of the plane of the strip; or at least one strip of highly electrically conductive material attached to at least the one structural component, wherein the strip comprises first and second planar attachment portions for attaching the strip to the structural component(s) and an intermediate portion extending between the first and second attachment portions, and wherein the intermediate portion includes a loop which extends outwards from the plane of the first attachment portion.

Abstract: A static discharge device includes a body and an electrical path carried in the body for discharging static electricity. Carried on the body is visual indicia indicating a present operational status of the electrical path to discharge static electricity effectively. The visual indicia is observable to an airplane operator or technician to quickly determine the operational or non-operational status of the static discharge device.

Abstract: An electrical grounding arm is described and which has a predetermined geometry that dissipates stress imparted to the electrical grounding arm by the repeated movement of the electrical grounding arm, so as to inhibit stress related damage from being imparted to the electrical grounding arm, and which further, inhibits a source of fluid from pooling or collecting on the exterior facing surface thereof in order to prevent an unsanitary condition from developing.

Abstract: A static discharge device includes a body an an electrical path carried in the body for discharging static electricity. Carried on the body is visual indicia indicating a present operational status of the electrical path to discharge static electricity effectively. The visual indicia is observable to an airplane operator or technician to quickly determine the operational or non-operational status of the static discharge device.

Abstract: Embodiments of the invention provide an electrostatic discharge protection device or network for an integrated circuit. The network includes a first circuit branch and a second circuit branch connected in a parallel configuration. The first branch has a first inductance, a first resistance, and includes a first capacitive component. The second branch has a second inductance, a second resistance, and includes a second capacitive component. A first end of the first circuit branch and a first end of the second circuit branch are coupled to a first node, and a second end of the first circuit branch and a second end of the second circuit branch are coupled to zero-voltage reference level. The network is capable of providing a low impedance path away from a terminal of the integrated circuit during an electrostatic discharge event.

Abstract: A fastener assembly for attaching a component or bracket to the inner surface of the skin of an aircraft wing is disclosed. The fastener assembly comprises a bolt having a shaft and a bolt retaining member that threadingly cooperates with the shaft to retain the bolt in a position in which it extends through a hole in the skin. The fastener also includes a component or bracket retaining member that also threadingly cooperates with a portion of the shaft protruding through said bolt retaining member to attach a component or bracket to said inner surface.

Abstract: There is provided a method for mitigating static discharge in a fuel container. The method provides a static dissipative coating having a volume resistivity of 1.0×109 ?-m (ohm-meter) or less when measured at 40 V (volts) or less, having a surface resistivity of 1.0×1011 ?/sq (ohm per square) or less when measured at 100 V (volts) or less, having a breakdown voltage of 4000 V (volts) or less, and having a charge decay of 60 seconds or less. The method further provides applying the static dissipative coating to a surface of the fuel container to form a coated surface.

Abstract: The present disclosure teaches a lightning damage index is that used to predict the propensity of a lightning strike to an aircraft and the degree of damage to the aircraft that the lightning strike will cause. This index can help to obviate operational issues and other losses related to subsequent repairs to the aircraft that are required because of lightning damage. The disclosed method of predicting lightning strike damage to an aircraft involves generating data relating to the aircraft by measuring the dimensions of the aircraft, assessing the design features of the aircraft, and/or obtaining electromagnetic density data associated with regions of the aircraft. The method further involves creating a lightning damage index that provides a numeric representation for predicted lightning strike damage to the aircraft based on the generated data. The numeric representation may be further modified by factors associated with operation of the aircraft.

Abstract: A method and apparatus for covering a fastener system. In one illustrative embodiment, an apparatus comprises a cover. The cover is configured to be placed over a fastener system at a surface of an object in which the fastener system is installed. The cover is comprised of a number of composite materials selected such that the cover is configured to reduce an effect of an electrical discharge, which occurs around the fastener system, on an environment outside the cover.

Abstract: A lightning conductor system for a support structure having an external face intended to be subjected to a flow of air and an internal face opposite the external face, the lightning conductor system comprising an electrically conducting lightning conductor strip, intended to be placed on the side of the internal face of the support structure while being connected to ground, and means of fixing the lightning conductor strip to the support structure, the fixing means comprising fixing studs intended to be inserted into orifices formed in the support structure, said fixing studs being in electrical contact with the lightning conductor strip. The lightning conductor system includes the lightning conductor strip being mounted in an offset manner with respect to the main axes of the fixing studs.

Abstract: A system for lightning protection for power feeders may include at least one unshielded power feeder conductor; and a grounded wire extending adjacent the at least one unshielded power feeder conductor and being electrically isolated therefrom, whereby lightning current flowing through the grounded wire establishes a magnetic field sufficient to oppose and reduce lightning-induced current on the at least one power feeder conductor.

Abstract: A method for sealing an interface to attenuate high energy currents and voltages traveling thereacross may include forming a cover defining an inner volume shaped to enclose the interface; forming a filled sealant including a semi-rigid sealant mixed with a filler having a multiplicity of discrete particles of different composition than the semi-rigid sealant; placing the filled sealant within the inner volume; and placing the cover containing the filled sealant over the interface such that the filled sealant is adjacent the interface.

Abstract: A device has a first electrically conductive component, a second electrically conductive component, and an electrically conductive nanocoating (ECN) electrically connecting the first electrically conductive component to the second electrically conductive component. An aircraft has an engine, a fuselage, and a device having a first electrically conductive component, a second electrically conductive component, and an electrically conductive nanocoating (ECN) electrically connecting the first electrically conductive component to the second electrically conductive component. A method of providing an electrical conduction path includes providing a first electrically conductive component, providing a second electrically conductive component, and decreasing an electrical resistance between the first electrically conductive component and the second electrically conductive component using an electrically conductive nanocoating (ECN).

Abstract: Provided is a coupling structure for airframe components that is capable of ensuring sufficient lightning protection capability. A conductive pattern part 40 made of a conductive material is formed around each fastener member 24 between wing surface panels 21A and 21B. The conductive pattern part 40 is formed, for example, around each of holes 21c and 21d on the plane on which the wing surface panel 21A and the wing surface panel 21B abut against each other. Then, the conductive pattern part 40 is pushed against both the wing surface panel 21A and the wing surface panel 21B by the fastening power of the fastener members 24, whereby electrical conduction between the wing surface panel 21A and the wing surface panel 21B can be achieved.

Abstract: A method for forming a structure having lightning strike protection includes receiving at least one structural layer, receiving at least one lightning strike protection strip disposed on at least one reinforcement layer, automatically applying the at least one lightning strike protection strip disposed on the at least one reinforcement layer onto the at least one structural layer, and forming the at least one structural layer, the at least one lightning strike protection strip, and the at least one reinforcement layer, into the structure. The at least one lightning strike protection strip comprises a first material, and the at least one reinforcement layer comprises a second material different from the first material. The automatically applying may include using at least one of fiber placement equipment, tape laying equipment, and similar automated equipment.

Abstract: Apparatus for bleeding electrical charge and methods for installing a ground stud in a composite structure. The apparatus includes a ground stud and a composite structure including a hole. In one embodiment the ground stud engages the hole in the composite structure in a transition fit. In another embodiment the ground stud is countersunk within the composite structure. Embodiments of the present methods include drilling a hole in the composite structure; inserting the ground stud into the hole such that the ground stud is in electrical contact with conductive fibers within the composite structure; securing the ground stud to the composite structure; and attaching a connective device to the ground stud such that the connective device is in electrical contact with the ground stud. In some embodiments the ground stud and the composite structure engage one another in a transition fit.

Abstract: A lightning protection system is provided, typically for use on an outer surface of an aircraft, which includes the use of a lightning protection sheet that includes an electrically conductive film patterned into a plurality of hill features. The lightning protection sheet may additionally include an electrically non-conductive discriminator layer over the electrically conductive film.

Abstract: Embodiments of the presently disclosed system include a thin thermoplastic or thermosetting polymer film loaded with non-polymeric inclusions that are susceptible to heating under a time-varying magnetic field. Insertion of this additional heating layer into a structural or semi-structural heterogeneous laminate provides an “on-demand” de-bonding site for laminate deconstruction. For example, in some embodiments when the heating layer is inserted between a cured Carbon-Fiber Reinforced Plastic (CFRP) layer and a Polymeric/Metallic film stackup layer, the heating layer can be selectively heated above its softening point (e.g., by using energy absorbed from a locally-applied time-varying magnetic field) to allow for ease of applique separation from the CFRP layer.

Abstract: A firing prevention structure of a fuel tank is provided with a double sleeve to pass through a hole formed in a rib, and a supporting structure to support a pipe to pass through the double sleeve. The supporting structure is attached to the rib. The supporting structure is provided with an insulating section which electrically insulates the pipe and the rib. The double sleeve is formed of electrically insulating material. Thus, an ignition source in the fuel tank is prevented.

Abstract: A blade for use in a gas turbine engine has an airfoil including a leading edge and a trailing edge. A sheath is positioned at the leading edge and secured to the airfoil by a first adhesive formed of a first material. The sheath is formed of a second material that is distinct from said first material. The first material is less electrically conductive than the second material. A grounding element is in contact with the sheath. The grounding element is in contact with a portion of the airfoil formed of a third material that is more electrically conductive than the first material. The grounding element and the portion of the airfoil together form a ground path from the sheath into the airfoil.

Abstract: A bonding lead comprising a core; and a sheath bonded to the core. The core comprises a substrate of fibers coated with nano-objects with at least one dimension between 1 nm and 200 nm. The nano-objects form a continuous electrically conductive network from one end of the bonding lead to the other with some of the nano-objects coating the fibers and others forming bridges between adjacent fibers. The nano-objects may be carbon nanotubes and the core may be woven or knitted. A conductive connector is provided at each end of the bonding lead, for instance a tab formed from an electrically conductive polymer. The lead can be used to dissipate static charge and/or lightning current between components, typically within an aircraft fuel tank.

Abstract: According to an embodiment a current return network assembly, for an aircraft having a predetermined potential lightning strike zone, is mounted within the predetermined potential lightning strike zone. The current return network assembly includes an electrically conductive honeycomb central core that conducts electrical current both through the assembly and through the predetermined potential lightning strike zone. The electrical current is caused by a lightning strike on the aircraft at the predetermined potential lightning strike zone. According to an embodiment, an aircraft has a predetermined potential lightning strike zone. A current return network assembly is within the zone. An electrically conductive honeycomb central core is provided for conducting electrical current through the assembly and through the zone wherein the electrical current has been caused by a lightning strike on the aircraft at the zone.

Abstract: A lightning protection system is provided, typically for use on an outer surface of an aircraft, which includes the use of a lightning protection sheet that includes an electrically conductive film and at least one patterned, electrically non-conductive discriminator layer.

Abstract: A method for reworking an electrically conductive layer of a composite skin is disclosed in which a patch replaces the altered section of the electrically conductive layer. The method is performed by removing a portion of the electrically conductive layer to reveal the underlying composite skin. A patch is formed, having an electrically conductive section coupled to an adhesive having a low dielectric breakdown strength, and is then introduced over the underlying composite skin such that the adhesive layer covers the underlying composite skin and overlaps an unremoved portion of the electrically conductive layer. The patch is applied such that the electrically conductive section within the patch covers the adhesive layer and overlaps the unremoved section of the electrically conductive layer. The adhesive layer preferably has a low dielectric breakdown strength, so that electricity from lightning which strikes the composite skin may be conducted through the adhesive.

Abstract: A lightning protection system is provided, typically for use on an outer surface of an aircraft, which includes the use of a lightning protection sheet that includes an electrically conductive film and at least one patterned, electrically non-conductive discriminator layer.

Abstract: The aircraft includes at least one piece of equipment and a composite material part to which the equipment is connected. It is arranged in such a manner that a fault current circuit of the equipment passes via the part.

Abstract: A lining/fairing panel, in particular a lining/fairing panel for an airborne vehicle such as an aircraft or a spacecraft is provided. The lining/fairing panel includes a panel body having a first surface and a second surface opposite to the first surface, an electrically conductive coating applied to the first surface or the second surface, and a via arranged in the panel body reaching from the first surface to the second surface of the panel body. The via is formed in an inner region of the panel body. The borders of the inner region are spaced apart by a predetermined distance from the borders of the first and second surface of the panel body.

Abstract: 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.

Abstract: A seal for attenuating energy from an electrical discharge across an interface may include a cover defining an inner volume containing a filled sealant including a semi-rigid sealant mixed with a filler having a multiplicity of discrete particles of different composition than the semi-rigid sealant such that the filled sealant is adjacent the interface when the cover is placed over said interface. A method for sealing an interface may include forming a cover defining an inner volume shaped to enclose the interface, forming a filled sealant including a semi-rigid sealant mixed with a filler having a multiplicity of discrete particles of different composition than said semi-rigid sealant, placing the filled sealant within said inner volume and placing the cover containing the filled sealant over the interface such that the filled sealant is adjacent the interface.

Abstract: The present disclosure is related to articles, such as aircraft windows and canopies, including a non-conductive substrate and a conductor pattern including one or more trace lines deposited onto the outside of the substrate such that the entire outside surface of the substrate is not coated with the conductor pattern. The present disclosure also provides methods of dissipating electrostatic charge from non-conductive substrates.

Abstract: A device (1) for the installation of a conducting component (2) on a structure (3) made from composite material, the inside of this structure (3) comprising a substance which can be ignited, which comprises an installation element (4) onto which the conducting component (2) is positioned, a conducting insert element (5), by means of which the installation element (4) is joined to the composite material structure (3) by its internal part, a conducting layer (6) arranged on the external part of the installation element (4) and a conducting fixing element (7) which joins the structure (3) and the installation element (4) to the insert element (5) and the conducting layer (6) so that the device (1) defines a low impedance current path through the conducting layer (6) and the insert element (5) through which the energy is dissipated from an atmospheric discharge to the component (2) or to the structure (3), the interior face of the structure (3) remaining isolated.

Abstract: In an insulating cover 50A according to the present invention, a dimension of each of an outer-circumferential-side cylindrical part 50c and an inner-circumferential-side cylindrical part 50b fitting in step parts 40 and 41 in an axial direction of a fastener body 25 is set large with respect to a tip covering part 50a covering a tip surface 26a of a fastening member 26. As a result, on an outer circumferential side and an inner circumferential side of the fastening member 26, a distance from a member 22 is sufficiently ensured by the cylindrical part 50b and 50c. The tip covering part 50a is thinner than the cylindrical part 50B and 50c. Therefore, when the fastener body 25 and the fastening member 26 are fastened together, the amount of deformation of the tip covering part 50a in a thickness direction can be made small.

Abstract: A system for dissipating a lightning current produced by a thunderstorm discharge on an avionic equipment installed on the external skin of an aircraft, the external skin being made of a composite material covered with a layer of expanded metal and including an orifice in which there is positioned an aerodynamic plate covering the avionic equipment. The aerodynamic plate is attached to the external skin by a doubler. The system includes at least one metal plate at least partially surrounding the aerodynamic plate and mounted so as to ensure electrical continuity between the doubler and the layer of expanded metal so as to dissipate the lightning current into the layer of expanded metal.

Abstract: A lightning strike protection system for protecting composite structures, an improved lightning strike appliqué (LSA) for such a lightning strike protection system, and a method of protecting composite structures, such as an aircraft fuselage. The LSA is electrically connected to adjacent conductive surfaces, e.g., by a fuzz button or a wire bond inserted in the bottom of the LSA. An adjacent conductive surface may be another LSA, a lightning diverter overlay, or a current return network. Charge, e.g., from a lightning strike to the LSA, flows to the conductive layer through the electrical connector.

Abstract: In the formation of a fiber reinforced composite material component produced by a resin transfer infusion process such as to have an electrically conductive surface layer for lightning strike protection wherein the component is to be drilled and countersunk to receive an electrically conductive fastener, a localized part of the electrically conductive mesh is deformed so as to be relocated in the countersunk recess thus to ensure electrical contact with the fastener when inserted and to eliminate any gap between the mesh and the fastener, thus determining the electrical conductive integrity of the mesh to avoid arcing in the event of lightning strike attachment.

Abstract: Fasteners are inserted into a stack of members and terminated with parts having at least one of a dry dielectric coating and an inner dry dielectric seal at select locations to protect against electromagnetic effects (EME).

Abstract: There is provided a lightning-resistant fastener that can secure sufficient lightning-resistance performance at low cost and realize efficiency of field work and improvement of reliability. An insulating coat film 40 is formed in a region opposed to a structural member 22 in a shaft section 25c of a fastener main body 25 and an insulating layer is interposed between the structural member 22 and the shaft section 25c of the fastener main body 25, whereby an electric current is fed along a head section 25b side of the fastener main body 25 and a wing panel 21 when lightning occurs. This suppresses the electric current from flowing to the front end portion side of the fastener main body 25, i.e., the interior side of a wing 20 and prevents arc discharge from occurring inside the wing 20.