Abstract: Carbon fiber reinforced plastic (“CFRP”) composite layups and processes for manufacturing CFRP composite layups that integrate z-conductivity features directly into CFRP composite layups during the manufacturing processes for lightning protection, more particularly, inherent edge glow protection from lightning direct effects, and electrical current flow path control. CFRP composite layups are configured during the manufacturing processes to provide inter-ply electrical connections between composite plies of the CFRP composite layups, therefore avoiding the need for add-on protection features that result in significant cost and weight penalties.

Abstract: A fastener includes an elongated shaft having a first end, a second end, and a shaft body, a head portion, and a threaded portion. At least one inner feed channel extends through the head portion and the shaft body and terminates proximal to the threaded portion. The fastener has a plurality of flutes formed along and circumferentially spaced around an outer surface of the shaft body and an outer surface of the head portion. Each flute has a first end and extends from a first location proximal to the threaded portion, along the outer surface of the shaft body, and radially outward along the outer surface of the head portion. The fastener further has one or more lateral feed channels formed laterally through the shaft body and connecting the inner feed channel to at least two opposing flutes on the outer surface of the shaft body.

Abstract: An aircraft component incorporated in a current return network (CRN) employs a composite structural element having a web. At least one flange is connected to the web. At least one metallic conductive layer is integrated with and extends the length of the web. The at least one metallic layer is configured to electrically bond to an aircraft system and provide a ground path.

Abstract: A system and method for testing a material system may include a support structure for mounting the material system, and a electromechanical device operably connected to the support structure, wherein the electromechanical device applies an electromechanical-induced force to the material system, and wherein the electromechanical-induced force causes a displacement in the material system equivalent to material displacement from thermal stress in significantly less time.

Abstract: A fastener for improved electrical contact with a composite structure and improved distribution of electric current to the composite structure. The fastener includes an elongated shaft having a first end with a head portion, a second end with a threaded portion, and a shaft body therebetween. At least one feed channel extends from an opening at the threaded portion, through the shaft body, and terminates proximal to the head portion. The shaft body radially expands upon pressure injection of a resin filler into the feed channel, when the fastener is installed in a corresponding fastener hole formed in the composite structure. Upon radially expanding, the outer surface of the shaft body makes contact with an inner hole surface of the corresponding fastener hole, resulting in the fastener providing electrical contact with the composite structure and providing distribution of electric current.

Abstract: A multilayer composite structure with integrated fastener-to-conductive layer surface lightning protection interconnection employs a conductive layer with an inner surface and a plurality of chamfered recesses forming countersinks in an outer surface. A carbon-fiber reinforced plastic (CFRP) composite layer is disposed on the inner surface of the conductive layer and conforms to the surface shape. A plurality of holes extend through the plurality of chamfered recesses in the conductive layer and the adjoining CFRP composite layer in a manner such that the conductive layer defines a countersink portion extending into the openings of the plurality of holes. The chamfered recesses in the conductive layer provides an electrically conductive surface area that contacts conductive countersunk fasteners installed within the plurality of holes to enable current sharing between groups of neighboring fasteners.

Abstract: An aircraft component incorporated in a current return network (CRN) employs a composite structural element having a web. At least one flange is connected to the web. At least one metallic conductive layer is integrated with and extends the length of the web. The at least one metallic layer is configured to electrically bond to an aircraft system and provide a ground path.

Abstract: A fastener for improved electrical contact with a composite structure and improved distribution of electric current to the composite structure. The fastener includes an elongated shaft having a first end with a head portion, a second end with a threaded portion, and a shaft body therebetween. At least one feed channel extends from an opening at the threaded portion, through the shaft body, and terminates proximal to the head portion. The shaft body radially expands upon pressure injection of a resin filler into the feed channel, when the fastener is installed in a corresponding fastener hole formed in the composite structure. Upon radially expanding, the outer surface of the shaft body makes contact with an inner hole surface of the corresponding fastener hole, resulting in the fastener providing electrical contact with the composite structure and providing distribution of electric current.

Abstract: A fastener includes an elongated shaft having a first end, a second end, and a shaft body, a head portion, and a threaded portion. At least one inner feed channel extends through the head portion and the shaft body and terminates proximal to the threaded portion. The fastener has a plurality of flutes formed along and circumferentially spaced around an outer surface of the shaft body and an outer surface of the head portion. Each flute has a first end and extends from a first location proximal to the threaded portion, along the outer surface of the shaft body, and radially outward along the outer surface of the head portion. The fastener further has one or more lateral feed channels formed laterally through the shaft body and connecting the inner feed channel to at least two opposing flutes on the outer surface of the shaft body.

Abstract: A multilayer composite structure with integrated fastener-to-conductive layer surface lightning protection interconnection employs a conductive layer with an inner surface and a plurality of chamfered recesses forming countersinks in an outer surface. A carbon-fiber reinforced plastic (CFRP) composite layer is disposed on the inner surface of the conductive layer and conforms to the surface shape. A plurality of holes extend through the plurality of chamfered recesses in the conductive layer and the adjoining CFRP composite layer in a manner such that the conductive layer defines a countersink portion extending into the openings of the plurality of holes. The chamfered recesses in the conductive layer provides an electrically conductive surface area that contacts conductive countersunk fasteners installed within the plurality of holes to enable current sharing between groups of neighboring fasteners.

Abstract: Carbon fiber reinforced plastic (“CFRP”) composite layups and processes for manufacturing CFRP composite layups that integrate z-conductivity features directly into CFRP composite layups during the manufacturing processes for lightning protection, more particularly, inherent edge glow protection from lightning direct effects, and electrical current flow path control. CFRP composite layups are configured during the manufacturing processes to provide inter-ply electrical connections between composite plies of the CFRP composite layups, therefore avoiding the need for add-on protection features that result in significant cost and weight penalties.

Abstract: Composite structures and methods for mitigating edge glow resulting from lightning strikes on composite structures, such as aerospace structures, containing carbon fiber reinforced plastic components. One or more thin layers of conductive coating material is applied over a cut edge or drop off of the carbon fiber reinforced plastic components to reduce inter-ply voltage potential between composite layers of the carbon fiber reinforced plastic component. The conductive coating material is made of a conductive doping material dispersed in a carrier medium.

Abstract: A system and method for testing a material system may include a support structure for mounting the material system, and a electromechanical device operably connected to the support structure, wherein the electromechanical device applies an electromechanical-induced force to the material system, and wherein the electromechanical-induced force causes a displacement in the material system equivalent to material displacement from thermal stress in significantly less time.

Abstract: A system comprises a structure having particles embedded at a level within the structure, and X-ray imaging apparatus for capturing images of the particles at the level.

Abstract: A device and method for monitoring the material health of a structure, providing a miniaturized MEMS Kelvin probe within a housing, wherein the Kelvin probe comprises a conductive plate formed of a stable metal and positioned substantially parallel to the structure; a piezoelectric vibrator for vibrating the conductive plate; and an electrical circuit connected to the conductive plate and the structure, wherein the conductive plate and the structure form a capacitor. The device is contained in one small, lightweight package that can be placed at one or more locations of interest. The sensor can be left in-place for continuous monitoring or for active testing at desired intervals, or be brought to the aircraft at desired intervals.

Abstract: A method and apparatus comprising a dielectric structure and a plurality of conductive segments. The dielectric structure is configured for placement in a waveguide. The plurality of conductive segments is located within the dielectric structure. Each of the plurality of conductive segments is configured to reduce a passing of a number of frequencies of electromagnetic signals traveling through the dielectric structure.

Abstract: A metamaterial has a magnetic permeability response at frequencies sufficient to generate a repulsive force between a fluid and a surface to which the metamaterial may be applied. The metamaterial may be nanofabricated such that an absolute value of the magnetic permeability of the metamaterial is substantially greater than an absolute value of an electric permittivity of the metamaterial. The metamaterial may generate a repulsive force between the surface and the fluid moving relative to the surface and thereby reduce viscous drag of the fluid on the surface. A method of reducing the viscous drag of the fluid moving past the surface includes producing relative motion between the surface and the fluid and generating the repulsive force between the surface and the fluid.

Abstract: In one embodiment, a system to detect one or more environmental conditions in proximity to a surface comprises a first metamaterial environmental sensor module proximate the surface. The environmental sensor comprises a metamaterial-based electrically resonant structure having a resonance frequency which varies in response to changes in at least one of a humidity proximate the sensor module, a temperature proximate the sensor module, or the presence of a chemical or biological agent proximate the sensor module. The system further comprises a remote receiver to receive an electromagnetic signal comprising the signal generated by the electrically resonant structure and a signal analysis module to determine an environmental condition such as humidity, temperature, pre-ice conditions, ice, chemicals or biological species from the at least one environmental condition signal. Other embodiments may be described.

Abstract: An electrically small antenna (ESA) for resolution of subwavelength features is disclosed. The ESA is on the order of meters and has an efficient transmit/receive capability. The ESA is 1/10 of the length of the equivalent dipole length, and may be scaled down to 1/10,000. The ESA includes a metamaterial shell. Such an antenna may include phase sensitive current injection in the metamaterial resonant structures for loss-compensation.

Abstract: A method and apparatus comprising a dielectric structure and a plurality of conductive segments. The dielectric structure is configured for placement in a waveguide. The plurality of conductive segments is located within the dielectric structure. Each of the plurality of conductive segments is configured to reduce a passing of a number of frequencies of electromagnetic signals traveling through the dielectric structure.