An aerostructure is provided. The aerostructure may comprise an airfoil extending from a leading edge to a trailing edge, the airfoil comprising a stiffness and a camber, and a shape memory alloy (SMA) mechanically coupled to the airfoil via a resin, the SMA configured to be coupled to a current source, wherein at least one of the stiffness or the camber changes in response to a phase change of the SMA.

An aerostructure is provided. The aerostructure may comprise an airfoil extending from a leading edge to a trailing edge, the airfoil comprising a stiffness and a camber, and a shape memory alloy (SMA) mechanically coupled to the airfoil via a resin, the SMA configured to be coupled to a current source, wherein at least one of the stiffness or the camber changes in response to a phase change of the SMA.

A composite core material and methods for making same are disclosed herein. The composite core material comprises mineral filler discontinuous portions disposed in a continuous encapsulating resin. Further, the method for forming a composite core material comprises the steps of forming a mixture comprising mineral filler, an encapsulating prepolymer, and a polymerization catalyst; disposing the mixture onto a moving belt; and polymerizing said encapsulating prepolymer to form a composite core material comprising mineral filler discontinuous portions disposed in a continuous encapsulating resin.

A composite core material and methods for making same are disclosed herein. The composite core material comprises mineral filler discontinuous portions disposed in a continuous encapsulating resin. Further, the method for forming a composite core material comprises the steps of forming a mixture comprising mineral filler, an encapsulating prepolymer, and a polymerization catalyst; disposing the mixture onto a moving belt; and polymerizing said encapsulating prepolymer to form a composite core material comprising mineral filler discontinuous portions disposed in a continuous encapsulating resin.

A method for manufacturing a structural component of a blade segment for a rotor blade includes providing a mold of the structural component having an outer wall that defines an outer surface of the structural component. The method also includes laying up one or more fiber layers in the mold so as to at least partially cover the outer wall. As such, the fiber layer(s) form the outer surface of the structural component. Further, the method includes providing one or more metal mesh layers having one or more ends. Moreover, the method includes providing a cover material to the end(s) of the metal mesh layer(s). In addition, the method includes placing the metal mesh layer(s) with the covered end(s) atop the fiber layer(s). Thus, the method includes infusing the fiber layer(s) and the metal mesh layer(s) together via a resin material so as to form the structural component.

A motor vehicle component with a lighting function includes a laminate component having a first fiber-reinforced composite material and a second fiber-reinforced composite material, the first fiber-reinforced composite material being electrically insulating and the second fiber-reinforced composite material being electrically conductive. The motor vehicle component also includes a light source which is at least partially embedded in the first fiber-reinforced composite material. The light source is electrically conductively connected to the second fiber-reinforced composite material, and the second fiber-reinforced composite material has a light exit region from which light emitted by the light source can exit so that it can be seen from outside the motor vehicle component.

A method of manufacturing a product including at least two carbon parts including the step of: manufacturing a first carbon part, manufacturing at least a second carbon part, providing on a surface of one of the first carbon part or second carbon part a plurality of protrusions including a carbon resin, joining together the first carbon part and the second carbon part in such a way that the plurality of protrusions is interposed between the first carbon part and second carbon part for providing physical and electrical connection is provided.

A liner for a crisp plate includes ceramic nanoparticles and a polymer material combined with the ceramic nanoparticles to provide a mixture. A network of carbon nanotubes is embedded within the mixture to form a composite matrix, wherein the carbon nanotubes are unidirectionally aligned within the composite matrix.

Methods of manufacturing multi-material fibers having one or more electrically-connectable devices disposed therein are described. In certain instances, the methods include the steps of: positioning the electrically-connectable device(s) within a corresponding pocket provided in a preform material; positioning a first electrical conductor longitudinally within a first conduit provided in the preform material; and drawing the multi-material fiber by causing the preform material to flow, such that the first electrical conductor extends within the multi-material fiber along a longitudinal axis thereof and makes an electrical contact with a first electrode located on each electrically-connectable device. A metallurgical bond may be formed between the first electrical conductor and the first electrode while drawing the multi-material fiber and/or, after drawing the multi-material fiber, the first electrical conductor may be located substantially along a neutral axis of the multi-material fiber.

A heat-conducting sheet (10) has a plurality of unit layers (13) each containing a silicone resin (11) wherein the plurality of unit layers (13) are laminated so as to be adhered with each other, wherein among the plurality of unit layers (13), at least one thereof contains a heat-conducting filler, and the compression ratio of the heat-conducting sheet when being compressed at 0.276 MPa is 20 to 65%.