The invention relates to a load-bearing structure for automobiles and the like, including a chassis (2), a shell (3), a floorpan or other components, at least a part of which (13, 15, 16) is made by using composite honeycomb panels (20).

According to the invention, such panels (20) are provided with an external reinforcing layer (25, 26) made of a high-strength polymeric material such as carbon fiber, aramid fiber, fiberglass or the like.

The invention relates to a load-bearing structure for automobiles and the like, including a chassis (2), a shell (3), a floorpan or other components, at least a part of which (13, 15, 16) is made by using composite honeycomb panels (20).

According to the invention, such panels (20) are provided with an external reinforcing layer (25, 26) made of a high-strength polymeric material such as carbon fiber, aramid fiber, fiberglass or the like.

The present invention provides a tool 1 for curing a composite component, the tool comprising a lay-up surface 8 for laying-up layers of an uncured composite component, a cover assembly 9 for moving in relation to the lay-up surface to cover a layed-up uncured composite component on the lay-up surface, the cover assembly comprising a sealable cover for sealing around the uncured composite component on the lay-up surface to form a sealed zone, and a vacuum port 25 for providing a vacuum to the sealed zone, wherein the tool further comprises at least one heating element 15, 53 within the sealed zone for heating the uncured composite component. The invention also provides a method of manufacturing a composite component and a composite component. The composite component may form at least part of a piece of aircraft furniture, such as an aircraft seat shell.

A gas turbine casing made of composite material from fiber reinforcement densified by a matrix. The casing includes at least one stiffener portion extending at a radius greater than the radius of upstream and downstream portions of the casing that are adjacent to the stiffener portion so as to form an annular recess in the inside surface of the casing.

A gas turbine casing made of composite material from fiber reinforcement densified by a matrix. The casing includes at least one stiffener portion extending at a radius greater than the radius of upstream and downstream portions of the casing that are adjacent to the stiffener portion so as to form an annular recess in the inside surface of the casing.

Various components and methods related to a leading edge assembly are disclosed. The leading edge assembly can include an outer strike shell and a foam core. The foam core can be located inside the outer strike shell. The leading edge assembly can include a heating element with a plurality of sensors and wires. A method of manufacturing a leading edge assembly can include forming a composite layer, applying a metallic layer to the composite layer, installing an electronic device, and inserting a foam core into a cavity bounded by the composite layer and/or the electronic device.

A method for preparing a fully soft self-powered vibration sensor mainly uses a laser carbonization technology to prepare a two-dimensional porous carbon electrode with an origami structure, and then transfers the two-dimensional porous carbon electrode to a three-dimensional polydimethylsiloxane (PDMS) cavity through mold transfer; Finally, a laser engraving technology is used to create microstructures on surfaces of the porous carbon electrode and a PDMS film. The sensor includes the PDMS film, a liquid metal droplet oscillator, a porous out-of-plane carbon electrode, and a 3D PDMS cavity assembled tightly from top to bottom. The sensor works based on the triboelectric nanogenerator principle, when the sensor is excited by vibrations, contact and triboelectrification at an interface of the liquid metal droplet oscillator and PDMS film charge both objects, making contact surfaces carry stable charges, which allows the movement of the liquid metal droplet oscillator to output current through electrostatic induction.

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 fastening inclusion is provided and includes a hard point made of coalesced metal sheets, metal or fiber flanges extending from edges of the hard point, and a fastener arranged on the hard point. The fastening inclusion can be incorporated into a fiber reinforced polymer structure by interleaving the flanges with fiber reinforced resin plies, and then curing the fiber reinforced plies to form a composite structure. The fastener on the hard point may be used for mechanically connecting the composite structure to a separate component, such as a metal component on a vehicle.