The invention relates to a method for applying a material (30) to a fiber composite component within an application region (13) of the fiber composite component, the fiber composite component being produced from a fiber composite material having a fiber material (11) and a matrix material (12), the method comprising the following steps: providing at least one monofilament woven fabric (20), in which a plurality of or all threads each consist of a single filament, arranging the at least one monofilament woven fabric (20) on a fiber preform (10) in the application region (13), which fiber preform is formed from the fiber material (11) of the fiber composite material, curing, in a common process step, the matrix material (12) of the fiber composite material, which matrix material embeds the fibers material (11) of the fiber preform (10), and a matrix material (12) embedding the monofilament woven fabric (20), thereafter the matrix material (12) of the fiber preform (10) and the matrix material (12) of the monofilament woven fabric (20) being at least partially cured, tearing off the monofilament woven fabric (20) integrally bonded to the fiber preform (10), andapplying the material (30) in the application region (13) after the monofilament woven fabric (20) has been torn off.

A method for producing a circuit board includes a first step of arranging a circuit alignment jig having a pierced portion for receiving a circuit conductor corresponding to a circuit pattern on an insulating layer formed on a metal substrate, a second step is inserting the circuit conductor into the pierced portion, and a third step is pressing the circuit conductor to the insulating layer together with the circuit alignment jig.

Aspects of the present disclosure are directed to a three-dimensional joint and/or formation thereof, such as by 3D-printing the joint. The joint is provided with an interface region having a curable material in a curable state. The joint is positioned with the interface region in contact with a joinable member, and the interface region is cured to form a bond between the joint and the joinable member. Such an approach may, for example, involve forming a mechanical and/or chemical bond with the joint. Further, by utilizing such a joint (e.g., in a 3D-printed form), complex structural components can be formed from a curable material that can be partially cured with structures formed therein, and cured further to create the bond.

The disclosure relates to a component device, in particular for a primary supporting component of an aircraft, which comprises a first component element, a second component element, a bonding providing a connection between the first component element and the second component element, a marker substance device configured to dispense a volatile marker gas to the environment when in contact with the surrounding air and being hermetically sealed from the surrounding air by the first component element, the second component element, and/or the bonding if the bonding is not damaged, and a detector device configured to detect the marker gas dispensed by the marker substance device.

The invention relates to a method for the application of heating mats (10) on a wing/blade of a wind power station or other devices for the purpose of achieving deicing also during operation when necessary. Temperature measurement and de-icing take place by means of pulsed current to the heating mat (10). The invention also relates to an arrangement.

A part made of a fiber-reinforced composite material includes a structure made from a set of fibers supported in a thermosetting resin and a peel ply across all or part of the outer surface of the structure. The part has a gradient of polymerization at the interface between the structure and the peel ply. Also, methods for making such a part and methods for bonding such parts.

Methods of co-bonding a first thermoset composite (TSC) and a second TSC to define a cured composite part are disclosed herein. The methods include partially curing the first TSC to a target state of cure (SOC) to define a first partially cured TSC. The partially curing is based, at least in part, on a maximum temperature of the first TSC during the partially curing and on an elapsed time that an actual temperature of the first TSC is greater than a threshold temperature. The methods further include combining the first partially cured TSC with the second TSC to define a partially cured TSC assembly and heating the partially cured TSC assembly to bond the first partially cured TSC to the second TSC, cure the partially cured TSC assembly, and produce a cured composite part.

A hinged component includes first and second portions of material coupled together by a composite live hinge. The live hinge includes a layer of tensile fabric and a layer of elastomer interposed between the tensile fabric and the material of one or both of the coupled first and second portions. The composite live hinge is capable of joining structural composite materials without the need for scoring, and thereby weakening, the structural composite material along the desired hinge line. The live hinge can be embedded in the materials it joins in a method that is compatible with traditional structural composite layup processes and in a manner which prevents resin from the structural composite materials from infiltrating the tensile fabric and compromising its flexibility.

A method of manufacturing a hollow composite structure is provided. The method includes forming a first portion of the hollow composite structure having at least one open region and at least one wall, the at least one wall partially defining a hollow interior. The method also includes bonding a laminate shell to the first portion of the hollow composite structure proximate to at least one location of the wall to cover the open region and enclose the hollow interior. The method further includes disposing a second portion of the hollow composite structure over the laminate shell, the second portion comprising a plurality of plies. The method yet further includes curing the first portion and the second portion during a final cure.

A method for coupling a tube to a tube fitting includes radially outwardly expanding a tubular compression collar from a constricted state to an expanded state, the compression collar having a throughway extending there through and being made of a resiliently flexible material. An end of the tube is inserted within the throughway of the expanded compression collar, the tube bounding a passage. A tube fitting is inserted within the passage of the tube. The compression collar is allowed to resiliently rebound back towards the constricted state so that the compression collar pushes the tube against the tube fitting.