The invention relates to a method for connecting two fibre-reinforced plastic components, comprising the following steps: producing a first fibre-reinforced plastic component, wherein a fabric made of fibrous matting is provided, which is impregnated with a resin-curing agent mixture, which is then subsequently cured, wherein the part of the surface of the first fibre-reinforced plastic component, which is to be later adhered to the second fibre-reinforced plastic component (hereinafter also referred to as joining surface), is masked with an adhesive strip before the impregnation of the fibrous matting with the resin-curing agent mixture; producing a second fibre-reinforced plastic component using the above steps, wherein the part of the surface of the second fibre-reinforced plastic component, which is to be later adhered to the first fibre-reinforced plastic component, is also masked with an adhesive strip before the impregnation of the fibrous matting with the resin-curing agent mixture; removing the adhesive strips from the two finished fibre-reinforced plastic components; bringing the two joining surfaces in contact; introducing a resin-curing agent mixture between the two joining surfaces; curing the resin-curing agent mixture, wherein the adhesive strip has a carrier film, on one side of which an adhesive mass, in particular self-adhesive mass is applied, and wherein the carrier film consists of fluoropolymers, polyethylene polymers, undrawn polypropylenes or of metal, and the adhesive mass is an acrylate or silicon adhesive mass.

A method for plasma treating a surface of a first substrate is disclosed. The method may comprise generating a plasma flume using a plasma treatment device having a nozzle. The plasma flume may emanate through a flume aperture of the nozzle at an emanation angle of about 5 degrees or less. The emanation angle may be defined as an angle between a central axis of the nozzle and a central axis of the flume aperture. The method may further comprise plasma treating the surface of the first substrate with the plasma flume by scanning the plasma flume over the surface of the first substrate. The first substrate may be one of a consolidated thermoplastic material and a cured thermoset material.

A method is provided in one example embodiment and may include assembling a first component and a second component together using, at least in part, a first adhesive film on the first component and a second adhesive film on the second component, wherein the first component and the second component are fully cured and the first adhesive film and the second adhesive film are at least partially uncured; and curing the first adhesive film and the second adhesive film to form a bonded structure.

A mat unit includes a plurality of gaps defined by a first layer that are in open communication with gaps defined by a second layer so as to permit debris to fall entirely through both gaps to pass completely through the mat unit. The mat unit is part of an omnidirectional mat cleaning system that includes a first direction of travel above the mat unit extending through a door opening defined by a building structure. A different second direction of travel is above the mat unit extending through the door opening or another door opening defined by the building structure. The mat unit is installed on a floor adjacent the door opening. The mat unit cleans shoes regardless of the direction of travel traveled above the mat unit.

A method for manufacturing a tool including assembling a stack-up that includes a plurality of precured composite laminates, the stack-up having an engagement surface, wherein each precured composite laminate of the plurality of precured composite laminates is flexible, and wherein an adhesive is positioned between adjacent precured composite laminates of the plurality of precured composite laminates, and placing the engagement surface of the stack-up onto a target surface of a substrate.

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.

A vehicle component is provided that includes a first cured layer of a molding composition having a predominant fiber filler chopped glass fibers, a second cured layer of molding composition having a predominant fiber filler chopped carbon fibers, and an elastomeric bonding agent with elongation properties configured to accommodate the differential coefficients of linear thermal expansion between the first cured layer and the second cured layer. The second cured layer is substantially devoid of glass fiber. The bonding agent is an elastomeric adhesive, which is operative from 40 to 205 C. The first cured layer forms an outer skin layer surface of a vehicle and the second cured layer forms an interior layer, where the outer skin layer surface has a class-A finish.

Provided herein is a spar cap having a profile for guiding and receiving a shear web for wind turbine blade. Particularly, the present disclosure provides a pultruded spar cap having a bond gap feature to maintain a uniform space for distribution of bonding paste between the spar cap and shear web. Also, the spar cap is formed with locating features which guide and receive placement of the shear web.

A cascade array includes a first strongback having a first thermoset or thermoplastic composite material. The cascade array further includes a second strongback having a second thermoset or thermoplastic composite material. The cascade array further includes a first vane that is coupled to the first strongback and the second strongback and includes a third thermoset or thermoplastic composite material.

Embodiments are directed to systems and methods for two or more cured composite assemblies that are bonded together to form a tubular composite structure, wherein each of the cured composite assemblies do not have a tubular shape. The tubular composite structure may form a spar for an aerodynamic component, for example. The two or more cured composite assemblies may comprise carbon or fiberglass composite materials or a combination of materials. Each of the cured composite assemblies may further comprise axial edges that are configured to be bonded to another of the cured composite assemblies, wherein the axial edges have a sloped shape. An adhesive agent may be applied on the axial edges for bonding two cured composite assemblies. Alternatively, or additionally, one or more fasteners may be used to attach the axial edges of at least two cured composite assemblies.