A method for bonding two elements, the method including receiving first and second elements, the first element being a composite material; applying a laser-based treatment to a surface of the first element to obtain a treated surface; patterning the treated surface to have plural trenches; applying an adhesive to one of the first and second elements; and joining the first element to the second element so that the adhesive is between the first and second elements.

The invention relates to a process (100) for manufacturing an object (1) made of thermoplastic polymer composite from at least two parts (10) made of thermoplastic polymer composite, said thermoplastic polymer composite comprising a fibrous reinforcement and a thermoplastic polymer matrix, said process comprising the steps of: arranging (120) the two parts (10) made of thermoplastic polymer composite adjacently or overlapping at an assembly interface zone (11), and heating (130) to melt the thermoplastic polymer matrix at said assembly interface zone (11), so as to form an object (1) made of thermoplastic polymer composite comprising a welded interface (12).

A method for bonding composite substrates includes coupling a first co-cure prepreg layer having a first off-set amine to epoxide molar ratio onto a surface of a first composite substrate and coupling a second co-cure prepreg layer having a second off-set amine to epoxide molar ratio onto a surface of a second composite substrate. The first and second composite substrates are cured to the first and second co-cure prepreg layers, respectively, using a first cure cycle (including B-stage and cure temperatures) to form a first and a second co-cure prepreg layer portion. The method further includes coupling the first co-cure prepreg layer portion to the second co-cure prepreg layer portion and applying a second cure cycle to cure the first co-cure prepreg layer portion of the first composite substrate to the second co-cure prepreg layer portion of the second composite substrate to form a monolithic covalently bonded composite structure.

Systems and methods are described for applying a self-heating structural adhesive to components of aircraft or other structures. A conductive scrim can be placed in between layers of adhesive for use in joining two components together. Leads can be provided to apply an electrical current to the scrim, which can raise the temperature of the system and cure the adhesives, creating a strong bond with a conductive layer there between.

A method for creating a termination by attaching some kind of fitting to the end of a tensile member such as a cable. The end fitting is provided with an internal cavity. The cavity has a proximal portion that is adjacent to the area where the tensile member exits the fitting and a distal portion on its opposite end. A length of the tensile member's filaments is placed within this expanding cavity and infused with liquid potting compound. The method exploits the characteristic of a liquid potting compound as it transitions to a solid. The potting compound in one portion of the cavity is typically transitioned to a solid at a more rapid rate than other portions. Once the potting compound in one portion of the cavity has transitioned sufficiently to hold the filaments at the desired level, tension is placed on the tensile member and a small linear displacement may be imposed on the tensile member. This linear displacement tends to pull the filaments residing in the potting compound into better alignment and improve load sharing.

A composite material is formed by irradiating a bonding position on a surface of the composite material with a laser to cause a reinforcing base member of the composite material, that is impregnated with a resin and onto which a bonding agent is applied, to be exposed and fluffed.

An assembly of two parts, one of the parts being made of composite material with fiber reinforcement obtained from a fiber preform made by three-dimensional weaving and densified with a matrix, the assembly including a mechanical anchor element secured to one of the parts and inserted inside the other part.

A probe includes an elastic element having first and second ends, a transmitter, one or more receiving antennas and one or more narrow-band amplifiers. The transmitter is coupled to the first end and is configured to transmit signals in a given range of frequencies. The one or more receiving antennas are coupled to the second end and are configured to receive the signals. The one or more narrow-band amplifiers have a pass-band that matches the given range of frequencies and are configured to amplify the signals received by the one or more receiving antennas, respectively.

Disclosed is a method for producing components from fiber-reinforced thermoplastic. The method involves manufacturing a multitude of semifinished products, each of which includes a plurality of impregnated fabric layers that are joined to one another only locally, as well as a frame structure having at least one cutout. The semifinished products are consolidated using a consolidation device, an inlay element being placed in each cutout before the semifinished products are consolidated.

The present invention relates to a wind turbine blade and a method for its manufacture. A lower shell part and an upper shell part are provided, each shell part having a leading edge and a trailing edge. A first shear web and a second shear web for connecting an inner surface of the lower shell part with an inner surface of the upper shell part are provided. The first shear web and the second shear web are connected by a first distance member in a chordwise direction. The first distance member is arranged for accommodating a variable chordwise distance between said first shear web and said second shear web. The first shear web and the second shear web are placed in the lower shell part and the upper shell part is mounted.