Systems and methods for mating component parts are described. In some embodiments, a system for mating components may include a first component, a second component, a first adhesive, and a second adhesive. The first adhesive may be configured to set in less than 5 minutes after the first component and the second component are placed in a mating position, and the second adhesive may require greater than 5 minutes to set. The first adhesive, after setting, may have sufficient strength to maintain the first component and the second component in the mating position while the second adhesive sets.

A system including two pre-fixed substrates, wherein a first substrate and a second substrate. Each of the substrates has an opening in an overlap region, and an adhesive is arranged between the overlap regions, wherein the adhesive connects the two substrates together and is arranged at least partly in the openings. The adhesive is locally cured in the region of the openings. A cured sub-region of the adhesive extends from the first opening into the second opening, and a second sub-region of the adhesive is not cured.

A method of manufacturing a metal-clad laminate and uses of the same are provided. The method comprises the following steps: (a) impregnating a reinforcement material with a first fluoropolymer solution, and drying the impregnated reinforcement material under a first temperature to obtain a first prepreg; (b) impregnating the first prepreg with a second fluoropolymer solution, and drying the impregnated first prepreg under a second temperature to obtain a second prepreg; and (c) laminating the second prepreg and a metal-clad to obtain a metal-clad laminate, wherein the first fluoropolymer solution has a first fluoropolymer, the second fluoropolymer solution has a second fluoropolymer, and the first fluoropolymer and the second fluoropolymer are different.

Methods and apparatus for performing repair operations using an unmanned aerial vehicle (UAV). A UAV carries a repair patch ensemble containing all repair materials (including a repair patch, a heating blanket and other ensemble materials) in a prepackaged form to the repair area. During flight of the UAV, the repair patch is vacuum adhered to the heating blanket. Vacuum pressure is also used to hold the repair patch ensemble in position on the composite surface of the structure. Then the hot bond process is enacted to bond the repair patch to the repair area. In accordance with one embodiment, the hot bond process involves heating the repair patch to adhesively bond the repair patch while applying vacuum pressure to consolidate the composite material. Then the repair patch is released from the ensemble and residual ensemble materials (heating blanket, bleeder material, and release films) are removed by the UAV.

Aspects of the present disclosure provide for composite structures including a bonding layer that adheres a substrate (e.g., including a polymeric composition such as rubber) to a material (e.g., including a polymer such as polyurethane). The adhesion of the substrate to the material through the bonding layer can include chemical bonds such as, but not limited to, siloxane linkages, silanol linkages, silyl linkages, or any combination thereof in the bonding layer.

Proposed is a method of manufacturing a piezoelectric composite material. The method includes the steps: wet mixing the ceramic powder, the polymer binder, the plasticizer, and the solvent for 4 to 72 hours to produce the mixed slurry, in which the amount of the polymer binder in the mixed slurry is 3 to 10 parts by weight, the amount of the plasticizer is 0.1 to 3 parts by weight, and the amount of the solvent is 30 or more to less than 50 parts by weight, based on 100 parts by weight of the ceramic powder in the mixed slurry; introducing the mixed slurry into a tape casting process to produce a piezoelectric composite sheet; drying and molding the piezoelectric composite sheet in a roll-to-roll process to form a molded piezoelectric composite sheet; laminating and compressing piezoelectric composite sheets molded to produce piezoelectric composite sheet laminates; and cutting the piezoelectric composite sheet laminate into the desired shape and size.

In one example, a method of preparing a fluidic channel includes covalently coupling a first region of a substrate to a first region of a cover using first moieties covalently coupled to the first region of the substrate and second moieties covalently coupled to the first region of the cover. The covalent coupling between the first region of the substrate and the first region of the cover suspends a second region of the cover over a second region of the substrate to form a fluidic channel.

Disclosed herein are a two-component polyurethane adhesive and a dual cure polyurethane-based adhesive for use in laminated films. The adhesives are particularly useful for producing photochromic and clear-to-polarized laminates for ophthalmic lens applications.

The invention relates to a composition for the layer-by-layer building of a three-dimensional article by sintering of the composition brought about by electromagnetic radiation, the composition comprising a semicrystalline thermoplastic polymer powder and at least one wax, the wax having a dropping point which is greater than the crystallization temperature of the semicrystalline thermoplastic polymer, said composition in addition optionally comprising a flow agent.

The invention also relates to a process for the preparation of said composition and also to its use for the layer-by-layer building of a three-dimensional article.

Methods of repairing damaged composites are described. The damaged composites can comprise a polymeric matrix and one or more layers of fibers (e.g., carbon or glass fibers). According to the described method, the damaged area of the composite is replaced by an insert comprising a core geometry and radial projections. The insert can comprise the same polymeric matrix and one or more layers of fibers as the original composite of the damaged composite. The method can provide a repaired composite with greater compressive strength and/or greater tensile strength than a composite repaired with a traditional patch having no radial projections.