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.

A joint structure includes a reinforcement portion that is formed by joining a composite material and a reinforcing material through an adhesive. The composite material includes a plate portion that is formed by laminating a plurality of fiber sheets, and a raised portion that is formed by laminating a plurality of fiber sheets in addition to the plurality of fiber sheets of the plate portion, and surfaces of the plate portion and the raised portion are covered with a single fiber sheet. The reinforcement portion includes the raised portion and the reinforcing material that is bonded to the raised portion through an adhesive. A first boundary between the plate portion and the raised portion and a second boundary between the raised portion and the reinforcing material are located at different positions in an in-plane direction of a laminated interface between the fiber sheets that are laminated.

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.

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.

A mat unit is formed from at least two layers ultrasonically welded together. Each layer is individually formed from non-vinyl nontoxic thermoplastic elastomer (TPE) material. In ultrasonically joining the two layers together, there is no need to use additional materials, such as adhesive (i.e., chemical attachment) or stitched thread (i.e., mechanical attachment) to form the joint/weld point. Once formed from the two layers, the mat unit has four quadrants and a plurality of longitudinal ribs integrally formed in the first layer positioned in the first and third quadrants, and a plurality of transverse ribs integrally formed in the first layer positioned in the second and fourth quadrants. Additionally, there are a plurality of longitudinal ribs integrally formed in the second layer positioned in the second and fourth quadrants, and a plurality of transverse ribs integrally formed in the second layer positioned in the first and third quadrants.

Aspects of the disclosure relate to manufacturing a balloon envelope for use in a stratospheric balloon system. For instance, a stream of polyethylene mixture us extruded. through an extruder in order to orient molecules of polymer chains of polyethylene and to provide an oriented film. The oriented film is passed through an electron beam and thereby crosslinking the polymer chains to provide a cross-linked film. The cross-linked film is heat sealed to form the balloon envelope

A method for making a gas-tight container (1) in elastomeric material comprises: providing two or more separate elastomeric portions (2, 3), cleaning and/or roughening the gluing surfaces (6) of the gluing edges (5), applying an adhesive (7) onto the previously cleaned, degreased and/or roughened gluing surfaces (6), assembling the portions (2, 3) to form the container (1) and inserting between the gluing surfaces (6) a raw elastomeric tape (8) not yet cured, applying a cold pressure on the overlapped gluing edges (5), heating the overlapped gluing edges (5) to thermally activate the curing of the raw tape (8), cooling the gluing areas.

Mechanically attaching articles made from composites has problems due to the difference in properties of the composite in the x, y planar direction and the z perpendicular direction, this results in different properties between the composite and the attachment member such as differences in coefficients of thermal expansion which can weaken the joint further leading to differences in moisture uptake which can further reduce the strength and robustness of the joint. The invention relates to the selection of the position of a joint in order to reduce such problems and to operating the moulding process in a way that improves the provision of mechanical attachments such as bolt holes.

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.

A stiffened part formed from at least two members of thermoset composite material including at least one body of a first structure and optionally a second structure. A manufacturing method includes: forming a fibre preform and impregnating each body of the first structure with thermosetting resin or forming a pre-impregnated fibre preform to obtain a body formed from uncured thermosetting composite material supported by a mandrel; optionally partially or fully polymerising at least one body supported by a mandrel; optionally, providing the second structure formed from uncured, partially uncured or fully uncured thermosetting composite material; optionally, depositing a layer of uncured thermosetting adhesive on an area where a fully cured member makes contact with another member of the part; joining the members, each member being juxtaposed with; or stacked upon, at least one other member; fully curing the assembly by heat treatment; removing the mandrel from each fully cured body.