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 joining method is provided during which a first thermoplastic component joint section and a second thermoplastic component joint section are arranged between first tooling and second tooling. The second thermoplastic component joint section is abutted against the first thermoplastic component joint section at a joint area. The first thermoplastic component joint section is joined to the second thermoplastic component joint section to provide a unitized thermoplastic structure. The joining includes: pressing the first thermoplastic component joint section against the second thermoplastic component joint section at the joint area between the first tooling and the second tooling using a pressure device; and heating the first thermoplastic component joint section and the second thermoplastic component joint section at the joint area using a first heater configured with the first tooling. The unitized thermoplastic structure is cooled at the joint area using a first cooler configured with the first tooling.

Disclosed are embodiments of a volume control storage bag and methods of making same. The volume control storage bag may have first and second sidewalls, a double-locking closure mechanism with a first closure element extending along the first sidewall and a second closure element extending along the second sidewall, each closure element having a channel and an elongated member configured for interlocking with one another. A gusset is sealed along three sides of the first and second sidewalls, leaving an opening through the closure mechanism and defining an interior space having a specific volume. Corner seals may be formed at the corners of the first and second sidewalls, further reinforcing the double-locking closure mechanism for an airtight and hence waterproof seal. The volume control storage bag may be made of a food-grade polyethylene vinyl acetate blend, approximately 90% or less ethylene vinyl acetate and approximately 10% or less polyethylene.

A device and a method for manufacturing a rotor blade for a wind energy installation, wherein the rotor blade includes at least two rotor blade shells which are bonded together, includes a holding device arranged to hold a rotor blade shell such that at least one bonding surface on the rotor blade shell and/or on a web attached to the rotor blade shell is exposed. The bonding surface of the rotor blade shell can be bonded to a further rotor blade shell. The device further includes a robot arm arranged to apply adhesive to the at least one bonding surface, a carriage on which the robot arm is mounted, and a guide device mounted on the holding device. The carriage is mounted on the guide device so as to be movable. The guide device is arranged to guide the carriage and the robot arm along the holding device, in particular along the bonding surface.

A first thermoplastic component and a second thermoplastic component including a first joint portion and a second joint portion, respectively, are provided. A least a portion of a surface area of each of the first and second joint portions include a respective first and second mating surface. The first and second mating surfaces of the respective first and second joint portions are positioned in contact with one another. The first and second joint portions are fusion joined. Fusion joining the first and second joint portions forms a fused unitary portion of the first and second thermoplastic components.

A method for joining two substantially planar fiber-composite structural components, includes stacking the two components on a support jig to overlap along a joining region. A lower component end section within the joining region borders a gap between the upper component and the jig, where the upper component is unsupported by the jig. The gap is bordered on an opposite side of the lower component end section by a filling portion of the upper component or a planar filler element supported by the jig. The lower component is joined to the upper component within the joining region by applying temperature and pressure to the components. A width of the gap allows the upper component to elastically deform along the gap under the pressure and bend down into the gap to abut the jig along the gap and thereby compensate thickness tolerances between the components during the pressure application.

Systems and methods for assembling elongate composite structures are disclosed. The systems include a first rigid elongate cure tool defining a first elongate support surface for supporting a first elongate charge of composite material (FEC), a second rigid elongate cure tool defining a second elongate support surface for supporting a second elongate charge of composite material (SEC), and a flexible elongate caul plate. The systems further include a vacuum compaction film, a translation structure, and a vacuum source. Methods according to the present disclosure include positioning a vacuum compaction film, positioning a flexible elongate caul plate, and positioning an FEC. The methods further include positioning an SEC, contacting a region of the FEC with a region of the SEC, sealing the vacuum compaction film, evacuating the enclosed volume to generate an elongate composite assembly, and heating the elongate composite assembly to define the elongate composite structure.

A fuselage structure of an aircraft includes a fuselage skin, and a plurality of frame elements spaced apart from one another in a direction parallel to the aircraft longitudinal axis for supporting the fuselage skin. The fuselage skin includes a plurality of interconnected fiber-reinforced composite skin panels that extend between each pair of frame elements and are connected thereto. The composite skin panels further comprise a stiffener integrally formed in each composite skin panel. A method for manufacturing the fuselage skin. The composite skin panels may be interconnected and/or connected to a frame element through an induction welded connection.

A method for fusing thermoplastic composite structures includes placing a substructure on an inner surface of a skin that is laid up on a shaping surface of a tool configured to maintain the shape of an outer mold line. The method further includes applying at least one insulation layer over a flange of the substructure and over exposed portions of the inner surface of the skin not in contact with the substructure, and applying a vacuum bag to at least partly enclose the skin and the substructure. The method yet still further includes applying heat to the shaping surface to fuse the substructure to the skin such that the skin exceeds its melting point and at least a portion of a raised segment of the substructure does not exceed its melting point.

Provided is a moving handrail that can lengthen its lifetime. The moving handrail includes: a handrail main body portion; a fabric arranged on a guide surface of the handrail main body portion and extending in a handrail longitudinal direction; and a resin sheet arranged on the fabric so that the fabric is sandwiched between the handrail main body portion and the resin sheet, wherein a surface of the fabric facing a handrail guide has arranged thereon an end portion of the fabric in the handrail longitudinal direction, and wherein the end portion of the fabric in the handrail longitudinal direction is covered with the resin sheet.