Composite components having a T or L-shaped configuration that include features that reduce void defects between abutting laminate portions and provide improved mechanical properties are provided. Methods for forming such components are also provided. In one exemplary aspect, a composite component defines a first direction and a second direction and includes a wedged-shaped noodle at a joint interface between an abutting first laminate portion extending along the first direction and a second laminate portion extending along the second direction. The noodle has a first surface that is angled with respect to the second direction. At least one of the plies of the second laminate portion terminate and attach to the angled first surface of the noodle.

A method and apparatus for fabricating a composite structure. The method comprises defining a shape for the composite structure with a first face sheet. The method places core sections on the shape defined by the first face sheet. The method places an adhesive in a group of joint cavities. The method places a second face sheet on the core sections placed on the first face sheet, wherein the first face sheet, the core sections, and the second face sheet, define a structural assembly in which the group of joint cavities are present. The method cures the structural assembly with the adhesive in the group of joint cavities to fabricate the composite structure in which the adhesive fills the group of joint cavities when the adhesive is cured.

A method for connecting components having a fibre-reinforced thermoplastic plastic includes provision of a first component with a first joining surface, provision of a second component with a second joining surface, flush placement of the first joining surface against the second joining surface in order to form a connection joint, placement of a friction stir welding tool against the connection joint, or a surface directly adjacent thereto, of at least one of the components, softening of the first component and the second component, in each case in a region adjacent to the connection joint, by rotation of the tool, such that the thermoplastic plastic of the two components locally fuses, and movement of the tool along the connection joint for the purposes of connecting the two components by formation of a fusion seam, wherein portions of reinforcement fibres are stirred in to increase the strength of the fusion seam.

A composite radius filler material is provided. The composite radius filler includes a resin, a first group of fibers dispersed within the resin, and a second group of fibers dispersed within the resin. The first group of fibers has a first length configured to facilitate orientation in a longitudinal direction. The second group of fibers has a second length that is shorter than the first length, with the second group of fibers configured to facilitate random orientation in a transverse direction.

Aspects of the present disclosure are directed to a three-dimensional joint and/or formation thereof, such as by 3D-printing the joint. The joint is provided with an interface region having a curable material in a curable state. The joint is positioned with the interface region in contact with a joinable member, and the interface region is cured to form a bond between the joint and the joinable member. Such an approach may, for example, involve forming a mechanical and/or chemical bond with the joint. Further, by utilizing such a joint (e.g., in a 3D-printed form), complex structural components can be formed from a curable material that can be partially cured with structures formed therein, and cured further to create the bond.

Systems and methods are provided for blade-and-slot panel affixation. One embodiment is a method. The method includes cutting a first slot into a first composite panel that includes a core between two facesheets. The first slot penetrates through the core of the first composite panel. The method also includes cutting a second slot into a second composite panel that includes a core between two facesheets. The second slot penetrates through a facesheet of the second composite panel as well as the core of the second composite panel. The method further includes inserting a blade into the first slot, and inserting the blade into the second slot.

An assembly, configured in particular in the form of an aircraft assembly, comprises a plurality of individual components composed of a fibre-reinforced composite material. An edge section of at least one individual component is sealed by means of a sealing tape which contains reinforcing fibres and a curable plastics material.

A method for curing an adhesive composition includes: arranging an adhesive composition that transmits laser light of a first wavelength in contact with a surface of a first adherend that contains, at least at its surface, a first light-to-heat conversion material that generates heat by absorbing laser light of the first wavelength; and curing the adhesive composition by irradiating the adhesive composition and the first adherend with laser light of the first wavelength. In a method for manufacturing a bonded structure, a first bonded structure is manufactured by bonding the adhesive composition to the first adherend by using the method for curing an adhesive composition.

Systems and methods for non-destructive inspection of curved composite laminate structures using interface guided waves. In particular, if the curved composite laminate structure has a noodle, then the noodle area may be inspected using interface guided waves. The systems and methods provide a repeatable and reliable nondestructive technique for monitoring the structural health of the noodle area of an adhesively bonded curved composite laminate structure by comparing detection data acquired from an inspected curved composite laminate structure with prediction data derived using a simulated curved composite laminate structure.

A bonder and a method for bonding corrugated sidewalls to a thermoplastic belt at a splice joint. Two heating jaw assemblies with complementary and confronting corrugated vertical faces clamp a thermoplastic belt to a base of the bonder with a corrugated sidewall section separated from the belt across a splice joint received in a corrugated slot formed between the confronting vertical faces. Corrugated bonding strips at the bottoms of the corrugated vertical faces apply heat to melt the bottom of the sidewall section on opposite sides to bond the corrugated sidewall section to the base.