A composite hat stringer for stiffening a panel includes a plurality of composite fabric plies arranged to form a cap, a pair of flanges and a pair of webs respectively connecting the cap with the pair of flanges. The cap includes at least one 0° composite tape ply interleafed in the composite fabric plies within the cap.

A panel is disclosed, including a first facesheet, a second face sheet, and a plurality of pultrusion-formed web structures. Each web structure has a middle support portion, a first end portion, and a second end portion. The first end portion of each web structure is attached to the first facesheet and the second end portion of each web structure is attached to the second facesheet. The middle support portion, first end portion, and second end portion of each web structure form a single monolithic structure.

The invention provides an integrated aircraft structure, such as a fuselage, with reinforcing elements in areas of the structure that need them because they have openings or are subjected to high loads. The structure comprises a skin, a plurality of stringers and a plurality of frames with mouseholes for the passage of stringers at their crossing zones. The reinforcing elements are configured with a suitable shape to be superimposed to the stringers in said areas. A manufacturing processes of said integrated aircraft structure is also provided.

A method and apparatus is presented. A layer of composite material is laid up on a forming tool. A bend is formed in the layer on the forming tool to form a bent layer. A laminate stack and the bent layer are assembled to form the composite filler.

A supporting profiled element is configured to support a reinforcing profiled element that is formed from a fiber composite semi-finished product during a curing process of a method for producing a vehicle fuselage component, during which the reinforcing profiled element is bonded to a surface of a fuselage shell that is also formed from a fiber composite semi-finished product. The supporting profiled element includes an air-impermeable profiled hose having two ends and a first end piece that is detachably inserted at a first of the two ends of the profiled hose so as to form an insertion connection. The first end piece is sealed against the profiled hose by the insertion connection.

Systems and methods for assembling a structurally reinforced composite structure are disclosed herein. The methods include deforming a composite tubular skin to a deformed conformation to generate clearance to permit a frame assembly to be conveyed into an internal volume that is defined by the composite tubular skin. The methods further include conveying the frame assembly into the internal volume, permitting the composite tubular skin to deform from the deformed conformation to the target conformation, and operatively attaching the frame assembly to the composite tubular skin to form the structurally reinforced composite structure. The systems include a frame support that is configured to support the frame assembly, a frame deformation assembly, a skin support that is configured to support the composite tubular skin, and a skin deformation assembly.

This structure is provided with a first composite material 11, a second composite material 12 joined to the first composite material 11 by a film adhesive 21 provided between the first composite material 11 and the second composite material 12, and a corner fillet part 13 provided on a corner part 15 formed by the first composite material 11 and the second composite material 12. The shape of the corner fillet part 13 is a design shape P designed in advance, and the corner fillet part 13 is formed by curing the film adhesive 21 after arranging the film adhesive 21 on the corner part 15 so as to fit into the design shape P.

A large scale composite structure is fabricated by forming a plurality of composite laminate modules and joining the modules together along their edges using scarf joints.

A composite structure includes a first composite material, a second composite material bonded to the first composite material, and a corner fillet part provided at a corner part formed by the first composite material and the second composite material. In the composite structure, the rigidity of the corner fillet part is adjustable, and a pull-off stress to be applied to the corner part is adjusted by adjusting the rigidity of the corner fillet part. The pull-off stress to be applied to the corner part is adjusted to be decreased by adjusting the rigidity of the corner fillet part to be decreased.

Presently disclosed systems and methods for depositing a compound into a void in a sandwich panel are configured to reduce the air pressure in and around the void as the compound flows into the void, thereby reducing the amount of air trapped between the compound and the sandwich panel skin within the void during the repair. Systems may include a dispenser for holding the compound, a vacuum canister, and a valve operable to allow the compound to flow from the dispenser, through at least a portion of the vacuum canister, and into the void. After the compound flows into the void, the system is configured to apply ambient air pressure to the compound and the void, before the compound is allowed to harden or cure. Some such systems are pre-filled with the compound, and/or configured to be disposable after a single use.