Abstract: The disclosure proposes a method for producing a panel having an outer skin and stiffeners that have a connecting portion, and at least one projecting portion, the method comprising a step of draping layers of fibers over at least one insert such that each layer of fibers has a connecting portion and a portion that projects downwardly from the connecting portion, a step of draping a layer of fibers that forms the outer skin, and a step of bonding the layers of fibers together. The disclosure also provides a device for implementing the method.

Abstract: A method for producing a central wing box having an upper panel, a lower panel, a front spar and a rear spar, the upper edges of said spars approximately parallel to an axis Y being connected by the upper panel, and the lower edges of said spars approximately parallel to the axis Y being connected by the lower panel. The method includes producing at least one panel and at least one spar from composite material in one piece.

Abstract: The disclosure proposes a method for producing a panel having an outer skin and stiffeners that have a connecting portion, and at least one projecting portion, the method comprising a step of draping layers of fibers over at least one insert such that each layer of fibers has a connecting portion and a portion that projects downwardly from the connecting portion, a step of draping a layer of fibers that forms the outer skin, and a step of bonding the layers of fibers together. The disclosure also provides a device for implementing the method.

Abstract: The invention relates to an automated device for implementing a drape-forming step to form a laminated fibrous preform, which is then impregnated with resin to produce a part made of composite material. The invention relates more particularly to the production of preforms for manufacturing parts such as panels, in particular very thick panels, that extend basically in two dimensions. The device of the invention comprises a manipulator able to move and orient in space a tape laying head, said tape laying head comprising: a drum comprising a suction orifice leading to its surface and able to individually grasp a length of fabric on a mounting outside the tool and the tape laying head; means designed to subsequently place this length of fabric on the preform comprising means of compacting; and means of heating the length of fabric.

Abstract: A wing box rib, joining an aircraft wing to the wing box and to the rest of the structure, extends advantageously over an adjacent part of the fuselage, having in particular an upper line situated above a junction line of the wing upper surface panel. The connection is simplified, as is the structure of the aircraft and its manufacture, a lightening is possible, and the transmission of stresses takes place in a more favorable manner.

Abstract: An aircraft structure includes a wing spar (10), with orbital frames (24, 24?, 24?) arranged in transverse planes, right and left horizontal spars (26) connected to the wing spar (10) at the upper panel (14) of the spar respectively to the right and to the left of the spar, and for each right or left horizontal spar (26), a triangular panel (50) that includes a wall (60), a first edge arranged at the horizontal spar (26), a second side arranged at the wing spar (10), and a third side at which a first rectilinear oblique reinforcement (62) connecting the horizontal spar (26) and the wing spar (10) is provided, characterized in that the triangular panel (50) includes at least one second rectilinear oblique reinforcement (64) that connects the horizontal spar (26) and the wing spar (10).

Abstract: A weaving process for direct manufacture of three-dimensional structures with bidimensional walls with corners, without the need for sewing or other assembly between two ridges. The weaving is made by transforming weft threads into warp threads for making at least one face. The process is particularly adapted for the weaving of reinforcing elements for composite structures of corner fitting type.

Abstract: A method for producing a central wing box having an upper panel, a lower panel, a front spar and a rear spar, the upper edges of said spars approximately parallel to an axis Y being connected by the upper panel, and the lower edges of said spars approximately parallel to the axis Y being connected by the lower panel. The method includes producing at least one panel and at least one spar from composite material in one piece.

Abstract: A weaving method that makes it possible to directly produce three-dimensional structures having two-dimensional walls with corners, without requiring sewing or other joining between two edges. The weave is created by turning weft threads (24) into warp threads to create at least one face. The method is particularly suitable for weaving reinforcing pieces for composite structures such as three-dimensional corner reinforcements.

Abstract: A wing box rib (13), joining an aircraft wing (3) to the wing box and to the rest of the structure, extends advantageously over an adjacent part of the fuselage (2), having in particular an upper line (14) situated above a junction line (15) of the wing upper surface panel (3). The connection is simplified, as is the structure of the aircraft and its manufacture, a lightening is possible, and the transmission of stresses takes place in a more favourable manner.

Abstract: The invention relates to an automated device for implementing a drape-forming step to form a laminated fibrous preform, which is then impregnated with resin to produce a part made of composite material. The invention relates more particularly to the production of preforms for manufacturing parts such as panels, in particular very thick panels, that extend basically in two dimensions. The device of the invention comprises a manipulator (1) able to move and orient in space a tape laying head (10), said tape laying head comprising: a drum comprising a suction orifice leading to its surface and able to individually grasp a length of fabric on a mounting outside the tool and the tape laying head (10); means designed to subsequently place this length of fabric on the preform (70) comprising means of compacting and means of heating the length of fabric.

Abstract: An aircraft structure includes a wing spar (10), with orbital frames (24, 24?, 24?) arranged in transverse planes, right and left horizontal spars (26) connected to the wing spar (10) at the upper panel (14) of the spar respectively to the right and to the left of the spar, and for each right or left horizontal spar (26), a triangular panel (50) that includes a wall (60), a first edge arranged at the horizontal spar (26), a second side arranged at the wing spar (10), and a third side at which a first rectilinear oblique reinforcement (62) connecting the horizontal spar (26) and the wing spar (10) is provided, characterized in that the triangular panel (50) includes at least one second rectilinear oblique reinforcement (64) that connects the horizontal spar (26) and the wing spar (10).

Abstract: A weaving method that makes it possible to directly produce three-dimensional structures having two-dimensional walls with corners, without requiring sewing or other joining between two edges. The weave is created by turning weft threads (24) into warp threads to create at least one face. The method is particularly suitable for weaving reinforcing pieces for composite structures such as three-dimensional corner reinforcements.

Abstract: To make a laminated structure comprising a panel made of composite materials and placed flat against at least one metal plate, the panel and the plate are presented in a stack, this stack is drilled to form a fastening borehole, a fastening rod is introduced into the bore and the fastener is fixed. In the invention, during the drilling, a negative clearance is made between a diameter of the bore and a diameter of the fastener, and when the fastener is being introduced, it is introduced from the metal plate. This mode of action prompts a positive interference that promotes the lasting nature of the fastener.