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 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 process for the production of a structural part of an aircraft, whereby the part is made of composite material that includes a thermosetting resin and that has a section profile that can be stamped, whereby the process includes: producing a flat blank by draping layers of supports that are preimpregnated with thermosetting resin, partially cross-linking the flat blank, and stamping the flat blank between a matrix (14) and a punch (16) that are called the equipment, each including an impression that is adapted to the shape of the surface that is in contact with the part that is to be produced and whose air gap is sized based on the part that is to be produced, wherein the equipment is heated to modulate the progress of the cross-linking at the end of the forming operation.

Abstract: A process for the production of a core that can be used for the manufacturing of a part that is made of composite material, whereby the core consists of at least one powdered and/or granular product (16), includes introducing the at least one powdered and/or granular product (16) by vibrating it in an outer envelope (14) placed in a device (18) having a cavity that is delimited by a wall (20) whose geometry is adapted to that of the core to be produced and flattening the outer envelope (14) against the wall (20), characterized in that vibrations are emitted slightly above the fill level during filling.

Abstract: A process for the production of a core that can be used for the manufacturing of a part that is made of composite material, whereby the core consists of at least one powdered and/or granular product (16), includes introducing the at least one powdered and/or granular product (16) by vibrating it in an outer envelope (14) placed in a device (18) having a cavity that is delimited by a wall (20) whose geometry is adapted to that of the core to be produced and flattening the outer envelope (14) against the wall (20), characterized in that vibrations are emitted slightly above the fill level during filling.

Abstract: A process for the production of a structural part of an aircraft, whereby the part is made of composite material that includes a thermosetting resin and that has a section profile that can be stamped, whereby the process includes: producing a flat blank by draping layers of supports that are preimpregnated with thermosetting resin, partially cross-linking the flat blank, and stamping the flat blank between a matrix (14) and a punch (16) that are called the equipment, each including an impression that is adapted to the shape of the surface that is in contact with the part that is to be produced and whose air gap is sized based on the part that is to be produced, wherein the equipment is heated to modulate the progress of the cross-linking at the end of the forming operation.