초록 ▼

Method for manufacturing a base structure (8) of an aeronautical torsion box (1) for an aircraft (11) characterized in that it comprises the steps of: a.—providing at least a fresh skin (3), at least one fresh stringer (4), at least a fresh front spar (5) and fresh rear spar (6),b.—positioning the f

Method for manufacturing a base structure (8) of an aeronautical torsion box (1) for an aircraft (11) characterized in that it comprises the steps of: a.—providing at least a fresh skin (3), at least one fresh stringer (4), at least a fresh front spar (5) and fresh rear spar (6),b.—positioning the fresh skin (3), the at least one fresh stringer, the fresh spars (5, 6) in a curing tool in a configuration corresponding to that of a base structure (8),c.—subjecting the structure (8) to a single curing cycle, obtaining a cured base structure (8).

대표청구항 ▼

1. A method for manufacturing a base structure of an aeronautical torsion box for an aircraft comprising: a. providing a fresh skin, a fresh stringer, a fresh front spar, a fresh rear spar, a rib, and a babette, wherein the babettte is a strip covering complete edges of the rib, wherein the rib is a

1. A method for manufacturing a base structure of an aeronautical torsion box for an aircraft comprising: a. providing a fresh skin, a fresh stringer, a fresh front spar, a fresh rear spar, a rib, and a babette, wherein the babettte is a strip covering complete edges of the rib, wherein the rib is at least one of a cured rib made of dry fiber, a cured rib made of a pre-preg and a rib made of metal;b. positioning in a curing tool the fresh skin, the fresh stringer, the fresh front spar, the fresh rear spar, the rib with the babette, wherein the babette is positioned between the rib and each of the fresh skin, the fresh front and rear spars, and the fresh stringer, and wherein the fresh skin, the fresh stringer, the fresh front and rear spars and the rib with the babette form an assembly corresponding to a base structure, andc. subjecting the assembly, while in the curing tool, to a single curing cycle which cures the fresh skin, the fresh stringer, and the fresh front and rear spars to form a cured base structure which includes the stringer, the front and rear spars, the rib and the babette. 2. The method according to claim 1 further comprising an additional step performed after step c, and the additional step comprising joining the at least one rib by joining elements, the joining elements being one of a fastening means and an adhesive. 3. A method for manufacturing an aeronautical torsion box for an aircraft comprising: d1. providing a cured base structure manufactured according to claim 1,d2. providing an additional skin to be reinforced by at least one stringer;d3. joining an additional fresh skin to the cured base structure, on a side of the cured base structure opposite to the cured fresh skin, andd4. a further curing cycle to cure the additional fresh skin to the cured base structure to form the aeronautical torsion box including the stringer, the front and rear spars, and the rib with the babette. 4. The method according to claim 3 wherein the additional fresh skin is a fresh upper skin. 5. Aeronautical torsion box structure manufactured with a method according to claim 3. 6. Aircraft comprising an aeronautical torsion box manufactured with a method according to claim 3. 7. The method according to claim 1 further comprising, before step b, applying an adhesive to the edges of the rib. 8. Tooling for manufacturing a base structure of a torsion box, the tooling comprising: base modules adapted to house at least one stringer in a groove between the base modules,blocks configured to be positioned in the groove,a rib positioned between the blocks in the groove,at least a wedge element in the groove and with at least one of the blocks and the rib, wherein the at least one wedge element is configured to apply a compressive force to the rib and at least one of the base modules, anda caul plate covering the base modules, the groove, and side edges of the blocks, the rib and the wedge element in the groove. 9. The tooling according to claim 8 further comprising at least one pin positioned to a base plate. 10. The tooling according to claim 8 wherein the base modules are made of steel.