Patent ID: 7959753

Claim:
A process for manufacturing panels ( 9 ) for aeronautical structures with U-shaped stiffening members ( 13 ) and I-shaped stiffening members ( 17 ) between their webs, comprising: a) providing a curing tool ( 31 ) and a pre-impregnated composite laminate for shaping the skin ( 11 ) of the panel ( 9 ) on the curing tool ( 31 ); b) providing planar pre-impregnated composite laminates ( 23 ) for shaping the U-shaped stiffening members ( 13 ) and the I-shaped stiffening members ( 17 ), respectively; c) shaping the U-shaped stiffening members ( 13 ) from the planar laminates ( 23 ) on individual shaping tools ( 33 ) and placing the I-shaped stiffening elements ( 17 ) in housings provided in said tools ( 33 ), each housing comprising a space between adjacent tools; d) grouping said individual shaping tools ( 33 ) together on an assembly tool ( 41 ); e) placing a group of stiffening members ( 13 , 17 ) on the skin ( 11 ), turning the assembly tool ( 41 ) 180°, and positioning the assembly tool ( 41 ) upon the group of stiffening members ( 13 , 17 ); f) removing the assembly tool ( 41 ) once the stiffening members ( 13 , 17 ) have been joined to the skin ( 11 ); g) placing a vacuum bag ( 55 ) on the assembly of the skin ( 11 ) and stiffening members ( 13 , 17 ), fitting the vacuum bag ( 55 ) as much as possible to the contour of the stiffening members by means of profiles ( 59 ); and h) consolidating said assembly by a curing process under suitable pressure and temperature conditions using external tools ( 60 ) located outside the vacuum bag ( 55 ) to assure verticality of the webs of the stiffening members ( 13 , 17 ), wherein the external tools ( 60 ) used in step h) comprise a pair of profiles ( 61 ) and springs ( 63 ), the profiles ( 61 ) tightening around the webs of the stiffening members ( 13 , 17 ) on top of the vacuum bag ( 55 ) by the pressure of the springs ( 63 ), and wherein step b) includes providing the laminates ( 23 ) for shaping the U-shaped stiffening members ( 13 ) with a layer of dry peel-ply fabric ( 29 ) on a lower side of the laminates ( 23 ) before said turning of the assembly tool ( 41 ) in step e).