| 摘要 |
The present invention relates to 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 the following steps: providing laminates for shaping the skin ( 11 ) on the curing tool ( 31 ); providing planar laminates ( 23 ) for shaping the stiffening members ( 13, 17 ); shaping the U-shaped stiffening members ( 13 ) on individual shaping tools ( 33 ) and placing the I-shaped stiffening elements ( 17 ) in said tools; grouping said individual shaping tools ( 33 ) together on an assembly tool ( 41 ); placing the group of stiffening members ( 13, 17 ) on the skin ( 11 ); placing a vacuum bag ( 55 ) on the assembly with the aid of profiles ( 59 ); consolidating said assembly by means of a curing process under suitable pressure and temperature conditions using external tools ( 60 ) to assure verticality of the webs of the stiffening members ( 13, 17 ).
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