| 摘要 |
<p>Procedure for the manufacture of a composite material part (11) having, at least, one reinforced area (13) of greater thickness than the surrounding areas, in which the dimensions and laying up sequence of the plies (21, 21′, 21″, 21′″) that are used in the laying up step of said reinforced area (13), are determined so that, at least one of the plies (21′, 21″, 21′″) crosses over the ply situated beneath it for reducing the volume of said reinforced area (13). The invention also refers to a composite material part (11) manufactured with said procedure, particularly a CFRP skin of an aircraft lifting surface.</p> |
