PROCEDURE FOR THE MANUFACTURE OF LARGE PARTS OF COMPOSITE MATERIAL CONTROLLING THE THICKNESS OF THE EDGES THEREOF

摘要

Procedure for the manufacture of large parts of composite material, controlling the thickness of the edges thereof. It relates to the manufacture of a part (11) possessing edge zone (11) in an aeronautical structure through a join with joining plate (23) and backing plate (25) by means of the following stages: a) Definition of interface surface (15) of edge zone (13) to be in contact with joining plate (23); b) Manufacture of first panel (31) possessing the configuration planned for part (11); c) Obtainment of a map of differences between the thickness of first panel (31) and that which it should possess to be coincident with said interface surface (15); d) Manufacture of supplementary panel (33) having a thickness to be coincident with that of said map of differences; e) joining of supplementary panel (33) to first panel (31).