| 摘要 |
The present invention refers a tooling for curing composite (CFRP) structures for aircrafts, such as stringers (1), torsion boxes, skin panels, wing surfaces, horizontal tail or vertical stabilizers (HTP & VTP), etc. A hybrid tool (14) comprises a metallic portion (15, 15') and an elastic portion (16, 16') arranged on a surface of the metallic portion (15, 15'). The elastic portion and the metallic portion are permanently joined to each other, so that the metallic portion and the elastic portion together define a surface having a shape which copies at least part of a surface of a piece of composite material to be cured. The tool of the invention is capable of satisfactorily curing pieces (25) of composite material, having minimum thickness and/or very aggressive change of thickness. |
