| 摘要 |
The present invention relates to a process for manufacturing an integrated shell element (13) having inner and outer surfaces (21, 22) and comprising on the inner surface at least one longitudinal and/or transversal stiffener element (23, 24, 26, 27, 29-32, 34-36), said process comprising providing a shell element lay-up tool comprising an upper tool surface; laying-up a plurality of resin impregnated fibers (10, 15, 37-39) on said upper tool surface to form the shell element; providing on the plurality of resin impregnated fibers laid-up in step (ii) a stiffener element lay-up tool (11, 14) comprising a sufficient number of surfaces to support a stiffener element structure; laying-up a plurality of resin impregnated fibers (12, 40) on said stiffener element lay-up tool to form the stiffener element; curing in a single step said plurality of resin impregnated fibers laid-up in steps (ii) and (iv) such that the plurality of fibers forming the shell element and the plurality of fibers forming the at least one stiffener element are laminated into an integrated shell element (13) comprising the at least one longitudinal or transversal stiffener element; and separating the integrated shell element (13) formed in step (v) from the shell element and stiffener element lay-up tools, and to an aircraft or spacecraft comprising such shell element. |
