Patent ID: 8622346
Filing Date: 2014-01-07
Classification: B29C,B29D,B29L,B64C,Y02T

Abstract:
1. A fuselage structure of composite material, comprising: at least one panel being formed of at least one group of composite layers and having sandwich elements; and at least one beam mounted the panel and provided with a flange positioned at least at one of its respective ends, and an essentially even outer surface and an essentially even inner surface at its flange, wherein the flange is configured for adhesive engagement with the at least one panel and the flange is in form locking engagement with the at least one group of composite layers of the panel; wherein sandwich elements of the at least one panel are apart from the areas of contact between the at least one panel and the at least one beam; wherein the at least one group of composite layers includes an outer group of composite layers being interrupted with a hole through which the beam is reaching; wherein the essentially even inner surface at the flange of the beam is mounted to the outside of the outer group of composite layers; and wherein the outer group of composite layers with the hole is overlapping partly the even inner surface for form lock with flange.