| 摘要 |
The present invention relates to a stringer 1 made of composite material for reinforcing aircraft skin panels. The invention comprises introducing plies at 90° in a segment close to the stringer run-out 3, and progressively reducing the number of plies at 0°, such that the majority of the number of plies is at 90° in a segment adjacent to the run-out, so the stiffness of the run-out is reduced, and the load it supports is also therefore reduced. The invention provides an alternative solution to the solutions already existing for getting the stringer run-outs to support a smaller load, thereby reducing the risk of the plies of the stringer peeling off and the risk of separation between stringer and skin panel. The invention also relates to a method of manufacturing said stringer. |
