Manufacturing method of an structural element with selected perforations

摘要

The structural element with defined perforations, pref. for boundary layer suction on an aircraft wing, is made using a prepreg with a three-dimensional weave of impregnated carbon fibres (2). Spacer fibres (4) of a material which evaporates at a higher temperature than the curing temperature of the prepreg are woven in perpendicularly to the surface (3) of the prepreg. The prepreg is then shaped and hardened at. 120 [deg]C after which it is heated further so that the spacer fibres (4) evaporate completely and leave perforations in the element.