Abstract: An apparatus for carrying a fiber composite resin system in a heat transfer device, in particular an autoclave, for transferring heat between the fiber composite resin system and a directed gas flow, to produce a fiber composite aircraft component. The apparatus comprises a carrier structure for carrying the fiber composite resin system, the carrier structure having at least one flow path which, when the apparatus is accommodated in the heat transfer device, extends from an inlet on a side facing the directed gas flow along the fiber composite resin system accommodated by the carrier structure, to allow heat exchange between the gas flow in the flow path and the fiber composite resin system, and a diverting device for diverting at least a part of the directed gas flow when the apparatus is accommodated in the heat transfer device, to feed this part to the carrier structure flow path.

Abstract: Curing of fiber composite materials is controlled by controlling in closed loop fashion the curing temperature, the curing pressure and/or curing time duration by control signals obtained from the curing of at least one separate test sample made of fiber composite material identical to the fiber composite material to be cured. One or more sensors are inserted into the test sample for sensing a curing characteristic such as the ion viscosity of the fiber composite material. The ion viscosity is a measure of the resistivity of the fiber composite material. The sensor or sensors produce respective electrical signals which represent the current degree of curing as a function of the ion viscosity or resistivity of the fiber composite material. The electrical signals obtained from the test sample or test samples are used for controlling the curing of the fiber composite materials either in real time or later. In both instances only the separate test sample is provided with sensors.