Abstract: A flexible, thermal bridge element, particularly for a space flight instrument, a satellite, a transportation device, or a machine component, includes a number of carbon fiber-reinforced plastic (CFK) layers stacked on top of one another. Each of the CFK layers is composed of a plurality of heat-conductive carbon fibers embedded in a matrix. In at least two segments, particularly opposing end segments, the CFK layers are freed of the material of the matrix so that the carbon fibers of a respective CFK layer are exposed in the at least two segments. The exposed segments of the carbon fibers are provided with an associated metallization, by way of which within the framework of a thermally assisted joining process, the bridge element is connected to a thermally conductive connector element.

Abstract: A flexible, thermal bridge element, particularly for a space flight instrument, a satellite, a transportation device, or a machine component, includes a number of carbon fiber-reinforced plastic (CFK) layers stacked on top of one another. Each of the CFK layers is composed of a plurality of heat-conductive carbon fibers embedded in a matrix. In at least two segments, particularly opposing end segments, the CFK layers are freed of the material of the matrix so that the carbon fibers of a respective CFK layer are exposed in the at least two segments. The exposed segments of the carbon fibers are provided with an associated metallization, by way of which within the framework of a thermally assisted joining process, the bridge element is connected to a thermally conductive connector element.