Abstract: A process is proposed for producing a bipolar plate for an electrochemical device, said process comprising providing a first main plate body and a second main plate body as fibrous shaped bodies including carbon fibers and each having a joining face and an opposing useful face, infiltrating the main plate bodies with at least one carbon allotrope, locally applying silicon to respective joining sites in the joining faces, placing the joining faces against one another, such that the joining sites rest against one another and the useful faces of the two main plate bodies face away from one another, and at least locally heating the joining sites, such that the silicon melts and reacts with adjoining carbon to form a silicon-carbon bond.

Abstract: A heating element for in-flight de-icing of aircraft is disclosed. The heating element includes a carbon fiber material that is designed to be arranged on a component of an aircraft. The carbon fiber material includes at least two electrical contacts for connecting to an electrical wiring system, and at least one insulation layer for electrical insulation.

Abstract: This disclosure relates to a method and an apparatus for sealing a double-walled glass tube in a vacuum-tight manner, in particular a production method for manufacturing of solar collectors. By means of a vacuum chamber, inside of which a holding element is fixed and inside of which a heating conductor is arranged, an electro-conductively heating and a subsequent deforming of the double-walled glass tube can be achieved. No additional materials, such as metallic auxiliary element, solders are required. A simple installation inside the vacuum chamber is possible and a minimum vacuum feedthrough for the power supply of a heating conductor is required. The direct heat transfer onto the double walled glass tube and a resulting quick process control allows to reliably seal a double-walled glass tube of a thermal solar collector under vacuum with simple means.

Abstract: A method for producing a surface structure with a lightning strike protective system involves providing a support structure based on a fiber-reinforced composite material. At least one arrangement of a lightning strike protective material made from or with a conductive material is applied onto the support structure so that the lightning strike protective material arrangement adheres to the support structure in such a way that it is held securely in its position. A cover material is applied in such a way that it embeds the at least one arrangement of a lightning strike protective material that is held securely in its position on the support structure, and the cover material is solidified.

Abstract: A heating element for in-flight de-icing of aircraft is disclosed. The heating element includes a carbon fiber material that is designed to be arranged on a component of an aircraft. The carbon fiber material includes at least two electrical contacts for connecting to an electrical wiring system, and at least one insulation layer for electrical insulation.

Abstract: This relates to a turbine blade comprising a preformed fibrous fabric of fibres consisting of carbon, silicon carbide or rhenium fixed with a binder resin, and wherein the preformed and fixed fibrous fabric is coated and infiltrated, respectively, with B4C, wherein the preformed fibrous fabric that has been fixed and coated and infiltrated, respectively, with B4C further has a multilayer coating consisting of at least one layer of silicon carbide and at least one layer of a metal boride, a metal nitride or a metal carbide, and wherein an oxide ceramic is applied over the multilayer coating. The turbine blade is resistant to high temperatures and is particularly well suited for use in a gas turbine. Methods for producing the turbine blade are also described.

Abstract: An ice protection system for de-icing an aircraft and/or for keeping the aircraft free of ice includes a composite structure for an aircraft component and a structural element of an aircraft with an ice protection system that is integrated in the composite structure. The ice protection system includes a flat surface-like electric heating element that is embedded in the composite structure below an outer layer of an outer surface of the aircraft component.

Abstract: A contact element for high voltage direct current switches includes a matrix made of a first material selected from the group comprising copper, silver, palladium, platinum, tungsten, molybdenum, rhenium, nickel, gold, and alloys thereof. The contact element also includes a foreign phase, which is dispersed in the matrix and is made of a second material selected from the group comprising carbon, tin(II) oxide, tin(IV) oxide, zinc(II) oxide, tungsten, nickel and mixtures thereof. The contact element has a porosity of ?1.0% by volume, based on a total volume of the contact element.

Abstract: A method for producing a surface structure with a lightning strike protective system involves providing a support structure based on a fiber-reinforced composite material. At least one arrangement of a lightning strike protective material made from or with a conductive material is applied onto the support structure so that the lightning strike protective material arrangement adheres to the support structure in such a way that it is held securely in its position. A cover material is applied in such a way that it embeds the at least one arrangement of a lightning strike protective material that is held securely in its position on the support structure, and the cover material is solidified.

Abstract: An ice protection system for de-icing an aircraft and/or for keeping the aircraft free of ice includes a composite structure for an aircraft component and a structural element of an aircraft with an ice protection system that is integrated in the composite structure. The ice protection system includes a flat surface-like electric heating element that is embedded in the composite structure below an outer layer of an outer surface of the aircraft component.

Abstract: The invention relates to a method for producing a plastic molded part (9) comprising an integrated conductor path (3), which plastic molded part is used in particular as an intermediate product to be further processed into an electrically heatable mirror (1). The method steps are: a) producing a substrate (7) from a carrier body (2) made of an electrically insulating plastic material having a conductor path (3) made of an electrically conductive material on or in a surface (8) of the carrier body (2), b) flooding the surface (8) of the substrate (7) equipped with the conductor path (3) or the surface (11) of the substrate (7) opposite said surface with a liquid, electrically insulating coating material. The flooding evens out depressions due to uneven shrinkage in the thick and thin areas of the carrier body and a smooth surface can be produced, which can subsequently be covered with a reflective layer.

Abstract: The invention relates to a method for producing a plastic molded part (9) comprising an integrated conductor path (3), which plastic molded part is used in particular as an intermediate product to be further processed into an electrically heatable mirror (1). The method steps are: a) producing a substrate (7) from a carrier body (2) made of an electrically insulating plastic material having a conductor path (3) made of an electrically conductive material on or in a surface (8) of the carrier body (2), b) flooding the surface (8) of the substrate (7) equipped with the conductor path (3) or the surface (11) of the substrate (7) opposite said surface with a liquid, electrically insulating coating material. The flooding evens out depressions due to uneven shrinkage in the thick and thin areas of the carrier body and a smooth surface can be produced, which can subsequently be covered with a reflective layer.

Abstract: A fibre composite material having a metal matrix includes a fibre material having individual fibres. A metal coating includes a metallization layer disposed on the individual fibres so as to surround the fibres.

Abstract: A vehicle rear-view mirror has a light-transmitting filtering layer for filtering out interfering fractions of the light entering the filtering layer in the yellow spectral range. The mirror includes an interference reflector which has a plurality of thin layers for the reflection of the light impinging on the mirror. The degree of reflection of the interference reflector is less in the yellow spectral range than in the green and/or red wavelength range.

Abstract: A vehicle rear-view mirror has a light-transmitting filtering layer for filtering out interfering fractions of the light entering the filtering layer in the yellow spectral range. The mirror includes an interference reflector which has a plurality of thin layers for the reflection of the light impinging on the mirror. The degree of reflection of the interference reflector is less in the yellow spectral range than in the green and/or red wavelength range.

Abstract: A vehicle rear view mirror comprising a mirror plate which is provided with a reflection layer and, on the surface facing the viewer of the mirror, is provided with a scratch-resistant protective layer. An adhesive layer which is essentially made of a silicone gel is arranged between the mirror plate and the reflection layer or between the reflection layer and the scratch-resistant protective layer. The silicone gel adhesive layer is formed by an addition cross-linking two-part silicone rubber and exhibits an elasticity which prevents excessive tensions in the mirror layers due to different thermal expansion coefficient of the layers.