Abstract: A device for creating a stiffened region on an outer structure of an aircraft for subsequently providing a service access if required is disclosed having an outer structure, a reinforcing plate which is mounted in a predetermined installation region on an inner side of the outer structure and forms a contact surface between the reinforcing plate and the outer structure. The reinforcing plate has a through-opening along the surface normal of the contact surface, and a connecting material which connects the reinforcing plate to the outer structure in an edge region of the contact surface by substance-to-substance bonding and/or by interlocking engagement.

Abstract: A structural part for lightning strike protection, preferably of an aircraft includes a first structure element, wherein the first structure element includes a conducting material and is adapted to conduct electric currents into a grounded conducting airframe structure, and a second structure element, wherein the second structure element includes an outer layer with a first surface, wherein the outer layer includes a composite, preferably carbon-fibre reinforced plastic, CFRP or glass-fibre reinforced plastic GFRP. The structural part further includes a first elongated, preferably wedge-shaped, electrical conductor, with a first end and a second end, wherein the first end of the first elongated electrical conductor is connected to the first structure element and extends through the second structure element to the first surface, so that the second end of the first elongated electrical conductor serves as a lightning receptor without impairing the radar cross section of the aircraft.

Abstract: A structural element, in particular for an aircraft, such as an airplane, contains a laminate having a plurality of layers made of a fiber composite plastics material with carbon fibers, a lightning protection layer and optionally an electrically insulating dielectric protection layer. The laminate contains at least one hybrid layer, which comprises a carbon fiber-absorption fiber composite, the elongation at break of the absorption fiber being greater than the elongation at break of the carbon fibers.

Abstract: A structural element, in particular for an aircraft, such as an airplane, contains a laminate having a plurality of layers made of a fiber composite plastics material with carbon fibers, a lightning protection layer and optionally an electrically insulating dielectric protection layer. The laminate contains at least one hybrid layer, which comprises a carbon fiber-absorption fiber composite, the elongation at break of the absorption fiber being greater than the elongation at break of the carbon fibers.

Abstract: Radome with an integrated plasma shutter covering an antenna and method for selectively shielding an antenna. The radome includes a honeycomb core formed to contain a plasma-guiding layer, and coverplates arranged to sandwich the honeycomb core. Electrodes are structured and arranged for plasma excitation, the electrodes being high frequency (HF)—transparent at least in an operating frequency range of the antenna. The instant abstract is neither intended to define the invention disclosed in this specification nor intended to limit the scope of the invention in any way.

Abstract: Radome with an integrated plasma shutter covering an antenna and method for selectively shielding an antenna. The radome includes a honeycomb core formed to contain a plasma-guiding layer, and coverplates arranged to sandwich the honeycomb core. Electrodes are structured and arranged for plasma excitation, the electrodes being high frequency (HF)-transparent at least in an operating frequency range of the antenna. The instant abstract is neither intended to define the invention disclosed in this specification nor intended to limit the scope of the invention in any way.

Abstract: An antenna mounted on a supporting system primary structure of a vehicle, in which the supporting system primary structure has an indentation. The antenna includes an EM functional core incorporated into the indentation of the supporting system primary structure, and a cover plate forming one of an upper and outer cover of the EM functional core that is structured and arranged as a conformal outside. Furthermore, boundary areas of the cover plate are connected with the supporting system primary structure. The instant abstract is neither intended to define the invention disclosed in this specification nor intended to limit the scope of the invention in any way.

Abstract: A cover skin for a variable-shape aerodynamic area, such as a wing structure, tail unit structure, control surface structure or flap structure is described. A cover skin is deformable in one direction without exhibiting substantial deformation in a transverse direction. A deformable framework structure is embedded in a layer of an elastic material, such as rubber or polymer. The framework structure may be comprised of non-deformable elements joined pivotably in auxetic and non-auxetic assemblies of elements that are capable of substantially eliminating transversal contraction, when the cover skin is longitudinal stretched, and substantially eliminating transversal expansion, when the cover skin is longitudinally contracted.

Abstract: A cellular actuator device suitable for a control surface of an aircraft or space craft has a number of elementary cells which are combined to a common arrangement and are formed by pressure-tight chambers. The elementary cells can be acted upon by a pressure medium and, when acted upon by the pressure medium, can be deformed in at least one work direction while changing their length. The elementary cells are coupled for combining their length changes in the at least one working direction to an overall movement of the elementary cell arrangement. The actuator device is particularly suitable for actuating a control surface of an aircraft or spacecraft.

Abstract: An antenna mounted on a supporting system primary structure of a vehicle, in which the supporting system primary structure has an indentation. The antenna includes an EM functional core incorporated into the indentation of the supporting system primary structure, and a cover plate forming one of an upper and outer cover of the EM functional core that is structured and arranged as a conformal outside. Furthermore, boundary areas of the cover plate are connected with the supporting system primary structure. The instant abstract is neither intended to define the invention disclosed in this specification nor intended to limit the scope of the invention in any way.

Abstract: In a nondestructive ultrasonic testing method for an implementation in a testing device, defects are installed in a testing area of a structural part by determining reflections on inhomogeneities in a testing area of the structural part. At least one ultrasonic transmitter is provided for coupling ultrasonic excitations into the structural part, and at least two ultrasonic receivers are installed for receiving structure responses to the excitations coupled into the structure. A number of testing points are determined and for each testing point and each location of the ultrasonic receivers, expectancy range data are determined and stored for signal forms being implemented in the testing device. When, an inhomogeneity is present in the respective testing point, excitations are reflected thereon and are measured by the respective ultrasonic receiver. The received reflection data are compared with the stored expectancy ranges to determine the location of a defect.

Abstract: A cellular actuator device suitable for a control surface of an aircraft or space craft has a number of elementary cells which are combined to a common arrangement and are formed by pressure-tight chambers. The elementary cells can be acted upon by a pressure medium and, when acted upon by the pressure medium, can be deformed in at least one work direction while changing their length. The elementary cells are coupled for combining their length changes in the at least one working direction to an overall movement of the elementary cell arrangement. The actuator device is particularly suitable for actuating a control surface of an aircraft or spacecraft.

Abstract: In a nondestructive ultrasonic testing method for an implementation in a testing device, defects are installed in a testing area of a structural part by determining reflections on inhomogeneities in the a testing area of the structural part. A least one ultrasonic transmitter is provided for coupling ultrasonic excitations into the structural part and at least two ultrasonic receivers are installed for receiving structure responses to the excitations coupled into the structure. A number of testing points being are determined and for each testing point and each location of the ultrasonic receivers, expectancy range data are determined and stored for signal forms being implemented in the testing device. When an inhomogeneity is present in the respective testing point, excitations are reflected thereon and are measured by the respective ultrasonic receiver. The received reflection data are compared with the stored expectancy ranges to determine the location of a defect.

Abstract: Carrying structure of an active antenna in the aerospace industry uses basically fiber reinforced synthetic material in which heat conductive elements and/or elements conducting electromagnetic waves (electro, optic) are integrated into that support structure for the antenna.