Abstract: Method for forming and component for rocket construction. Method includes depositing nickel on a base body by nickel vapor deposition to form a nickel coated base body. The nickel coated base body is processed to form the component.

Abstract: A nozzle extension including flange elements of C/SiC is able to be manufactured relatively simply and provides sufficient physical properties. The carbon-fiber structure of the nozzle extension is wound, and a flange for fastening the nozzle extension to the nozzle outlet of the combustion chamber is integrated in the nozzle extension by a continuous fiber flow of the wound carbon-fiber structure. The foregoing may be intended for use in rocket propulsion units.

Abstract: A nozzle extension including flange elements of C/SiC is able to be manufactured relatively simply and provides sufficient physical properties. The carbon-fiber structure of the nozzle extension is wound, and a flange for fastening the nozzle extension to the nozzle outlet of the combustion chamber is integrated in the nozzle extension by a continuous fiber flow of the wound carbon-fiber structure. The foregoing may be intended for use in rocket propulsion units.

Abstract: A winding apparatus is disclosed for winding force transmitting elements of iber reinforced materials. Such force transmitting elements are used, for example, for connecting helicopter rotor blades to the rotor head. A cylindrical winding carrier is mounted for rotation on a machine frame. The fiber strand feeding device is mounted for translation on the frame. A plurality of separate winding cores are distributed around the carrier. Relative motion of the carrier and fiber strand feeding device is controlled, for example, by computer to achieve the desired windings on the separate cores, so that at least one set of elements is produced simultaneously under the same winding conditions, whereby all the members of a set have uniform characteristics, especially force transmitting characteristics.