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 device for fastening an injection element 4 with its foot 5 in a hole of a base plate 1 of an injection head 2 of a rocket engine, the foot 5 is tapered in steps up to its end. A first shoulder 7 of the foot abuts against the base plate 1; a thread (6) screwed into the base plate 1 is present after the first shoulder 7; the thread 6 is followed by a second shoulder 8 and then by a first, smooth cylindrical piece 9. This is followed by a third shoulder 11, on which a solder ring 12 made of a gold alloy is seated. A second, smooth cylindrical piece 13, which has a solder gap 13a between it and the corresponding hole in the base plate 1, follows after the third shoulder 11 up to the end. A process for fastening the injection element 4 provides for the solder ring 12 being first placed on the third shoulder 11, after which the injection element 4 is screwed into the base plate by means of a hexagon 22, and the injection head 2 is subsequently heated to about 1,035.degree. C.

Abstract: An injection head for rocket engines, in the combustion chambers of which one or more liquid propellants are chemically reacted to generate thrust, with a plurality of injection elements as well as with a distribution chamber arranged before these injection elements in terms of flow. The distribution chamber is divided into two chambers connected in series in terms of flow by means of a separator plate arranged at right angles to the longitudinal direction of the engine. The separator plate has a plurality of openings, each with a different flow cross section and with a defined direction of flow, wherein each opening is associated with one or more injection elements.

Abstract: A bearing unit comprises a first shaft carrying the bearing proper, a second shaft extending coaxially at least partly within the first shaft and cooperating with the load, and a shaft coupling device which engage the two shafts with each other in both the axial and the radial direction. The device can be disengaged if the second shaft is exposed to an undesirable load, such as impacts or vibrations, in order to protect the bearing proper.