Industrieanlagen-betriebsgesellschaft Gmbh

Daimler-benz Aerospace Ag

Other

Messerschmitt-bolkow-blohm Gmbh

Deutsche Aerospace

Ernst Blenninger

Ulrich Papenburg

Peter Goedtke

Michael Deyerler

Albert Seidel

Ulrich Goetz

Henning Herbig

Hartmut Neuking

Manfred Lechner

Peter Sindlhauser

Guenter Langel

A rocket engine has a combustion chamber and an expansion chamber interconnected by a nozzle. Both chambers and the nozzle are made of carbon fiber reinforced silicon carbide formed as a monolithic rocket engine body or formed in sections bonded to each other to also form such a monolithic rocket engine body. The rocket engine body is mounted in a support structure, preferably made of a metal. The rocket engine body sections are produced by mechanical machining of respective blanks made of C/SiC materials. Cooling channels and/or heat insulation structures are used for heat control. The insulation structures are preferably also made of C/SiC materials or of carbon fiber felts or of graphite film.

Jet propulsion power unit with non-metal components

In order to produce lightweight mirror structures or other reflecting components, preformed silicon elements of sufficient wall thickness are applied to a CFC or CMC substrate structure with the dimensions of the component to be produced, at a temperature in the range 1300.degree. C. and 1600.degree. C. either in vacuum or in a protective atmosphere. In this way a mirror structure or reflector is formed directly. It is possible to work at temperatures in the range of 300.degree. C. to 600.degree. C. when the silicon is applied in the form of a preform such as a wafer, which is joined to the substrate by way of a zone of a melt eutectic incorporating a nonferrous metal, which is preferably gold. The surfaces are subsequently coated.

Reflector

Method for the production of a reflector

For the production of lightweight reflectors or mirror structures, metallic silicon of sufficient thickness is applied to a CFC or CMC substrate preform structure having the dimensions of the component to be produced by a heat treatment process, in particular at temperatures between 1300.degree. C. and 1600.degree. C. and in a vacuum or in a protective atmosphere. In this way, reflectors or mirror structures are formed directly. It is possible to work at temperatures of 300.degree.-600.degree. C. when the silicon is applied in the form of wafers which are joined to the substrate preform by way a zone of a melt eutectic incorporating a nonferrous metal. Preferably the nonferrous metal is gold.

Method for the production of reflectors

For the manufacturing of an oxidation-stable component that can withstand temperature changes for space travel, a solid CFC-body with a density of from 0.1 to 0.8 g/cm.sup.3, which has nondirectional short fibers, is made from short carbon fibers and a hardenable resin binder. From the solid CFC-body, a CFC-blank having the dimensions of the component to be manufactured is prepared by means of turning or other material cutting. The CFC-blank is infiltrated with pyrolytic carbon to a density of no more than 1.0 g/cm.sup.3 and then with metallic silicon so that its density amounts to more than 2.0 g/cm.sup.3. A portion of the metallic silicon is reacted with the pyrolytic carbon to form silicon carbide. The proportion of the unreacted metallic silicon which remains in the component after this reaction amounts to at least 15 percent by weight.

Process for manufacturing an oxidation-stable component on a CFC base,

A helium II phase separator reproducible in manufacture utilizes a thermo-mechanical effect and comprises a plurality of adjacent passage gaps of identical width which are provided in the walls of a cavity dipped into a bath of liquid helium, so that the gaseous helium can be taken off.

Helium II phase separator

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Munich, Germany

Ernst Blenninger