Abstract: A fibrous preform (1) is produced, provided with a sandwich structure comprising an intermediate flexible core (4) and two outer fibrous frames (2, 3), respectively arranged on opposing outer faces of said flexible core (4) and assembled by sections of wire (8, 9) passing through said fibrous frames (2, 3), said preform (1) being impregnated with resin. Said preform is then hardened and the core (4) is removed, preferably by pre-densification with chemical vapour infiltration, and the structure produced is then densified with liquid-phase infiltration.

Abstract: A fibrous preform (1) is produced, provided with a sandwich structure comprising an intermediate flexible core (4) and two outer fibrous frames (2, 3), respectively arranged on opposing outer faces of said flexible core (4) and assembled by sections of wire (8, 9) passing through said fibrous frames (2, 3), said preform (1) being impregnated with resin. Said preform is then hardened and the core (4) is removed, preferably by pre-densification with chemical vapour infiltration, and the structure produced is then densified with liquid-phase infiltration.

Abstract: A method for manufacturing components from parts made from different materials involves producing a transition between one part made from a first material and another part made from a second material by an additive layer manufacturing method. The additive layer manufacturing method involves starting with the first material and then gradually changing the material composition to the second material.

Abstract: A method for producing a component having a base body made of a carbon fiber reinforced ceramic and a protective layer which is applied on the base body includes the following steps: providing the base body: applying a first layer on the base body, the first layer comprising a slip with reactive carbon; applying a second layer on the first layer, the second layer comprising a slip with silicon. The application of the layers can be carried out by painting, brushing, filling or dipping techniques, or by fully automatable spraying devices. Finally, the silicon of the second layer is liquefied in a thermal treatment, so that the liquid silicon penetrates into the first layer and forms with the reactive carbon a reaction protective layer composed of a silicon carbide compound.

Abstract: A method for producing a brazed joint having at least one of a metal/ceramic joint and a ceramic/ceramic joint. The method includes forming bores in at least one ceramic surface to be brazed, and the bores have an average diameter of greater than 550 ?m. 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 combustion chamber, in particular for a rocket drive, includes at least one jacket madeof a composite material with a ceramic matrix. The composite material contains a fibrous structure made of carbon-containing fibers, and the fibrous structure comprises layers of fibers that form a three-dimensional matrix.

Abstract: A method for producing a brazed joint having at least one of a metal/ceramic joint and a ceramic/ceramic joint. The method includes forming bores in at least one ceramic surface to be brazed, and the bores have an average diameter of greater than 550 ?m. 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 combustion chamber, in particular for a rocket drive, comprises at least one jacket made of a composite material with a ceramic matrix. The composite material contains a fibrous structure made of carbon-containing fibers, and the fibrous structure comprises layers of fibers that form a three-dimensional matrix.

Abstract: A combustion chamber structure for a rocket engine or the like, has a combustion chamber liner with cooling channels and at least one manifold for feeding and removing a coolant, particularly a cryogenic fuel. The at least one manifold is brazed together with the combustion chamber liner and the area of the combustion chamber liner that is not covered by the at least one manifold is coated with an electroplated structural jacket. The invention also includes a method for manufacturing the combustion chamber structure.

Abstract: A combustion chamber structure for a rocket engine or the like, has a combustion chamber liner with cooling channels and at least one manifold for feeding and removing a coolant, particularly a cryogenic fuel. The at least one manifold is brazed together with the combustion chamber liner and the area of the combustion chamber liner that is not covered by the at least one manifold is coated with an electroplated structural jacket. The invention also includes a method for manufacturing the combustion chamber structure.

Abstract: A combustion chamber, in particular for a rocket drive, comprises at least one jacket made of a composite material with a ceramic matrix. The composite material contains a fibrous structure made of carbon-containing fibers, and the fibrous structure comprises layers of fibers that form a three-dimensional matrix.

Abstract: A combustion chamber, in particular for a rocket drive, comprises at least one jacket made of a composite material with a ceramic matrix. The composite material contains a fibrous structure made of carbon-containing fibers, and the fibrous structure comprises layers of fibers that form a three-dimensional matrix.

Abstract: A combustion chamber wall structure for a high performance propulsion plant or a wall structure for a nozzle of flying bodies has an outer pressure jacket and an inner wall member provided with a multitude of cooling channels. In operation the inner wall is in contact with hot gases. An intermediate layer made of a material having shape memory characteristics and/or superelastic characteristics is arranged between the inner wall member and the outer pressure jacket.

Abstract: A wall construction for a combustion chamber or thrust nozzle of a high power engine of a flying body includes an inner wall body that is subjected to the hot gases within the combustion chamber, and an outer jacket that surrounds the inner wall body and carries the mechanical loads. The inner wall body has a plurality of cooling channels through which a cooling medium may flow. The outer jacket is made of a long-fiber C/SiC composite material, while the inner wall member is made of a short fiber C/SiC composite material. The reduced thermal expansion coefficient of this ceramic composite material in comparison to metal alloys leads to a reduced straining and reduced deformation of the wall construction and therewith an increased operating life.

Abstract: A pulsed laser deposition (PLD) process is used for forming a functional metal, ceramic, or ceramic/metal layer on an inner wall of a hollow body. Simultaneously with the deposition process, a thin-film laser treatment is carried out, whereby a laser beam impinges on the coating layer as it is being formed to achieve a rapid heating followed by a rapid cooling and solidification of the deposited coating layer. In this context, the energy and material flux densities are prescribed and controlled as a function of the spacing of the condensation region from the substrate surface. Laser pulses having an energy of 1 to 2 Joules and a pulse repetition rate of 10 to 50 Hz are used. The pulse duration as well as the residual gas atmosphere in the vacuum deposition chamber are controlled so that the generated plasma flux forms the desired layered grain structure, namely a glassy amorphous structure, a columnar structure, or a polycrystalline structure.