Aerospatiale Societe Nationale Industrielle

Societe Nationale Industrielle Et Aerospatiale

Gerard Rousseau

Nicole Pastureau

Jean-Marc N Donzac

Jean-Marc Dorvaux

Pierre Terrade

Laurence Piketty-Leydier

Jean Christophe Pasquet

A process for the production of a panel, of the honeycomb support type clad on opposite sides with a skin of carbon/carbon or carbon/ceramic composite. A honeycomb support is produced by pyrolysis of a carbon cloth pre-impregnated with a thermosetting resin. Skins are produced from carbon cloth pre-impregnated with a thermosetting resin. The support and the skins are assembled with a carbon cloth pre-impregnated with a thermosetting resin between them. The assembly is polymerized and then pyrolyzed. Finally, a chemical infiltration in vapor phase is carried out for densification and reinforcement of the bonding of the assembly. Used in the production of structures requiring very high dimensional stability, such as those used in outer space.

Process for the production of a panel of the honeycomb type and

Process and system for protecting an oxidizable material against oxidation. The process according to the invention consists of forming a gas-permeable body (1) having open pores (28), a first surface (2) intended to come into contact with an oxidizing gaseous flow (4) liable to oxidize the body and a second surface (6) opposite to the first surface and injecting an oxygen-free protective gas (8) through the second surface (6) leading to disturbances in the material giving it a protection against oxidation.

Process and system for protecting an oxidizable material against

Process for the production of a composite material protected against oxidation and the material obtained by the process. The invention relates to a process for the production of a material incorporating a composite body on which an aluminum nitride layer is directly deposited and then a tight layer of a refractory oxide in order to ensure its protection against environmental oxidation. The aluminum nitride layer is attached to the composite by an aluminum carbide layer. The oxide layer is an alumina layer.

Process for the production of a composite material protected against

The process includes impregnating carbon threads with molten pitch in an impregnation tank 4, shaping them by means of a short die 8, subjecting the so thread to thermal treatment by progressive heating while it is continuously passed through a treatment furnace 9, then cutting the shaped member when it leaves the furnace.

Process of making shaped members length made from carbon-carbon

A process for making a composite material wherein carbon reinforcing fibers may be coated with a carbon coating and a silicon carbide coating. The fibers are then densified in a carbon-based matrix, covered by a first silicon carbide layer, optionally sealed by a second silicon carbide coating, then an aluminum nitride or hafnium nitride coating and finally an outer alumina coating are applied. This stainless material can be used as a heat shield for space shuttles.

Composite material with carbon reinforced fibers and its production

The composite material according to the invention has carbon reinforcing fibres (2) coated with a carbon coating (6) and then a SiC coating (8), embedded in a carbon-based matrix, covered by an outer silicon carbide layer (10), sealed by a silicon carbide coating (14), then an aluminium or hafnium nitride coating (16) and finally an outer alumina coating (18). This stainless material can be used as a heat shield for space shuttles.

Composite material with carbon reinforcing fibers and its production

Composite material with matrix and reinforcing fibres of carbon and its production process. The composite material according to the invention comprises a substrate (2) of carbon fibres covered with a fine silicon carbide coating (6) and embedded in a carbon matrix (4) containing 2 to 10% by weight silicon carbide, an outer silicon carbide covering (10), followed by a first filling of the cracks with silica (14) and a second filling with borosilicate glass (16) (SiO.sub.2 -B.sub.2 O.sub.3). This unoxidizable material can in particular be used as a heat shield for a spacecraft.

Growing community of inventors

Saint Aubin De Medoc, France

Gerard Rousseau