Societe Europeenne De Propulsion

Societe Europeene De Propulsion

Michel C Vives

Yves D Patrigeon

Pierre Taveau

Georges Habarou

Alain Lacombe

Bernard Buttazzoni

Jacques Etienne

Christian Bertone

Jean D Denoel

Francois R Barbaza

Pierre Daubigny

Yvon Sourdoulaud

Eric Pestourie

Denis Sabaca

Francois Bognandi

Yves Remillieux

Lucien Charbonnel

Jean L Limousin

Claude Ruet

A gun barrel lining made of composite material having refractory fiber reinforcement and a ceramic matrix, the fiber reinforcement comprises a cylindrical inner portion constituted by a three-dimensional fiber texture and a cylindrical outer portion surrounding the inner portion and having the same axis, the outer portion being constituted by a strip wound around the inner portion, and the inner and outer portions being codensified by the ceramic matrix.

Method of manufacturing a gun barrel provided with a lining

A structural connection is obtained between elements (21, 22) of the reinforcement texture to be assembled by using at least one blocking means (23). The latter is made of a fibrous texture that is compacted prior to being inserted in a corresponding lodging formed in at least one of the elements of the reinforcement texture in order to conform with the shape of the lodging. The blocking means (23) then locks itself into the lodging by relaxation of its fibrous texture, as a result of a removal of the prior compacting. The blocking means can be in the form of a dowel (23) inserted inside aligned lodgings formed in the elements (21, 22) of the reinforcement texture to be assembled, or may alternatively be part of one of the elements of reinforcement texture to be assembled.

Process for joining elements in the manufacture of thermostructural

The armor for providing ballistic protection comprises an armor plate for stopping projectiles with an auxiliary plate disposed in front thereof at a determined spacing therefrom, the auxiliary plate being constituted by a ceramic plate pierced by a large number of cells distributed in a regular mesh and constituted by blind holes extending perpendicularly to the rear face of the auxiliary plate and opening out into the front face thereof. The effect of the auxiliary plate is to destabilize and to score the projectiles so as to enhance their tendency to shatter on striking the armor plate.

Ballistic protection armor

The seat comprises panels made of ceramic matrix composite and assembled to one another by shape and by adhesion, either by interposition of an adhesive or else by condensification using the ceramic matrix material. The invention is particularly suitable for armored seats for helicopters.

Composite armored seat, and method of manufacture

A fibrous preform (10) of the component to be manufactured is conformed in the desired shape with the desired degree of compacting, prior to densification by chemical vapor deposition. The conformation is achieved by linking the preform (10) onto a rigid shaping device (12) by threads (30) that traverse the preform (10) and pass through holes (14) in the shaping device. The linking threads (30) are made of carbon or ceramic. Prior to the linking, a covering layer (16) may be arranged on the face of the preform (10) opposite to the one turned towards the shaping device.

Process for manufacturing a thermostructural composite by chemical vapor

The shaping of the fibrous texture is at least partly achieved by applying a deformable layer or strip, such as a cloth, made from a material having a thermal expansion coefficient different from that of the material constituting the fibrous texture. The layer or strip is stretched over the fibrous texture or is held in position against the texture by being wound over in order to obtain the degree of compaction wanted for the fibrous texture. The texture is densified by chemical vapor infiltration of the material constituting the matrix of the composite.

Method for shaping a fibrous reinforcement texture used in the

The invention relates to the manufacture of a composite material part by shaping a fibrous reinforcement texture and densifying the texture by chemical vapor infiltration of the material constituting the matrix of the composite through the porosity of the texture. Before densification, the texture is separated from an adjacent structure, such as an adjacent surface of a tool (12, 14) inside which the texture is held, or another texture, by means of an inserted layer (10) of fabric produced in a refractory material having a thermal expansion coefficient different from that of the constituent material of the texture.

Method for the manufacture of a composite material part

Sintered ceramic elements are associated to at least one composite material layer having a fibrous reinforcement arrangement and a ceramic matrix located behind the sintered ceramic elements.

Protective material having a multilayer ceramic structure

A method and apparatus for cutting up thick layers of fibrous material, the apparatus comprising a base to which a blade is fixed. The end of the blade carries a nozzle which emits an ultrafast fine water jet when fed with water under pressure via a duct. On each cutting pass, an additional thickness (H) of the layer is cut while the flanks of the cut that has already been made are held apart from each other by the blade, thereby ensuring that the jet is not disturbed by the flanks and retains its full cutting power.

Method and apparatus for cutting up fixed layers of flexible material

The invention relates to an anchoring dowel (11) for joining two bodies (7, 8). The dowel is composed of two contacting half-dowels (11a, 11b) whose opposing faces (13a, 13b ) are helical surfaces twisting in opposite directions. The projecting ends of the half-dowels are thus mutually spread apart with respect to contact zones (19a, 19b), which are compressed by the joined bodies (7, 8) so ensuring the anchoring of the dowel.

Anchoring dowel composed of two twisted half-dowels

A process relating to the manufacture of a composite component comprising a web and a reinforcement structure. The process includes providing a profiled section constituting a fibrous structure that is rigidified by impregnation with a thermoformable binder. The profiled section provided has a cross-section corresponding to the dimensions of a non-compacted blank of the component to be formed in a single unit with the web and the reinforcement structure. A blank of the component to be produced is machined from a length of the profiled section. The blank is press formed to obtain a preform having a shape and dimensions approximating those of the component to be produced and the preform is densified by chemical vapor infiltration of a material constituting a matrix within the fibrous structure, after elimination of the thermoformable binder.

Process for the manufacture of composite components comprising a web and

A laminated tubular fibrous structure is produced using a tubular braid and folding over its wall in order to form corrugations or wrinkles superposed in axial direction. The tubular braid is brought over a mandrel of which the inner diameter corresponds to that of the structure to be produced, by causing the braid to pass around a forming head which is mounted on the mandrel and of which the outer diameter corresponds to that of the structure to be produced, and at least one yarn is wound following a helicoidal path on the braid, around the mandrel and at the front of the forming head, between said head and a counter-piece of which the faces in facing relationship have shapes corresponding to the shape of the wrinkles to be produced, the winding of the yarn being performed while the forming head is moving away from the counter-piece progressively with the formation of the wrinkles. The structure is particularly suitable for use as reinforcing structure for producing pieces in composite material, such as ablative thermal protections for solid propellant rocket motors.

Process for producing a laminated tubular fibrous structure for use as

The invention relates to a retention pin for fixing a support plate or other prosthesis on bone tissue. The pin is made of a material which is bio-compatible with human tissue and comprises two half-pins each having a half-head for bearing against the prosthesis and a retention shank projecting therefrom, with the outline of each shank being semi-cylindrical and with the two half-pins being generally symmetrical to each other about a radial separation plane passing at least partially along the axis of the pin and extending at least as far as the inside faces of the half-heads from which the respective retention shanks project. Said shanks being of sufficient length to project beyond a wall of bone by a distance which is not less than the diameter of the fixing hole through the bone, thereby enabling locking means in the vicinity of the free end of the pin to urge the two half-pins apart from each other so as to urge them resiliently over at least a portion of their length against the inside wall of the fixing hole.

Bio-compatible retention pin, and a prosthesis including such a pin

The structure is formed by superposed layers of fibrous reinforcing material, which layers are bound together by threads implanted through the layers by being pushed by a pressurized fluid into a tubular needle which is actuated with back and forth movements during which it penetrates through the superposed layers and is pulled out therefrom, leaving in a portion of binding thread, the next portion of binding thread being positioned after a relative displacement of the needle with respect to the structure along the surface thereof.

Method for the production of a multi-directional fibrous structure and

The disc consists of a core (1), being a hub (3) surrounded by spokes (2), and friction pads in the form of annular sectors (8) having recesses (15, 16) in their inside backs (10) to cooperate with the spokes (2) in providing radial guidance and angular locking. Elastic means are provided for removably axially mounting the sectors on the core (1), which elastic means (19, 6) also serve to removably radially mount the sectors on the core.

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Eysines, France

Michel C Vives