| Patent Number |
Title Of Patent |
Date Issued |
| 5980105 |
Device of optically measuring a cryogenic temperature |
November 9, 1999 |
| The present invention relates to a device for optically measuring the temperatures of cryogenic fluids or of moving surfaces in such fluids by analyzing the decay in the luminescence of a doped crystal, the device comprising a light source for exciting said crystal, an optical fiber for |
| 5941062 |
Pulse rocket engine |
August 24, 1999 |
| A liquid propellant rocket engine comprising a chamber body connected to a converging/diverging thrust nozzle and to at least one lightly pressurized propellant feed duct, said body including a body bore in which an injector-forming piston can move longitudinally between a rest first |
| 5935378 |
Apparatus for making tubes out of composite material having high tribological and mechanical cha |
August 10, 1999 |
| A method of manufacturing a composite material in the form of an annular tube by winding on a mandrel both a reinforcing fiber fabric and a sheet of matrix material, comprising the following steps: 1) preheating the mandrel to a predetermined temperature; 2) fixing the reinforcing fiber |
| 5904957 |
Vapour phase chemical infiltration process for densifying porous substrates disposed in annular |
May 18, 1999 |
| A chemical vapor infiltration method for densifying porous substrates disposed in annular stacks. The substrates to be densified (12) are loaded inside a reaction chamber (11) of an infiltration oven, being disposed in at least one annular stack (30) defining an interior passage (31) wit |
| 5903976 |
Method of manufacturing a combustion enclosure with cooling by transpiration |
May 18, 1999 |
| The invention relates to a method of manufacturing an enclosure containing hot gases cooled by transpiration. The enclosure comprises a porous wall and means for applying a cooling fluid to the outside face of the porous wall to cause a flow of cooling fluid to pass through the porous wa |
| 5899388 |
Injection system and an associated tricoaxial element |
May 4, 1999 |
| The present invention relates to an injector of tricoaxial structure comprising a body that is circularly symmetrical about an axis of symmetry, said body being provided with a plurality of injection elements having axes parallel to said axis of symmetry and passing through an inject |
| 5894723 |
Rocket engine nozzle with ejectable inserts |
April 20, 1999 |
| The diverging part of the nozzle comprises an outer diverging part and at least one inner diverging part of outlet section that is smaller than that of the outer diverging part and designed to be separated therefrom and released at a predetermined instant in the operation of the combusti |
| 5853821 |
Method of protecting a part made of a carbon-containing composite material against oxidation |
December 29, 1998 |
| Prior to applying an impregnation composition constituted by a solution of at least one phosphate, a part made of composite material is treated in depth by means of an aqueous solution that penetrates into the open internal pores of the composite material, and is then dried. The aqueous |
| 5845398 |
Turbine of thermostructural composite material, in particular a turbine of large diameter, and a |
December 8, 1998 |
| The turbine comprises a plurality of blades disposed around a hub between two end plates, with the blades, the hub, and the end plates being made of thermostructural composite material. The hub is made by stacking plane annular plates of thermostructural composite material along a common |
| 5840227 |
Method of making internal thermal protection for a thruster |
November 24, 1998 |
| Internal thermal protection for a thruster structure, e.g. an end wall and extender structure of a tactical thruster, is made by preparing a low viscosity elastomer base suitable for being mixed with fibers by means of a mechanical mixer without putting the base into solution, by mixing |
| 5833402 |
Removable copying cutter |
November 10, 1998 |
| The present invention relates to a copying cutter provided with a cylindrical or conical body having a spherical end, constituting the active portion of the cutter, said end including a plurality of flutes inclined at a determined angle .theta. relative to the longitudinal axis of th |
| 5797260 |
Pulse rocket engine |
August 25, 1998 |
| A liquid propellant rocket engine comprising a chamber body connected to a converging/diverging thrust nozzle and to at least one lightly pressurized propellant feed duct, said body including a body bore in which an injector-forming piston can move longitudinally between a rest first |
| 5778033 |
Refractory composite structure with a plastically deformable metal lining |
July 7, 1998 |
| A sealed passage is formed in a part of refractory composite material by inserting a tubular metal lining in a hole in the part, brazing material being interposed between the lining and the hole, and by heating to braze the metal lining to the wall of the hole, so that the metal lining d |
| 5772777 |
Method for processing composite materials to enable recycling thereof |
June 30, 1998 |
| A method for processing composite materials (matrix+reinforcing fibers) to enable recycling thereof. The method is useful for chemically upgrading materials and comprises exposing the materials to ozone. |
| 5765367 |
System for controlling a space vehicle by gating gas |
June 16, 1998 |
| The control system comprises a plurality of nozzles pointing in different directions, a plurality of gas generators, and pipework connecting the gas generators to the nozzles via gates for allowing or preventing gas being ejected therethrough. Each gas generator is fitted with a shutter |
| 5738908 |
Method of densifying porous substrates by chemical vapor infiltration of silicon carbide |
April 14, 1998 |
| A reaction gas containing methyltrichlorosilane (MTS) and hydrogen is injected into the infiltration chamber (30) in which the substrate is placed and where predetermined infiltration temperature and pressure conditions obtain. The gas entering the infiltration chamber is preheated ( |
| 5725955 |
Process for protecting products made of composite material containing carbon against oxidation, |
March 10, 1998 |
| The method comprises forming at least one external coating on the surface of the product to be protected, the coating being constituted by a composition mainly containing a mixture of phosphates, of silica, and of alumina belonging to a P.sub.2 O.sub.5 --SiO.sub.2 --Al.sub.2 O.sub.3 |
| 5714244 |
Method for protecting a porous carbon-containing material from oxidation, and material obtained |
February 3, 1998 |
| A material is impregnated with an aqueous solution containing precursors of a glass-containing phosphate base modified at least by the presence of zinc oxide, then dried and heat treated to form an internal oxidation protection constituted by the modified phosphate glass-containing base. |
| 5697212 |
Rocket propellant tank self-pressurization |
December 16, 1997 |
| A device for pressurizing at least one propellant tank feeding the combustion members of a space vehicle, the tank(s) being connected to one or more pipes for feeding said combustion members, and at least one of the propellants being catalytically or thermally decomposable, the device |
| 5686144 |
Method for applying an anti-oxidative coating on brake disks of a carbon-containing composite ma |
November 11, 1997 |
| Each friction face of a brake disk (10) is masked (plates 40, 46) to isolate and seal the exterior from liquids, and the disk is immersed in a bath (30) of impregnating composition containing at least one substance which can form a protective layer against oxidation. Impregnation is |
| 5677060 |
Method for protecting products made of a refractory material against oxidation, and resulting pr |
October 14, 1997 |
| A coating for providing anti-oxidation protection is formed at least on the surface of the material and it comprises a refractory phase which is formed mainly of the refractory silicide Ti.sub.(0.4-0.95) Mo.sub.(0.6-0.05)Si.sub.2, and which has a branching microstructure forming an a |
| 5676522 |
Supersonic distributor for the inlet stage of a turbomachine |
October 14, 1997 |
| The supersonic distributor for the inlet stage of a turbomachine comprises an outer case, a hub, and a set of peripheral blades disposed in a ring and attached to the hub to provide supersonic speed fluid passages between the blades to transform a flow at high pressure and low speed into |
| 5665192 |
Method of making tubes out of composite material having high tribiological and mechanical charac |
September 9, 1997 |
| A method of manufacturing a composite material in the form of an annular tube by winding on a mandrel both a reinforcing fiber fabric and a sheet of matrix material, comprising the following steps: 1) preheating the mandrel to a predetermined temperature; 2) fixing the reinforcing fiber |
| 5660039 |
Injection system and an associated tricoaxial element |
August 26, 1997 |
| The present invention relates to an injector of tricoaxial structure comprising a body that is circularly symmetrical about an axis of symmetry, said body being provided with a plurality of injection elements having axes parallel to said axis of symmetry and passing through an inject |
| 5652030 |
Vapor phase chemical infiltration process of a material into a porous substrate at controlled su |
July 29, 1997 |
| The substrate (10) is placed in an enclosure (12) and is heated so as to establish therein a temperature gradient such that the substrate has a higher temperature in portions that are remote from its exposed surfaces than at its exposed surfaces. A reaction gas constituting a precursor f |
| 5622751 |
Method of protecting products of composite material against oxidizing and products protected the |
April 22, 1997 |
| The method comprises forming a coating on the product of composite material to be protected. The coating contains a mixture of a non-oxide refractory ceramic in finely-divided form, at least one refractory oxide in finely-divided form and providing healing properties by forming a glass, |
| 5604776 |
Method for making a sealed passage in a refractory composite part with a plastically deformable |
February 18, 1997 |
| A sealed passage is formed in a part of refractory composite material by inserting a tubular metal lining in a hole in the part, brazing material being interposed between the lining and the hole, and by heating to braze the metal lining to the wall of the hole, so that the metal lining d |
| 5604331 |
Fireproof sheath and method for making same |
February 18, 1997 |
| The present invention relates to a method of thermally and mechanically protecting cables and bundles of cables by use of a sheath braided directly around the element to be protected using a braiding yarn constituted by a plurality of elementary strands formed by interlacing syntheti |
| 5603213 |
Injection system with concentric slits and the associated injection elements |
February 18, 1997 |
| The present invention relates to a parallel-sheet injector provided with a body about an axis to which there is coaxially connected at least one annular injection element comprising a central annular injection slit surrounded by two other annular injection slits. The central annular slit |
| 5597009 |
Vacuum-enclosed integral cryogenic valve |
January 28, 1997 |
| The present invention relates to an electrically-controlled vacuum-enclosed cryogenic valve including firstly a body receiving the seat for a valve member, and inlet and outlet channels for a cryogenic fluid, the body and the channels being disposed in an enclosure in which a vacuum is c |
| 5583895 |
Method for making a sealed passage in a refractory composite part, and application to the produc |
December 10, 1996 |
| A sealed passage is formed in a part of refractory composite material by inserting a tubular metal lining in a hole in the part, brazing material being interposed between the lining and the hole, and by heating to braze the metal lining to the wall of the hole, so that the metal lining d |
| 5569422 |
Method of making parts out of an alumina matrix composite material |
October 29, 1996 |
| A part is made of a composite material having an alumina matrix by impregnating a fiber texture with a fluid composition containing a liquid precursor of alumina, a thermoplastic resin, and a suspension of alumina powder, and subsequently convening the precursor into alumina. Additional |
| 5559391 |
Three-grid ion-optical system |
September 24, 1996 |
| The present invention relates to an ion-optical system for a gas-discharge ion source, the system comprising a screen grid and an accelerator grid each constituted by a respective frame and a set of wires held parallel by supports and fixed to said frames by means of springs, the frames |
| 5549473 |
Loader device for an automatic space furnace |
August 27, 1996 |
| The loader device comprises a cartridge-carrying carousel provided with a set of cartridge-holders in which sealed closed cartridges are mounted in removable manner, each cartridge being designed to contain a sample for processing in a space furnace, the device further comprising a contr |
| 5547628 |
Method of manufacturing thermal shielding elements for space planes |
August 20, 1996 |
| A thermal shielding element which includes a hollow rigid panel in the form of a shell made of a thermostructural composite including fiber reinforcement densified by a matrix, and a thermal insulant filling the panel is obtained by making a rigid block (20) of thermally insulating m |
| 5536145 |
Method of manufacturing a turbine wheel having inserted blades, and a wheel obtained by performi |
July 16, 1996 |
| To manufacture a turbine wheel having blades made of a ceramic or composite material and inserted into a metal hub, firstly blades (16) are manufactured that are right cylindrical, each blade having a base (18) through which a hole is formed; a cylindrical ring (20) is formed, the ri |
| 5531067 |
Optimized system for feeding a reignitable rocket engine |
July 2, 1996 |
| The present invention relates to a system for feeding the engines of a space vehicle with at least one liquid propellant, the system comprising for the purpose of storing said liquid propellant under a pressure greater than the feed pressure, firstly a main tank having no liquid expulsio |
| 5514453 |
Method of manufacturing a composite |
May 7, 1996 |
| The pyrolytic carbon lamellar interphase is formed on the reinforcing fibers inside a chamber in which a plurality of successive cycles is performed, each cycle comprising: injecting a reaction gas in which the pyrolytic carbon precursor is selected from alkanes, excluding methane ta |
| 5514445 |
Honeycomb structure of thermostructural composite material |
May 7, 1996 |
| A method of manufacturing a honeycomb structure of thermostructural composite material comprising a fiber reinforcing fabric densified by a matrix, the fibers of the reinforcing fabric being of a material selected from carbon and ceramics, as is the matrix, the method comprising the |
| 5511426 |
Process and device for measuring operating turbine blade vibrations |
April 30, 1996 |
| A process and a device for the optical measurement of vibrations of rotating turbine blades moving with a specified speed of rotation. In one embodiment, the process comprises the steps of generating three reference signals in response to the detection, by an optical detector, of the |
| 5509266 |
Device for measuring variations in the thrust of a plasma acceleration with closed electron drif |
April 23, 1996 |
| A device for measuring variations in the thrust of a plasma accelerator with closed electron drift comprising a main annular channel for ionization and acceleration, at least one hollow cathode disposed outside the main channel and downstream therefrom, an anode, ionizable gas feed m |
| 5501011 |
Method of manufacture of an enclosure containing hot gases cooled by transportation, in particul |
March 26, 1996 |
| A method of manufacturing an enclosure containing hot gases cooled by transpiration comprises:forming a shaped rigid shell comprised of a microperforated sheet metal, hydraulic calibration sheath,welding spacers to an outside face of the hydraulic calibration sheath;welding an outer sealing |
| 5490892 |
Method of fabricating a composite material part, in particular a sandwich panel, from a pluralit |
February 13, 1996 |
| Distinct preforms are made for different portions of a composite material part that is to be fabricated, and they are assembled together in a non-densified state or in a state that is not completely densified by uniting respective contacting surfaces of the preforms (13, 15, 36) toge |
| 5490629 |
Rocket engine nozzle with an engine diffuser |
February 13, 1996 |
| The downstream portion of the diverging part of the nozzle of the rocket engine is extended by an ejectable diffuser which, downstream from the zone where it is connected to the diverging part, presents a zone of smaller cross-section that acts during a first stage of flight in the p |
| 5489074 |
Thermal protection device, in particular for an aerospace vehicle |
February 6, 1996 |
| The thermal protection device is made up of a plurality of juxtaposed unit modules each comprising a fairing element provided with fixing tabs and thermal insulation integrated in the fairing element. The gap between neighboring fairing elements is limited to the minimum width necessary |
| 5486379 |
Method of manufacturing a part made of composite material comprising fiber reinforcement consoli |
January 23, 1996 |
| A fiber preform constituting the fiber reinforcement of the part to be made is itself made by shaping and consolidating a fiber fabric by a liquid process. An interphase layer between the fibers and the matrix is formed on the consolidated preform prior to densification thereof with the |
| 5481870 |
Rocket engine nozzle with selectively smaller outlet cross-section |
January 9, 1996 |
| In a rocket engine nozzle with a selectively smaller outlet cross-section, the nozzle comprising a converging portion which receives the gases produced in a combustion chamber, a nozzle throat of small cross-section and a diverging part connected to the nozzle throat and terminating at i |
| 5476685 |
Process for the manufacture of a fiber reinforced composite material having a ceramic matrix and |
December 19, 1995 |
| In a process according to the invention, before a carbon/fiber ceramic matrix is densified, the carbon fiber reinforcement material is subjected to a thermal treatment in a non-oxidizing environment at a temperature greater than 1300.degree. C. and less than 2200.degree. C., to act on th |
| 5475354 |
Plasma accelerator of short length with closed electron drift |
December 12, 1995 |
| The system (31 to 33, 34 to 38) for generating a magnetic field in the main channel of the plasma accelerator are adapted to produce, in the main channel (24) an essentially radial magnetic field at the downstream end (225) of the channel (24), its induction being maximum at this point. |
| 5456981 |
Process for the manufacture of a fibrous preform formed of refractory fibers for producing a com |
October 10, 1995 |
| A process for the manufacture of a fibrous texture for producing a composite material article. The fibrous texture is formed of a yarn comprising discontinuous fibers which are made of a refractory material or a precursor thereof. The discontinuous fibers are disposed parallel to one |
