The present invention relates to a method for producing a compartmented tank made of composite material, in which a structure comprising a common base precursor is fired under vacuum in equipment, and in which domes intended to form the end bases are then mounted and secured using a thermosetting adhesive.
B29C 70/34 - Shaping by lay-up, i.e. applying fibres, tape or broadsheet on a mould, former or coreShaping by spray-up, i.e. spraying of fibres on a mould, former or core and shaping or impregnating by compression
B29C 53/60 - Winding and joining, e.g. winding spirally helically using internal forming surfaces, e.g. mandrels
B29C 65/70 - Joining of preformed partsApparatus therefor by moulding
B29C 70/38 - Automated lay-up, e.g. using robots, laying filaments according to predetermined patterns
B29C 70/44 - Shaping or impregnating by compression for producing articles of definite length, i.e. discrete articles using isostatic pressure, e.g. pressure difference-moulding, vacuum bag-moulding, autoclave-moulding or expanding rubber-moulding
B64G 1/40 - Arrangements or adaptations of propulsion systems
F17C 1/02 - Pressure vessels, e.g. gas cylinder, gas tank, replaceable cartridge involving reinforcing arrangements
F17C 1/16 - Pressure vessels, e.g. gas cylinder, gas tank, replaceable cartridge constructed of plastics materials
B29C 33/00 - Moulds or coresDetails thereof or accessories therefor
B29C 33/44 - Moulds or coresDetails thereof or accessories therefor with means for, or specially constructed to facilitate, the removal of articles, e.g. of undercut articles
F17C 1/12 - Pressure vessels, e.g. gas cylinder, gas tank, replaceable cartridge with provision for thermal insulation
The present invention relates to a method for producing a compartmented tank made of composite material, in which a precursor of the common base and domes intended to form the end bases are secured to a body that is fired in advance using a thermosetting adhesive.
B29C 70/34 - Shaping by lay-up, i.e. applying fibres, tape or broadsheet on a mould, former or coreShaping by spray-up, i.e. spraying of fibres on a mould, former or core and shaping or impregnating by compression
B29C 33/00 - Moulds or coresDetails thereof or accessories therefor
B29C 33/44 - Moulds or coresDetails thereof or accessories therefor with means for, or specially constructed to facilitate, the removal of articles, e.g. of undercut articles
B29C 53/60 - Winding and joining, e.g. winding spirally helically using internal forming surfaces, e.g. mandrels
B29C 65/70 - Joining of preformed partsApparatus therefor by moulding
B29C 70/38 - Automated lay-up, e.g. using robots, laying filaments according to predetermined patterns
B29C 70/44 - Shaping or impregnating by compression for producing articles of definite length, i.e. discrete articles using isostatic pressure, e.g. pressure difference-moulding, vacuum bag-moulding, autoclave-moulding or expanding rubber-moulding
B64G 1/40 - Arrangements or adaptations of propulsion systems
F17C 1/02 - Pressure vessels, e.g. gas cylinder, gas tank, replaceable cartridge involving reinforcing arrangements
F17C 1/16 - Pressure vessels, e.g. gas cylinder, gas tank, replaceable cartridge constructed of plastics materials
F17C 1/12 - Pressure vessels, e.g. gas cylinder, gas tank, replaceable cartridge with provision for thermal insulation
The present invention relates to a method for producing a compartmented tank made of composite material, in which an assembly comprising a common base precursor is fired under vacuum in equipment, the moulding parts of which are external to the assembly in order to facilitate subsequent removal from the mould.
B29C 70/38 - Automated lay-up, e.g. using robots, laying filaments according to predetermined patterns
B29C 65/70 - Joining of preformed partsApparatus therefor by moulding
B29C 70/44 - Shaping or impregnating by compression for producing articles of definite length, i.e. discrete articles using isostatic pressure, e.g. pressure difference-moulding, vacuum bag-moulding, autoclave-moulding or expanding rubber-moulding
The present invention relates to a method for producing a tank made of composite material, in which an assembly comprising precursor base domes provided with a thermoset reinforcement are employed so as to simplify the moulding equipment.
B29C 65/70 - Joining of preformed partsApparatus therefor by moulding
B29C 70/44 - Shaping or impregnating by compression for producing articles of definite length, i.e. discrete articles using isostatic pressure, e.g. pressure difference-moulding, vacuum bag-moulding, autoclave-moulding or expanding rubber-moulding
B64G 1/40 - Arrangements or adaptations of propulsion systems
F17C 1/02 - Pressure vessels, e.g. gas cylinder, gas tank, replaceable cartridge involving reinforcing arrangements
F17C 1/16 - Pressure vessels, e.g. gas cylinder, gas tank, replaceable cartridge constructed of plastics materials
B29C 70/34 - Shaping by lay-up, i.e. applying fibres, tape or broadsheet on a mould, former or coreShaping by spray-up, i.e. spraying of fibres on a mould, former or core and shaping or impregnating by compression
A three-point propulsion system of an orbital deployment space module for at least one satellite including: chassis including exactly three first housings shaped to each receive a propulsion unit and at least one second housing shaped to receive a tank, at least one liquid fuel tank disposed in a second housing, and exactly three propulsion units, each propulsion unit being disposed in one of the first housings, and each propulsion unit including at least one thruster.
12 - Land, air and water vehicles; parts of land vehicles
13 - Firearms; explosives
42 - Scientific, technological and industrial services, research and design
Goods & Services
Motors and engines (other than for land vehicles); space
vehicle engines; rocket engines other than for land
vehicles; propulsion mechanisms other than for land
vehicles; rocket engine thruster; component parts of
propulsion mechanisms other than for land vehicles;
rocket-engine thruster component parts; rocket nozzles
[engine parts]; hypersonic engines; solid-propulsion rocket
engines; rocket engines for launchers; rocket engines for
ballistic and tactical missiles; motor-driven tools. Sounding rocket; micro-launchers and nano-launchers;
unmanned spaceships of all kinds for suborbital flight;
launch vehicles; rockets for space navigation; space
vehicles, namely, rockets and rockets equipped with a rocket
payload system; rocket-propelled vehicles; rocket launching
platforms [vehicles]; spacecraft for placing objects in
outer space; rocket launch devices. Flying bodies equipped with a rocket engine; missiles;
pyrotechnic products; pyrotechnic compositions; solid
pyrotechnic products for rocket engines; propellant powders;
solid propellants; rockets; signal rocket flares;
pyrotechnic transmission cords; pyrotechnic charges;
pyrotechnic engines; rocket-propelled ballistic missiles;
flares [pyrotechnic]; pyrotechnic ammunition; launchers for
pyrotechnic use. Engineering and technical consultancy services (services
provided by engineers); analysis and appraisal services;
engineering work; scientific and industrial research in the
fields of aerospace, composite materials and energy
equipment; chemical research; technical project studies;
testing of machines; testing of materials; testing of
spacecraft; system testing; testing of aerospace vehicle
parts and equipment; technical inspection service for
systems; equipment and parts of aerospace vehicles;
analysis, expertise and processing of the acquisition of
technical data recorded during test campaign of systems,
equipment and parts of aerospace vehicles (engineering
works); design of spatial structures; design, installation,
maintenance, updating and rental of software; computer
programming; database design and maintenance; research and
development of new products for third parties; rocket design
and development services; design and development services
for space launchers; conducting technical project studies in
relation to satellites and/or spacecraft; technical advisory
services in aerospace engineering; scientific analysis,
research and development services; industrial analysis and
research services; technical project studies in the field of
construction; industrial design services; industrial
development services; research in industrial processes;
scientific and industrial research; industrial design of
vehicles; industrial design of vehicles, namely, spacecraft;
design of industrial machines; design of new products;
development of new products; research and development of new
products; design and testing of new products.
7.
SYSTEM AND METHOD FOR CONDITIONING FUEL FOR AN AIR-BREATHING HYDROGEN ENGINE
A fuel conditioning system for an aerobic hydrogen engine, including: at least one hydrogen pump configured to increase the pressure of the liquid hydrogen delivered at the outlet of a tank, one or several heat exchangers configured to increase the temperature of the pressurized hydrogen, an air supply circuit, at least one combustion device configured to ensure a partial combustion of the hydrogen with air coming from the air supply circuit in order to produce a fuel including a gas mixture including gaseous hydrogen and devoid of oxygen.
Embodiments of the invention relate to a hypersonic transport system including: an aircraft which includes a hypersonic lift-to-drag ratio greater than or equal to 2.5, wherein the aircraft includes a secondary propulsion device and position sensors, and wherein the aircraft also includes a variably shaped aerodynamic surface; a main propulsion device which is removably attached to the aircraft; and a control unit which is configured to monitor the aircraft and the main propulsion device.
A method for preparing 3,5-dinitropyrazole, includes obtaining N-acetyl-3-nitropyrazole from pyrazole, and a sigmatropic rearrangement of the compound obtained.
The invention relates to a facility (1) for destroying an item by explosion, the facility comprising: - a chamber (3) configured to contain the explosion, the chamber comprising two longitudinal bottoms (31) each provided with a door for accessing the inside of the chamber, and a body (33) extending between the longitudinal bottoms; and - shielding (5), located inside the chamber, configured to protect the chamber from the fragments produced by the explosion and defining an internal treatment space (VT) that opens onto each longitudinal bottom, the shielding extending along the body at a distance therefrom and resting on positioning elements (7) located beneath the shielding so as to create, between the body and the shielding, an accessible circumferential space (VC) that opens onto each longitudinal bottom.
An adjustable automatic valve and a supply circuit, the valve comprising: a first flow chamber (12); a second flow chamber (13) that communicates with the first flow chamber (12) via a flow orifice (15) that forms a valve seat; a linear-stroke actuator (20); a control rod (24) that extends axially into the first flow chamber (12); a valve gate (25) that is movable between a closed position and an open position; and a spring (50), which is mounted in series with the actuator (20), for controlling the position of the control rod (24).
F16K 1/14 - Lift valves, i.e. cut-off apparatus with closure members having at least a component of their opening and closing motion perpendicular to the closing faces with ball-shaped valve members
F16K 17/04 - Safety valvesEqualising valves opening on surplus pressure on one sideSafety valvesEqualising valves closing on insufficient pressure on one side spring-loaded
F16K 17/168 - Safety valvesEqualising valves opening on surplus pressure on one sideSafety valvesEqualising valves closing on insufficient pressure on one side combined with manually-controlled valves, e.g. a valve combined with a safety valve
F16K 41/10 - Spindle sealings with diaphragm, e.g. shaped as bellows or tube
F02M 47/02 - Fuel-injection apparatus operated cyclically with fuel-injection valves actuated by fluid pressure of accumulator-injector type, i.e. having fuel pressure of accumulator tending to open, and fuel pressure in other chamber tending to close, injection valves, and having means for periodically releasing that closing pressure
F02M 63/00 - Other fuel-injection apparatus having pertinent characteristics not provided for in groups or Details, component parts or accessories of fuel-injection apparatus, not provided for in, or of interest apart from, the apparatus of groups or
F16K 1/30 - Lift valves, i.e. cut-off apparatus with closure members having at least a component of their opening and closing motion perpendicular to the closing faces specially adapted for pressure containers
F16K 31/126 - Operating meansReleasing devices actuated by fluid the fluid acting on a diaphragm, bellows, or the like
B64D 37/00 - Arrangements in connection with fuel supply for power plant
A valve for a cryogenic fluid and a supply circuit for a cryogenic fluid, the valve comprising: a control chamber (11); a first flow chamber (12) that communicates with the control chamber (11) via a control orifice (14); a second flow chamber (13) that communicates with the first flow chamber (12) via a flow orifice (15) that forms a valve seat; a linear-stroke actuator (20) that is accommodated in the control chamber (11) and configured to actuate a control rod (24) which penetrates the control orifice (14) and extends axially into the first flow chamber (12); a valve gate (25) that is movable between a closed position and an open position; and bellows (30) that surround the control rod (24) and are sealed while being axially stretchable.
F16K 1/14 - Lift valves, i.e. cut-off apparatus with closure members having at least a component of their opening and closing motion perpendicular to the closing faces with ball-shaped valve members
F16K 1/30 - Lift valves, i.e. cut-off apparatus with closure members having at least a component of their opening and closing motion perpendicular to the closing faces specially adapted for pressure containers
F02M 47/02 - Fuel-injection apparatus operated cyclically with fuel-injection valves actuated by fluid pressure of accumulator-injector type, i.e. having fuel pressure of accumulator tending to open, and fuel pressure in other chamber tending to close, injection valves, and having means for periodically releasing that closing pressure
F02M 63/00 - Other fuel-injection apparatus having pertinent characteristics not provided for in groups or Details, component parts or accessories of fuel-injection apparatus, not provided for in, or of interest apart from, the apparatus of groups or
B64D 37/00 - Arrangements in connection with fuel supply for power plant
13.
METHOD AND DEVICE FOR TRACKING SATELLITES IN AN IMAGE SEQUENCE
The present invention relates to a method and a device (APP) for tracking satellites in an image sequence (IMG_SEQ). In particular, the method comprises: - a step of obtaining a set of measurements (SIN) associated with space objects observed in the images of the sequence (IMG_SEQ), each measurement comprising a position of an object in an image and a time index of the image; - a step of detecting satellite trajectories (TRJ) in the image sequence (IMG_SEQ) by means of a detector (DET) comprising at least one neural network and using all or part of the obtained set of measurements (SIN); and - a step of classifying the detected satellite trajectories (TRJ) by means of a classifier (CLA) comprising at least one other neural network.
The invention relates to a method for infusing a fibre preform with a polycondensation resin, the method comprising at least: A) supplying an intermediate container (13) with a resin at a pressure higher than atmospheric pressure, the supplying operation comprising at least: A1) transferring the resin (20) from the initial container (11) to a heater (12); A2) heating the resin using the heater; and A3) transferring the heated resin (22) to the intermediate container (13); B) infusing the fibre preform (14) with the thus-transferred polycondensation resin by means of suction from the intermediate container which is kept at an infusion temperature higher than or equal to the injection temperature; the intermediate container being supplied at a pressure higher than or equal to 1.5 bar absolute and the fibre preform being infused at a pressure lower than or equal to 0.1 bar absolute.
B29C 70/44 - Shaping or impregnating by compression for producing articles of definite length, i.e. discrete articles using isostatic pressure, e.g. pressure difference-moulding, vacuum bag-moulding, autoclave-moulding or expanding rubber-moulding
B29C 70/48 - Shaping or impregnating by compression for producing articles of definite length, i.e. discrete articles using matched moulds, e.g. for deforming sheet moulding compounds [SMC] or prepregs and impregnating the reinforcements in the closed mould, e.g. resin transfer moulding [RTM]
C08K 5/107 - EstersEther-esters of monocarboxylic acids with phenols with polyphenols
C08G 8/04 - Condensation polymers of aldehydes or ketones with phenols only of aldehydes
C07D 307/77 - Heterocyclic compounds containing five-membered rings having one oxygen atom as the only ring hetero atom ortho- or peri-condensed with carbocyclic rings or ring systems
15.
METHOD FOR EXTRACTING A SOLID ENERGETIC MATERIAL FROM CONTAMINATED SOIL
The present invention relates to a method for extracting a solid energetic material from contaminated soil comprising a mixture of the energetic material with plant substances, mineral aggregates and metal parts, the method comprising: - a sieving and washing of the contaminated soil to recover said mixture and to remove the earth and the sand possibly present, - a first densimetric separation between a light fraction comprising the plant substances and a heavy fraction comprising the energetic material, the mineral aggregates and the metal parts, by immersing the mixture thus recovered in a water bath, - an extraction of the heavy fraction obtained during the first densimetric separation, - a drying or draining of the heavy fraction thus extracted, - a second densimetric separation between the energetic material on the one hand and the mineral aggregates and the metal parts on the other hand, by immersing the heavy fraction thus dried or drained into a brine bath of an alkali metal formate, said brine having a density higher than that of the energetic material and lower than each of the densities of the metal parts and of the mineral aggregates, and - an extraction of the energetic material obtained as a result of the second densimetric separation.
CENTRE NATIONAL DE LA RECHERCHE SCIENTIFIQUE (France)
UNIVERSITE CLAUDE BERNARD LYON 1 (France)
Inventor
Joucla, Lionel
Gasnier, Gwénaël
Comte, Sébastien
Silva Costa, Raphaël
Abstract
A method for producing the pentazolate anion, includes at least the oxidation of a phenolic arylpentazole by a particular hypervalent iodine oxidant in the presence of a base.
The invention relates to a casing for a rotary machine, comprising a solid first wall (21) delimiting an inner space (11) of the casing (10), a solid second wall (22) extending opposite the first wall (21) on the outer side thereof, and a porous filling portion (31) extending between the first wall (21) and the second wall (22), wherein the first wall (21), the second wall (22) and the filling portion (31) are produced jointly and integrally by an additive manufacturing technique.
The invention relates to a fluid connection flange for rigidly and sealingly connecting a hydraulic member, comprising: a solid first wall (21) forming a bearing surface (21a) intended to be applied against an attachment surface; a solid second wall (22) provided facing the first wall (21); at least one solid, cylindrical spacer (23) extending perpendicularly between the first and the second wall (21, 22), forming a passage (24) intended to allow a rod (3a) of an attachment member (3) to pass therethrough; and a porous filling portion (31), extending between the first wall (21) and the second wall (22), outside the spacers (23), wherein the first wall (21), the second wall (22), the at least one spacer (23) and the filling portion (31) are produced jointly and integrally by an additive manufacturing technique.
CENTRE NATIONAL DE LA RECHERCHE SCIENTIFIQUE (France)
UNIVERSITE CLAUDE BERNARD LYON 1 (France)
Inventor
Fournier, Maylis
Terreux, Raphaël
Defoort, Brigitte
Jacob, Guy
Abstract
The invention relates to a method for evaluating a prediction of a result of a property of a molecule referred to as the predicted molecule, the property being one among genotoxicity, mutagenicity and carcinogenicity, the method comprising the following steps: obtaining (S100) the prediction of the result of the property of the predicted molecule, the prediction being determined by a model on the basis of a first sub-set of a set of molecules; determining (S200) at least two values among a value representative of a consistency, for the property, of the results of the molecules of the sub-set with said prediction; a value representative of a co-similarity of the molecules within the sub-set; and a value representative of a capacity of the model to predict the result of the property of the predicted molecule; and determining (S300), by means of a fuzzy logic inference algorithm, a value representative of the reliability of the prediction of the property result of the predicted molecule.
The invention relates to a method for manufacturing a stiffened cylindrical part (1000), comprising: - positioning a precursor assembly of the part to be manufactured in tooling (30), the assembly being made of thermoplastic pre-impregnated fibrous material and comprising (i) a sectorized cylinder, and (ii) stiffening elements present on an inner surface of the cylinder, the tooling comprising an inner part (32) covered with a vacuum bag (34), situated facing the inner surface of the cylinder, and on which the assembly is positioned, and a molding outer part (60) of cylindrical shape, situated facing an outer surface (S2) of the cylinder, and - shaping the assembly on the molding outer part and securing the stiffening elements on the inner surface of the cylinder by co-consolidation by pulling a vacuum in the molding tooling, in order to obtain the part made from composite material to which the stiffening elements are secured.
B29C 70/30 - Shaping by lay-up, i.e. applying fibres, tape or broadsheet on a mould, former or coreShaping by spray-up, i.e. spraying of fibres on a mould, former or core
B29C 70/34 - Shaping by lay-up, i.e. applying fibres, tape or broadsheet on a mould, former or coreShaping by spray-up, i.e. spraying of fibres on a mould, former or core and shaping or impregnating by compression
B29C 70/44 - Shaping or impregnating by compression for producing articles of definite length, i.e. discrete articles using isostatic pressure, e.g. pressure difference-moulding, vacuum bag-moulding, autoclave-moulding or expanding rubber-moulding
B29D 99/00 - Subject matter not provided for in other groups of this subclass
The present invention relates to a method for manufacturing a tank (1) made of composite material, in which a precursor assembly made of thermosetting pre-impregnated fibrous material is fired under vacuum in a tool (30), the moulding parts of which are external to the assembly in order to facilitate subsequent removal from the mould. The assembly comprises a body-precursor cylinder (100) closed by two bottom-precursor domes (200) which are rigidly connected to the cylinder by co-firing. The invention is of particular interest in the production of large tanks.
B29C 70/30 - Shaping by lay-up, i.e. applying fibres, tape or broadsheet on a mould, former or coreShaping by spray-up, i.e. spraying of fibres on a mould, former or core
B64G 1/40 - Arrangements or adaptations of propulsion systems
B29C 70/44 - Shaping or impregnating by compression for producing articles of definite length, i.e. discrete articles using isostatic pressure, e.g. pressure difference-moulding, vacuum bag-moulding, autoclave-moulding or expanding rubber-moulding
B29D 99/00 - Subject matter not provided for in other groups of this subclass
B29C 70/38 - Automated lay-up, e.g. using robots, laying filaments according to predetermined patterns
A system for recovering compression energy from a gas, the system comprising an organic Rankine cycle module and an adiabatic compressor, the organic Rankine cycle module comprising a heat transfer fluid and the adiabatic compressor comprising N adiabatic compression stages for the gas, N being greater than or equal to 2, and, downstream of each adiabatic compression stage, two heat exchangers, a first heat exchanger configured to extract heat from the gas leaving the adiabatic compression stage and to heat the heat transfer fluid passing through the first heat exchanger and a second heat exchanger configured to extract heat from the gas leaving the first heat exchanger to a cold source passing through the second heat exchanger. A liquefier comprising such a system and method for recovering compression energy from a gas.
F25J 1/02 - Processes or apparatus for liquefying or solidifying gases or gaseous mixtures requiring the use of refrigeration, e.g. of helium or hydrogen
F25J 1/00 - Processes or apparatus for liquefying or solidifying gases or gaseous mixtures
CENTRE NATIONAL DE LA RECHERCHE SCIENTIFIQUE (France)
UNIVERSIE DE RENNES 1 (France)
Inventor
Attaja, Nicolas
Ettorre, Mauro
Sauleau, Ronan
Guihard, Davy
Abstract
Antenna includes at least one first resonant cavity and a second resonant cavity, each resonant cavity being closed by a base at one end and including a radiating element superimposed on the base of the resonant cavity, the radiating element of the first cavity being able to transmit a signal on a first frequency band and the radiating element of the second cavity being able to transmit a signal on a second frequency band separate from the first frequency band, characterized in that a first distance between the base and radiating element of the first cavity differs from a second distance between the base and radiating element of the second cavity.
A method for cutting, in a non-through manner, a body of a thruster of an aerospace vehicle, water jets, the method including a plurality of passes of a high-pressure water jet along the same cutting path extending across the external perimeter of the thruster body, the cutting path describing a closed loop circuit, and each water jet pass starting from a starting point located on the cutting path and stopping just after returning on the starting location. The starting point of each high-pressure water jet pass is different from the starting points of the other water jet passes.
B24C 1/04 - Methods for use of abrasive blasting for producing particular effectsUse of auxiliary equipment in connection with such methods for treating only selected parts of a surface, e.g. for carving stone or glass
B26F 3/00 - Severing by means other than cuttingApparatus therefor
25.
Cryogenic regulating valve for aircraft or spacecraft
Regulating valve with a rack and pinion transmission system for an aircraft or a spacecraft, including a valve body, a transmission shaft, a rolling element, a rack of the rolling element being engaged with a pinion of the shaft, a first end of the rolling element being guided in translation by a first bearing, and a second end of the rolling element being guided in translation by a second bearing, the valve including an annular connecting flange fixed to the valve body, the annular connecting flange radially extending between an axisymmetric inner face about a second axis of the rolling element and an axisymmetric outer face about a central axis, the inner face including a radially inner housing in which the second bearing is housed, the second axis being radially offset with respect to the central axis.
F16K 31/54 - Mechanical actuating means with toothed gearing with pinion and rack
F16K 3/26 - Gate valves or sliding valves, i.e. cut-off apparatus with closing members having a sliding movement along the seat for opening and closing with sealing faces shaped as surfaces of solids of revolution with cylindrical valve members with fluid passages in the valve member
The invention relates to a heating installation (150) for an aircraft, the installation being arranged between a dihydrogen tank (104) and an engine (108) with a first supply pipe (152a) connected to the tank (104) and a second supply pipe (152b) connected to the engine (108) and comprising two branch pipes (154a-b) connected in parallel between the first supply pipe (152a) and the second supply pipe (152b), wherein a first valve (156a-b), a heating system (158a-b) and a second valve (160a-b) are mounted, in series, from upstream to downstream, on each branch pipe (154a-b) .
F02C 3/22 - Gas-turbine plants characterised by the use of combustion products as the working fluid using a special fuel, oxidant, or dilution fluid to generate the combustion products the fuel or oxidant being gaseous at standard temperature and pressure
F02C 7/224 - Heating fuel before feeding to the burner
27.
METHOD FOR DETERMINING THE ELECTRIC POTENTIALS OF THE PHASES OF A POLYPHASE MOTOR
The invention relates to a method (100) for determining the potentials (Vi) at the terminals of the N phases of a motor, N being an integer greater than or equal to 4, which method comprises: - determining (102) reference potentials (VREF_i) at the terminals of the N phases for a defined control voltage VMAG (101) of phase θ, where i is between 1 and N, using formula (I) - comparing (103) the reference potentials with a first threshold (threshold 1); - if the reference potentials are all less than or equal to the first threshold (104), then the potentials at the terminals of the N phases are equal to the reference potentials, or if at least one of the reference potentials is greater than the first threshold, comparing (105) these potentials to a second threshold (threshold 2) that is greater than the first threshold; - if all of these reference potentials are all less than or equal to the second threshold (106), then the potentials at the terminals of the N phases are Vi = VREF_i + VH, using formula (II), or if at least one of the potentials is greater than the second threshold (107), then the potentials at the terminals of the N phases are Vi = VREF_i + VS_i + VHN, where VHN and VS_i are dependent on N and the reference potentials.
H02P 27/06 - Arrangements or methods for the control of AC motors characterised by the kind of supply voltage using variable-frequency supply voltage, e.g. inverter or converter supply voltage using DC to AC converters or inverters
The invention relates to a solid composite propellant comprising: 5.0% to 20.0% by mass of a polyurethane crosslinked binder, which is the reaction product of a polyester polyol and a polyisocyanate crosslinking agent, in the presence of a crosslinking catalyst; 20.0% to 90.0% by mass of ammonium perchlorate; optionally up to 25.0% by mass of aluminum; optionally up to 5.0% by mass of a ballistic catalyst; optionally up to 20.0% by mass of at least one additive.
C06B 29/22 - Compositions containing an inorganic oxygen-halogen salt, e.g. chlorate, perchlorate the salt being ammonium perchlorate
C06B 33/06 - Compositions containing particulate metal, alloy, boron, silicon, selenium or tellurium with at least one oxygen supplying material which is either a metal oxide or a salt, organic or inorganic, capable of yielding a metal oxide the material being an inorganic oxygen-halogen salt
C06B 45/10 - Compositions or products which are defined by structure or arrangement of component or product comprising solid particles dispersed in solid solution or matrix the solid solution or matrix containing an organic component the organic component containing a resin
The invention relates to a device for separating a second part (14) from a first part (12), comprising a first interface (16) intended to be attached to the first part and a second interface (18) intended to be attached to the second part, a lashing stud (20) passing through the first and second interfaces and being held at the first interface by a separation nut (22) and at the second interface by a first nut/locknut assembly (24), the lashing stud being covered by a cap (26) integral with the second interface and intended to receive the stud once the separation nut has been broken and the first and second interfaces have been separated, and a retraction spring (28) is provided for extracting the lashing stud from the first interface, propelling it towards a damping material (36) attached to the bottom of the cap and keeping it there solely by its residual holding force.
09 - Scientific and electric apparatus and instruments
42 - Scientific, technological and industrial services, research and design
Goods & Services
Software in the aerospace and aeronautical field; software
in the field of propelled projectiles, machinery or vehicles
for civil or military use. Computer engineering; design, development, maintenance and
updating of software in the aerospace and aeronautical field
and of software in the field of propelled projectiles,
machinery or vehicles for civil or military use.
31.
ANNULAR ENCLOSURE FOR AN INTERMEDIATE STAGE OF AN AEROSPACE LAUNCHER WITH FALL RETARDER
The invention relates to an annular enclosure (10) for an intermediate stage of a multi-stage aerospace launcher, the annular enclosure (10) comprising at least two segments (12) together forming a ring defining an axial direction (DA), a radial direction (DR) and a circumferential direction (DC). Each segment (12) of the annular enclosure (10) comprises: - a first panel (16) and a second panel (18) each comprising a first circumferential end (16a, 18a) and a second circumferential end (16b, 18b), - a hinge (14) mechanically coupling the first circumferential end (16a) of the first panel (16) to the first circumferential end (18a) of the second panel (18) and configured to fold the first panel (16) towards the second panel (18) when the enclosure segment (12) is detached from the annular enclosure (10).
CENTRE NATIONAL D'ETUDES SPATIALES (CNES) (France)
Inventor
Pyanet, Marine
Joffre, Théo
Richard, Pascal
Abstract
The invention relates to a space surveillance method for detecting space objects in orbit around the Earth in images captured during the daytime, the method comprising the following steps: - capturing (100) a plurality of infrared images of the daytime sky using an imaging device comprising at least one infrared sensor - detecting (140 and 150) space objects in orbit around the Earth on the basis of the images, the detection of light points being carried out by a deep-learning artificial intelligence system; - identifying (160) each detected object using a catalogue of space objects known to be in orbit around the Earth.
G06V 10/143 - Sensing or illuminating at different wavelengths
G06V 10/50 - Extraction of image or video features by performing operations within image blocksExtraction of image or video features by using histograms, e.g. histogram of oriented gradients [HoG]Extraction of image or video features by summing image-intensity valuesProjection analysis
G06V 10/75 - Organisation of the matching processes, e.g. simultaneous or sequential comparisons of image or video featuresCoarse-fine approaches, e.g. multi-scale approachesImage or video pattern matchingProximity measures in feature spaces using context analysisSelection of dictionaries
G06V 10/82 - Arrangements for image or video recognition or understanding using pattern recognition or machine learning using neural networks
A seat system for use in a crew escape system of a space transport vehicle comprises a seat having a backrest with a supporting surface. The seat is configured to be installed in a cabin area of the crew escape system so it can rotate about a first axis between a first position where the seat faces a first direction, and a second position where faces a second direction that is opposed to the first direction. The seat system further comprises a control unit configured to control a rotation of the seat at least between the first position and the second position in dependence on at least one signal which is indicative of a trajectory of the crew escape system.
A reusable orbital vehicle (14) for a space transport system (10) comprises a fuselage (22) the shape of which widens in a direction extending from the front end (24) of the reusable orbital vehicle to a rear end (26) of said fuselage (22) and inside which there is defined a housing (32), and a crew-evacuation vehicle (34) housed in said housing (32) and oriented in such a way as to be extracted from the housing (32) in a direction (D1) directed from said rear end (26) of the fuselage (22) toward said front end (24) of the reusable orbital vehicle (14).
A seat system (10) for use in a crew escape system (500) of a space transport vehicle (1000) comprises a seat (12) having a backrest (14) with a supporting surface (16) which, when the seat (12) is used by a crew member (106), is suitable to support an upper body of the crew member (106), and being configured to be installed in a cabin area (100) of the crew escape system (500) so as to be rotatable about a first axis (R1) at least between a first position, wherein the supporting surface (16) of the backrest (14) faces a first direction (D1), and a second position, wherein the supporting surface (16) of the backrest (14) faces a second direction (D2), the second direction (D2) being opposed to the first direction (D1). The seat system (10) further comprises a control unit (25) which is configured to control a rotation of the seat (12) at least between the first position and the second position in dependence on at least one signal which is indicative of a trajectory of the crew escape system (500).
B60N 2/14 - Seats specially adapted for vehiclesArrangement or mounting of seats in vehicles the seat or part thereof being movable, e.g. adjustable the whole seat being movable rotatable, e.g. to permit easy access
A space transportation system intended to be mounted on a space launcher comprising a re-ignitable propulsion device and steerable flaps located at a second end and a monitoring unit, each flap comprising an actuating means configured to modify the orientation of said flap, said monitoring unit being configured to control the activation of the propulsion device and individually control the orientation of the flaps in order to implement the following steps:
a launch step during which the propulsion device is off and the flaps are in a retracted position;
a return step during which the monitoring unit deploys the flaps and individually controls the orientation of the flaps to slow down the system, the propulsion device being off;
a landing step during which the monitoring unit controls the propulsion device and the actuating means to orient the flaps to slow down.
The invention relates to an assembly for producing braided structures of variable size, comprising: - a braiding machine (1000) defining a first guide path (100) on which a plurality of spindles (3) are movable, which guide path is defined by an assembly of drive modules (30) and first spacer modules (10), a first spacer module (10) being inserted between two drive modules (30) so as to space them apart by a first angular spacing; and - second spacer modules (20) capable of being removably assembled with all or some of the drive modules (30) by inserting a second spacer module (20) between two drive modules (30) so as to define a second guide path (200) and so as to space two consecutive drive modules (30) apart by a second angular spacing, the assembly being configured to obtain a braiding machine (2000) having a second size.
The invention relates to a braiding machine comprising: - a plurality of yarn feed spindles (30) movable along a guide path (100) so as to participate in the braiding, and - a reserve zone (20) able to receive at least one spindle (30) such that its participation in the braiding is interrupted.
D04C 3/38 - Driving-gearStarting or stopping mechanisms
D04C 3/30 - Devices for controlling spool carriers to obtain patterns, e.g. devices on guides or track plates by controlling switches of guides or track plates
09 - Scientific and electric apparatus and instruments
42 - Scientific, technological and industrial services, research and design
Goods & Services
(1) Logiciels dans le domaine aérospatial et aéronautique; logiciels dans le domaine des projectiles, engins ou véhicules propulsés à usage civil ou militaire. (1) Ingénierie informatique; conception (élaboration), développement, maintenance et mise à jour de logiciels dans le domaine aérospatial et aéronautique et de logiciels dans le domaine des projectiles, engins ou véhicules propulsés à usage civil ou militaire.
09 - Scientific and electric apparatus and instruments
42 - Scientific, technological and industrial services, research and design
Goods & Services
Software in the aerospace and aeronautical field; software in the field of propelled projectiles, machinery or vehicles for civil or military use Computer engineering; design, development, maintenance and updating of software in the aerospace and aeronautical field and of software in the field of propelled projectiles, machinery or vehicles for civil or military use
42.
METHOD FOR DETECTING DEFECTS DURING LASER ADDITIVE MANUFACTURING, DATA PROCESSING DEVICE, COMPUTER PROGRAM AND STORAGE MEDIUM FOR IMPLEMENTING THE METHOD
A method for detecting defects during laser additive manufacturing, comprising the following steps: B21) a first image is captured, the first image being the image, captured in the infrared spectrum, of an upper surface of a layer of powder exposed to laser scan; B23) the first image is processed using a first convolutional neural network of self-encoding type, in such a way as to produce a defect mask indicating the location of defects at the upper surface of the layer of powder. A method for manufacturing parts during which the presence of defects is detected using the preceding method. A data-processing device, computer program and storage medium for the implementation of this method.
The invention relates to a device (1) for monitoring objects in space orbit around the Earth, the device (1) comprising a frame (2), a plate (3), at least three optical monitoring modules (4), and a power supply and control unit (5) housed at least partially inside the frame (2). The plate (3) is mounted on the frame (2), and each optical monitoring module (4) is mounted on the plate (3) and comprises a rotary turret (400), an image sensor (408) mounted on the rotary turret (400) and a passive optical system (410) mounted on the inlet of the image sensor (408). The rotary turret (400) is configured to pivot over more than 360° about a first axis perpendicular to the plane in which the plate (3) extends and to pivot over 90° about a second axis perpendicular to the first axis and parallel to the plane in which the plate (3) extends.
A method for manufacturing an aerospace and/or aeronautical composite tubular part, the composite tubular part includes a tubular body and at least one flange. The method includes the following steps: providing at least one composite tubular body portion; forming at least one flange component from a second thermosetting material; a first heat treatment to partially polymerize the flange component or components; assembling the flange component or components on the composite tubular body; a second heat treatment of the composite assembly so as to polymerize both the at least one tubular body portion and the flange component or components. A composite tubular part is also provided.
determining that there is a fault on at least one of the sensors as a function of the residuals calculated based on data obtained from measurements returned by said sensor.
G01D 3/08 - Measuring arrangements with provision for the special purposes referred to in the subgroups of this group with provision for safeguarding the apparatus, e.g. against abnormal operation, against breakdown
46.
REFRIGERATION METHOD USING AN ARTIFICIAL NEURAL NETWORK
This disclosure relates to a method for chilling down a cryogenic fluid supply circuit comprising a step of acquiring a state value of the cryogenic fluid supply circuit at a current time, a step of computing a corresponding opening time of each out of one or more valves of the cryogenic fluid supply circuit, and a step of opening each valve at the corresponding time to chill down the cryogenic fluid supply circuit. The step of computing is carried out by a computer applying an artificial neural network to compute a sequence of opening of the valves making it possible to reach, starting from the state value of the cryogenic fluid supply circuit at the current time, a state of the cryogenic fluid supply circuit meeting one or more predetermined chill down criteria at a predetermined time in the future.
A method of tracking objects is based on the use of a LIDAR apparatus. This method includes in particular a step C) of tracking the object. Step C of tracking the object including in particular a sub-step of determining a tracking pattern to pass along by the probe laser beam along a perpendicular plane containing the estimated position of the object and which is perpendicular to a line passing via the estimated position of the object and the position of the LIDAR apparatus, at least one angular parameter of the tracking pattern in relation to the LIDAR apparatus being determined from the estimated position of the object, including in particular the distance between the object and the LIDAR apparatus.
The invention relates to a method for controlling a synchronous electric motor, the method comprising: generating (400) a torque reference based on a mechanical setpoint; measuring (405) the position and determining the speed of the motor; measuring (410) the current generated by the motor; generating (445) voltage references based on the torque reference; and generating (450) control voltages based on the reference voltages. It comprises: detecting an anomaly in the position measurement; adapting (440) the electrical control gains according to whether or not an anomaly in the position measurement of the electric motor has been detected; and the voltage references being dependent on the values of the electrical control gains.
H02P 21/24 - Vector control not involving the use of rotor position or rotor speed sensors
H02P 25/026 - Synchronous motors controlled by supply frequency thereby detecting the rotor position
H02P 25/03 - Synchronous motors with brushless excitation
H02P 29/024 - Detecting a fault condition, e.g. short circuit, locked rotor, open circuit or loss of load
H02P 29/028 - Detecting a fault condition, e.g. short circuit, locked rotor, open circuit or loss of load the motor continuing operation despite the fault condition, e.g. eliminating, compensating for or remedying the fault
The invention relates to a needling system (100) for producing a textile preform, the system comprising: a needling head (110); a robotic arm (120) that is movable in multiple degrees of freedom, bears the needling head and is configured so as to move the needling head along predetermined trajectories and in predetermined orientations; a device (130) for supplying a textile web, the device being mounted on the needling head and being configured to deposit the textile web on a support and to cut it; and a control unit (140) configured to control the robotic arm, the actuation of the needling head and the deposition of the textile web according to a predefined program for producing the textile preform.
G05B 19/408 - Numerical control [NC], i.e. automatically operating machines, in particular machine tools, e.g. in a manufacturing environment, so as to execute positioning, movement or co-ordinated operations by means of programme data in numerical form characterised by data handling or data format, e.g. reading, buffering or conversion of data
50.
DEVICE FOR SUPPORTING A FLUID-CIRCULATION DUCT, AND ASSEMBLY COMPRISING SUCH A DEVICE AND SUCH A DUCT
A device (20) for supporting a fluid duct (C), comprising: - a link (22) for supporting the duct via two end parts (22a) of the link that are spaced apart from one another in a longitudinal direction and adopting, transversely, a curved shape for supporting a portion (Ca) of the duct, the two end parts (22a) being connected to one another by two intermediate parts of the link that each connect one end (22a1, 22a2) of the two end parts (22a), - two links (24, 26) for fastening the device (20) to an external structure, - two connection elements (28b-d) connecting the supporting link (22) and the fastening links (24, 26) and each traversed by a fastening link and an intermediate part of the supporting link and allowing these links to slide through the connection element.
F02K 9/84 - Rocket-engine plants, i.e. plants carrying both fuel and oxidant thereforControl thereof characterised by thrust or thrust vector control using movable nozzles
The disclosure includes a sealed device having a seal around an internal chamber, the seal having at least two closed-loop portions through which a through element extends.
Structure intended to stiffen a component made of thermosetting composite material by being fitted to at least one of its surfaces, including: at least one longitudinal body, with first and second longitudinal edge faces on opposite sides, and first and second lateral faces on opposite sides; at least one base including at least one mounting base, each base having a plate and first and second tongues which delimit, with the plate, a housing for at least one body, the first and second tongues extending from a main face of the plate and being pressed respectively against the first and second lateral faces of the body. Each mounting base has a plate which is secured to the first longitudinal edge face of a body and which is intended to be pressed against the surface of the component to be stiffened. Each body and each base are made of thermosetting composite material.
B29C 70/68 - Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts by incorporating or moulding on preformed parts, e.g. inserts or layers
B29C 70/84 - Moulding material on preformed parts to be joined
H01Q 1/28 - Adaptation for use in or on aircraft, missiles, satellites, or balloons
53.
STIFFENED PART FORMED FROM A THERMOSET COMPOSITE MATERIAL WITH A BOXED STRUCTURE AND MANUFACTURING METHOD
A stiffened part formed from at least two members of thermoset composite material including at least one body of a first structure and optionally a second structure. A manufacturing method includes: forming a fibre preform and impregnating each body of the first structure with thermosetting resin or forming a pre-impregnated fibre preform to obtain a body formed from uncured thermosetting composite material supported by a mandrel; optionally partially or fully polymerising at least one body supported by a mandrel; optionally, providing the second structure formed from uncured, partially uncured or fully uncured thermosetting composite material; optionally, depositing a layer of uncured thermosetting adhesive on an area where a fully cured member makes contact with another member of the part; joining the members, each member being juxtaposed with; or stacked upon, at least one other member; fully curing the assembly by heat treatment; removing the mandrel from each fully cured body.
B29C 70/86 - Incorporating in coherent impregnated reinforcing layers
B29C 70/32 - Shaping by lay-up, i.e. applying fibres, tape or broadsheet on a mould, former or coreShaping by spray-up, i.e. spraying of fibres on a mould, former or core on a rotating mould, former or core
B29C 70/68 - Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts by incorporating or moulding on preformed parts, e.g. inserts or layers
B29C 70/02 - Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts comprising combinations of reinforcements and fillers incorporated in matrix material, forming one or more layers, with or without non-reinforced or non-filled layers
Valve designed for large flow rates and high pressures, and a rocket engine comprising such a valve, the valve comprising a valve body (11), having a first path (I) and a second path (II), a movable shut-off member (40) configured to adjust the flow cross section between the first path (I) and the second path (II), and an electrical actuator (50) configured to adjust the position of the shut-off member (40), wherein the shut-off member (40) is able to move linearly between a first position and a second position, wherein the actuator (50) comprises a rotor (51) installed in a service cavity (15) of the valve body (11), the service cavity (15) being in fluidic communication with the first path (I) or the second path (II), and wherein the actuator (50) is configured to move the shut-off member (40) via a rotary-linear transmission member (60).
F16K 1/12 - Lift valves, i.e. cut-off apparatus with closure members having at least a component of their opening and closing motion perpendicular to the closing faces with streamlined valve member around which the fluid flows when the valve is opened
F02K 9/00 - Rocket-engine plants, i.e. plants carrying both fuel and oxidant thereforControl thereof
F16K 31/04 - Operating meansReleasing devices electricOperating meansReleasing devices magnetic using a motor
F02K 9/48 - Feeding propellants using pumps driven by a gas turbine fed by propellant combustion gases
F02K 9/60 - Constructional partsDetails not otherwise provided for
12 - Land, air and water vehicles; parts of land vehicles
37 - Construction and mining; installation and repair services
39 - Transport, packaging, storage and travel services
42 - Scientific, technological and industrial services, research and design
Goods & Services
Apparatus for locomotion by air, namely, aerospace vehicles,
thrusters for vehicles, namely, rockets and rockets equipped
with a space vehicle and spacecraft, space vehicles and
craft suitable for atmospheric re-entry; apparatus for
locomotion in outer space, multi-mission aerospace vehicle
and spacecraft, namely, used for freight, satellite
positioning, manned flights or space exploration; space
transport vehicles and craft, particularly reusable, and
parts and components thereof; air transport vehicles and
craft, particularly reusable, and parts and components
thereof; crew evacuation vehicle for air vehicles and craft,
particularly reusable; crew evacuation vehicle for space
vehicles and craft, particularly reusable; air and space
transport vehicles and craft comprising a crew evacuation
device; launch vehicles for aerospace vehicles and rockets;
braking devices for air vehicles and space vehicles and
craft suitable for atmospheric re-entry. Maintenance and repair of aerospace vehicles and craft,
particularly reusable aerospace vehicles and aerospacecraft;
spacecraft and space station refueling services. Space transport services, air transport by means of
aerospace vehicles and craft; launching air vehicles, space
vehicles, rocket boosters, aerospace vehicles and craft
suitable for atmospheric re-entry; space transport of
merchandise, people, satellites and aerospacecraft;
emplacement, mooring, docking and parking of space vehicles
and craft; chartering aircraft, aerospace vehicles;
satellite launch services; recovery (towing) of aerospace
vehicles and craft, particularly reusable. Engineering services in the fields of aeronautics,
aerospace, aerospace vehicles and craft, space transport
vehicles particularly for the re-use of space vehicles and
craft suitable for atmospheric re-entry, on-board propulsion
systems, composite materials, energy equipment, guidance,
navigation and course control systems (GNC) and landing,
safety and flight protection systems for people; analysis
and expertise services in the field of aeronautics,
aerospace, space transport vehicles particularly for re-use,
space vehicles and craft suitable for atmospheric re-entry,
on-board propulsion systems, composite materials, energy
equipment, guidance, navigation and course control systems
(GNC) and landing; scientific and industrial research in the
fields of aerospace, aeronautics, space transport vehicles
particularly for the re-use of space vehicles and craft,
on-board propulsion systems, composite materials, guidance,
navigation and course control systems (GNC) and landing;
technical project studies; testing of machines; testing of
materials; aircraft and spacecraft flight tests; testing of
aerospace vehicle systems, equipment and parts; technical
inspection of systems, equipment and parts of aerospace
vehicles; analysis, expertise and processing of the
acquisition of technical data recorded during the systems
test campaign, during air and space missions, equipment and
parts of aerospace vehicles; developing and designing
reusable space transportation vehicles, space vehicles and
craft suitable for atmospheric re-entry, on-board propulsion
systems, composite materials, guidance, navigation and
course control (GNC) and landing systems; designing space
vehicles.
56.
Circuit for supplying fuel to an aeronautical cryogenic turbomachine and associated method
A fuel supply circuit for an aeronautical cryogenic turbomachine including: at least one cryogenic reservoir containing a liquid fuel topped with a boil-off gas and including a high-pressure liquid pump to supply at least one main propulsion device of the turbomachine with liquid fuel, an auxiliary turbomachine including an electric generator, a gas compressor to supply the auxiliary turbomachine with gaseous fuel, and a buffer gas reservoir connecting the gas compressor to the cryogenic reservoir to reinject gas into the cryogenic reservoir in order to maintain the pressure in the cryogenic reservoir above a predefined value, the electric generator supplying the high-pressure liquid pump and the gas compressor.
F02C 7/224 - Heating fuel before feeding to the burner
F02C 3/20 - Gas-turbine plants characterised by the use of combustion products as the working fluid using a special fuel, oxidant, or dilution fluid to generate the combustion products
F02C 7/14 - Cooling of plants of fluids in the plant
F02C 6/20 - Adaptations of gas-turbine plants for driving vehicles
F02C 9/40 - Control of fuel supply specially adapted to the use of a special fuel or a plurality of fuels
F02C 9/36 - Control of fuel supply characterised by returning of fuel to sump
57.
ORBITAL DEPLOYMENT MODULE WITH A THREE-POINT SPACE PROPULSION SYSTEM
The invention relates to a three-point propulsion system (1) for an orbital-deployment space module (10) for at least one satellite, comprising: - a frame (2) comprising precisely three first recesses (6) each shaped to receive one propulsion unit (3) and also comprising at least one second recess (7) shaped to receive a tank (4), - at least one tank (4) for liquid fuel arranged in a second recess (7), and - precisely three propulsion units (3), each propulsion unit (3) being arranged in one of the first recesses (6), and each propulsion unit (3) comprising at least one thruster (30).
A method for recovering ammonium perchlorate from a solid composite propellant, the method being carried out at a temperature of less than 50° C. involving maceration of solid composite propellant fragments in the form of an aqueous suspension, the method being terminated when the ionic conductivity in the aqueous suspension reaches a stabilized value, of less than 60 mS/cm.
The invention relates to a method for assembling a first metal part with a second part made of an organic matrix composite material, the first part having a first connecting portion and the second part having a second connecting portion, the method comprising the steps of:
causing the first connecting portion and the second connecting portion to overlap, a through-hole of the second connecting portion opening onto the first connecting portion,
forming a protective layer on the side wall of the through-hole,
forming a seal between the protective layer and the first connecting portion, and
forming, by additive manufacturing using cold gas spray deposition of metal powder, a fastening element which extends into the through-hole, is fastened to the first connecting portion and encloses the second connecting portion.
A system for conditioning fuel for an air-breathing hydrogen engine (M), comprising: • - at least one hydrogen pump (16) configured to increase the pressure of the liquid hydrogen delivered at the outlet of a tank, • - one or more heat exchangers (24, 26, 28) configured to increase the temperature of the pressurized hydrogen, • - an air supply circuit (10G), • - at least one combustion device (32) configured to provide partial combustion of the hydrogen with the air coming from the air supply circuit in order to produce a fuel comprising a mixture of gas including gaseous hydrogen and not including oxygen.
F02K 9/42 - Rocket-engine plants, i.e. plants carrying both fuel and oxidant thereforControl thereof using liquid or gaseous propellants
F02K 9/78 - Rocket-engine plants, i.e. plants carrying both fuel and oxidant thereforControl thereof combined with another jet-propulsion plant with an air-breathing jet-propulsion plant
The invention relates to a device (200) for liquefying a gas (51), the device comprising: - a circuit (55) for conveying gas to be liquefied, the circuit comprising at least one heat exchanger (204) for exchanging heat between the gas (51) to be liquefied and a refrigerant flow (52) comprising at least dihydrogen refrigerant; - a closed refrigeration circuit (210) configured to convey the refrigerant flow, the closed refrigeration circuit comprising a means (215) for maintaining an internal composition of the dihydrogen refrigerant at a ratio of parahydrogen to orthohydrogen that is lower or higher than the ratio corresponding to a natural equilibrium composition in the refrigerant flow closed circuit, the means (215) comprising a catalytic reactor (220) configured to convert some of the orthohydrogen from the dihydrogen refrigerant flow into parahydrogen or vice versa.
The invention relates to an electrolytic system (1) for the synthesis of sodium perchlorate by electrochemical oxidation of sodium chlorate, said system comprising at least: - an electrolytic cell (3) defining a synthesis volume (V) and comprising an anode (5), which has an outer surface made of boron-doped diamond, a cathode (7), which has an outer surface made of stainless steel or graphite, and also a seal (9), which is between the anode and the cathode and defines the synthesis volume, the electrolytic cell having an inlet port (71), which is made through the cathode or the anode and is in communication with the synthesis volume, and an outlet port (73), which is made through the cathode or the anode and is in communication with the synthesis volume; - an assembly for the storage and circulation of an electrolyte, comprising: • a storage tank (10) which contains an electrolyte (12) comprising sodium chlorate and is in communication with the inlet port via an inlet pipe (14) intended for the introduction of the electrolyte into the synthesis volume, and • an outlet pipe (40) which is in communication with the outlet port intended for discharging the electrolyte from the synthesis volume; and - an electric generator connected to the anode and to the cathode.
The present invention relates to a method for preparing 3,5-dinitropyrazole, comprising a step involving obtaining N-acetyl-3-nitropyrazole from pyrazole, and a step involving the sigmatropic rearrangement of the compound obtained.
characterized in that the receiving element further comprises at least one additional cavity separate from the receiving cavity and linked to said receiving cavity by at least one channel, said at least one channel being open when the conductive element is broken by the piston.
The invention relates to a piece comprising a first metal part and a second part made of an organic matrix composite material, in which the first part has a first connecting portion and the second part has a second connecting portion, the second connecting portion having at least one blind hole, the second connecting portion being totally or partially sandwiched between the first connecting portion and a metal fastening element, the fastening element being fastened to the first part on a portion other than the first connecting portion and extending into the at least one blind hole, whereby the first part and the second part are fastened to one another.
Piece comprising a first metal part and a second part in organic matrix composite material, wherein the first part has a first connecting portion and the second part has a second connecting portion, the second connecting portion having at least one through-hole, the second connecting portion being totally or partially sandwiched between the first connecting portion and a metal fastening element, the fastening element being fastened on the first part both onto the first connecting portion via the through-hole of the second connecting portion and onto a portion other than the first connecting portion, whereby the first part and the second part are fastened to each other.
B22F 10/25 - Direct deposition of metal particles, e.g. direct metal deposition [DMD] or laser engineered net shaping [LENS]
B22F 5/00 - Manufacture of workpieces or articles from metallic powder characterised by the special shape of the product
B22F 7/06 - Manufacture of composite layers, workpieces, or articles, comprising metallic powder, by sintering the powder, with or without compacting of composite workpieces or articles from parts, e.g. to form tipped tools
B33Y 80/00 - Products made by additive manufacturing
Cryogenic turbopump feed line, comprising a main channel able to transport a cryogenic fluid, a plurality of secondary channels parallel to and disposed around the main channel in which the plurality of secondary channels are disposed on the periphery of an external perimeter of the main channel.
The invention relates to a resistive thermal flux meter (1) with compensated thermal drift, comprising a substrate (2) on which is deposited a Wheatstone bridge (3), the Wheatstone bridge (3) being deposited using a thin-film deposition process and comprising two first resistive branches (4) formed in a first film (6) and two second resistive branches (5) formed in a second film (7), the first and second films (6, 7) being separated by a silica film (8) deposited using a thin-film deposition process. It further comprises four compensation resistors (9), each compensation resistor (9) being coupled in parallel with one distinct resistive branch (4, 5) of the Wheatstone bridge (3), an equivalent resistor of each resistive branch having a temperature-variation coefficient equivalent to that of the other resistive branches (4, 5) to within one standard deviation, the equivalent resistor of a resistive branch (4, 5) corresponding to the resistor resulting from coupling in parallel of a resistive branch (4, 5) of the Wheatstone bridge (3) with the associated compensation resistor (9).
G01K 17/20 - Measuring quantity of heat conveyed by flowing media, e.g. in heating systems based upon measurement of temperature difference across a radiating surface, combined with ascertainment of the heat-transmission coefficient
CENTRE NATIONAL DE LA RECHERCHE SCIENTIFIQUE (France)
UNIVERSITE CLAUDE BERNARD LYON I (France)
Inventor
Terreux, Raphaël
Alliod, Charlotte
Denis, Roland
Jacob, Guy
Abstract
A selection process is iterative and includes an initialization associating with a so-called current molecule a value of a predetermined molecule descriptor associated with the target molecular structure, and during each iteration of the selection process, the process includes evaluating, for each molecule of a database including a plurality of molecules each associated with a value of the descriptor, a so-called overall similarity measure between the value of the descriptor associated with the molecule and the value of the descriptor associated with the current molecule; selecting molecules from the database having an overall similarity measure greater than a predetermined threshold, the selected molecules being added to the reference subset; and updating the value of the descriptor associated with the current molecule from the values of the descriptors associated with at least some of the molecules belonging to the reference subset.
12 - Land, air and water vehicles; parts of land vehicles
37 - Construction and mining; installation and repair services
39 - Transport, packaging, storage and travel services
42 - Scientific, technological and industrial services, research and design
Goods & Services
(1) Appareils de locomotion par air nommément véhicule aérospatial, propulseurs de véhicules à savoir de fusées et fusées équipés d'un véhicule spatial et engin spatial, véhicules et engins spatiaux de transport aptes aux rentrées atmosphériques; appareils de locomotion dans l'espace extra-atmosphérique, véhicule aérospatial et engin spatial multi mission à savoir utilisés pour le fret, pour la mise à poste de satellite, pour le vol habité ou pour l'exploration spatiale; véhicules et engins spatiaux de transport, notamment réutilisables, et leurs pièces et parties constitutives; véhicules et engins aériens de transport, notamment réutilisables, et leurs pièces et parties constitutives; véhicule d'évacuation d'équipage pour véhicules et engins aériens, notamment réutilisables; véhicule d'évacuation d'équipage pour véhicules et engins spatiaux, notamment réutilisables; véhicules et engins aériens et spatiaux de transport comprenant un dispositif d'évacuation d'équipage; véhicules de lancement pour véhicules aérospatiaux et fusées; dispositifs de freinage pour véhicules aériens et véhicules et engins spatiaux aptes aux rentrées atmosphériques. (1) Services de maintenance et de réparation de véhicules aérospatiaux et d'engins aérospatiaux, notamment de véhicules aérospatiaux et d'engins aérospatiaux réutilisables; services de ravitaillement d'engins spatiaux et stations spatiales.
(2) Services de transport spatial, transport aérien au moyen de véhicules et d'engins aérospatiaux; services de lancement de véhicules aériens, véhicules spatiaux, de propulseurs de fusées, de véhicules et d'engins aérospatiaux aptes aux rentrées atmosphériques; services de transport spatial de marchandises, de personnes, de satellites et d'engins aérospatiaux; stationnement, amarrage, arrimage et parking de véhicules et engins spatiaux; affrètement d'aéronefs, de véhicules aérospatiaux; services de lancement de satellite; services de récupération (remorquage) de véhicules et engins aérospatiaux, notamment réutilisables.
(3) Services d'ingénierie dans les domaines de l'aéronautique, de l'aérospatial, des véhicules et engins aérospatiaux, des véhicules de transport spatial notamment de la réutilisation des véhicules et engins spatiaux aptes aux rentrées atmosphériques, des systèmes propulsifs embarqués, des matériaux composites, des équipements énergétiques, des systèmes de guidage, navigation et de contrôle de trajectoire (GNC) et d'atterrissage, des systèmes de sureté et de protection en vol des personnes; services d'analyse et d'expertise dans les domaines de l'aéronautique, de l'aérospatial, des véhicules de transport spatial notamment de la réutilisation, des véhicules et engins spatiaux aptes aux rentrées atmosphériques, des systèmes propulsifs embarqués, des matériaux composites, des équipements énergétiques, des systèmes de guidage, navigation et de contrôle de trajectoire (GNC) et d'atterrissage; recherche scientifique et industrielle dans les domaines de l'aérospatiale, de l'aéronautique, des véhicules de transport spatial notamment de la réutilisation des véhicules et engins spatiaux aptes aux rentrées atmosphériques, des systèmes propulsifs embarqués, des matériaux composites, des systèmes de guidage, navigation et de contrôle de trajectoire (GNC) et d'atterrissage; études de projets techniques; essais de machines; essais de matériaux; essais en vol d'aéronefs et d'engins spatiaux; essais de systèmes, d'équipements et pièces de véhicules aérospatiaux; service d'inspection technique des systèmes, équipements et pièces de véhicules aérospatiaux; service d'analyse, d'expertise et de traitement de l'acquisition de données techniques enregistrées lors de campagne d'essais de systèmes, lors de missions aériennes et spatiales, équipements et pièces de véhicules aérospatiaux; services d'élaboration et de conception des véhicules de transport spatial réutilisables, des véhicules et engins spatiaux aptes aux rentrées atmosphériques, des systèmes propulsifs embarqués, des matériaux composites, des systèmes de guidage, navigation et de contrôle de trajectoire (GNC) et d'atterrissage; conception de véhicules spatiaux.
12 - Land, air and water vehicles; parts of land vehicles
37 - Construction and mining; installation and repair services
39 - Transport, packaging, storage and travel services
42 - Scientific, technological and industrial services, research and design
Goods & Services
Apparatus for locomotion by air, namely, aerospace vehicles, thrusters for vehicles, namely, rockets and rockets equipped with a space vehicle and spacecraft, space vehicles and craft suitable for atmospheric re-entry; apparatus for locomotion in outer space, multi-mission aerospace vehicle and spacecraft, namely, used for freight, satellite positioning, manned flights or space exploration; space transport vehicles and craft, particularly reusable, and parts and components thereof; air transport vehicles and craft, particularly reusable, and parts and components thereof; crew evacuation vehicle for air vehicles and craft, particularly reusable; crew evacuation vehicle for space vehicles and craft, particularly reusable; air and space transport vehicles and craft comprising a crew evacuation device; launch vehicles for aerospace vehicles and rockets; braking devices for air vehicles and space vehicles and craft suitable for atmospheric re-entry Maintenance and repair of aerospace vehicles and craft, particularly reusable aerospace vehicles and aerospacecraft; spacecraft and space station refueling services Space transport services, air transport by means of aerospace vehicles and craft; launching air vehicles, space vehicles, rocket boosters, aerospace vehicles and craft suitable for atmospheric re-entry; space transport of merchandise, people, satellites and aerospacecraft; emplacement, mooring, docking and parking of space vehicles and craft; chartering aircraft, aerospace vehicles; satellite launch services; Towing of aerospace vehicles and craft, particularly reusable Engineering services in the fields of aeronautics, aerospace, aerospace vehicles and craft, space transport vehicles particularly for the re-use of space vehicles and craft suitable for atmospheric re-entry, on-board propulsion systems, composite materials, energy equipment, guidance, navigation and course control systems (GNC) and landing, safety and flight protection systems for people; analysis and expertise services in the field of aeronautics, aerospace, space transport vehicles particularly for re-use, space vehicles and craft suitable for atmospheric re-entry, on-board propulsion systems, composite materials, energy equipment, guidance, navigation and course control systems (GNC) and landing; scientific and industrial research in the fields of aerospace, aeronautics, space transport vehicles particularly for the re-use of space vehicles and craft, on-board propulsion systems, composite materials, guidance, navigation and course control systems (GNC) and landing; technical project studies in the nature of conducting of feasibility studies in the field of new technologies; testing the functionality of machines; testing of materials; aircraft and spacecraft flight tests; testing of aerospace vehicle systems, equipment and parts; technical inspection of systems, equipment and parts of aerospace vehicles; analysis, expertise and processing of the acquisition of technical data recorded during the systems test campaign, during air and space missions, equipment and parts of aerospace vehicles; developing and designing reusable space transportation vehicles, space vehicles and craft suitable for atmospheric re-entry, on-board propulsion systems, composite materials, guidance, navigation and course control (GNC) and landing systems; designing space vehicles
09 - Scientific and electric apparatus and instruments
42 - Scientific, technological and industrial services, research and design
Goods & Services
Telecommunication access services, namely, global computer network access services with access codes for use in the aerospace field; Electronic data transmission services over a secure computer system network with access codes for use in the aerospace field. Augmented optical telescope for low (LEO), medium (MEO), geostationary (GEO) and high (HEO) orbits; surveillance and movement orbit determination monitoring sensors for detecting satellites and other objects in Earth orbit in space and for transmitting, receiving and processing data and images concerning the course and position of satellites and other objects in space. Scientific research in the field of monitoring all orbits, namely, low (LEO), medium (MEO), geostationary (GEO) and high (HEO) orbits; Engineering in the field of monitoring all orbits, namely, low (LEO), medium (MEO), geostationary (GEO) and high (HEO) orbits
CENTRE NATIONAL DE LA RECHERCHE SCIENTIFIQUE (France)
UNIVERSITE DE RENNES 1 (France)
Inventor
Attaja, Nicolas
Ettorre, Mauro
Sauleau, Ronan
Guihard, Davy
Abstract
An antenna (100) comprising at least a first resonant cavity (110) and a second resonant cavity (120), each resonant cavity (110, 120) being closed off by a base (112, 122) at one end and comprising a radiating element (111, 121) superimposed on the base of the resonant cavity, the radiating element (111) of the first cavity (110) being able to emit a signal in a first frequency band and the radiating element (121) of the second cavity (120) being able to emit a signal in a second frequency band separate from the first frequency band, characterized in that a first distance between the base (112) and the radiating element (111) of the first cavity (110) is different from a second distance between the base (122) and the radiating element (121) of the second cavity (120).
H01Q 1/28 - Adaptation for use in or on aircraft, missiles, satellites, or balloons
H01Q 5/48 - Combinations of two or more dipole type antennas
H01Q 19/10 - Combinations of primary active antenna elements and units with secondary devices, e.g. with quasi-optical devices, for giving the antenna a desired directional characteristic using reflecting surfaces
H01Q 21/26 - Turnstile or like antennas comprising arrangements of three or more elongated elements disposed radially and symmetrically in a horizontal plane about a common centre
74.
METHOD FOR PRODUCING THE PENTAZOLATE ANION USING A HYPERVALENT IODINE OXIDANT
CENTRE NATIONAL DE LA RECHERCHE SCIENTIFIQUE (France)
UNIVERSITE CLAUDE BERNARD-LYON 1 (France)
Inventor
Joucla, Lionel
Gasnier, Gwénaël
Comte, Sébastien
Silva Costa, Raphaël
Abstract
The present invention relates to a process for producing the pentazolate anion, comprising at least the oxidation of a phenolic arylpentazole with a particular hypervalent iodine oxidant in the presence of a base.
A device for neutralizing a chemical or biological weapon includes a sealed enclosure which delimits an internal volume and which is movable between a retracted position and an extended position, a pyrotechnic neutralizing charge which is disposed inside the enclosure, a decontaminating agent which is disposed inside the enclosure and which surrounds the pyrotechnic neutralizing charge, and a mitigating agent which is disposed in the enclosure and which covers the decontaminating agent.
System for recovering compression energy of a gas (56), the system comprising an organic Rankine cycle module (40) and an adiabatic compressor (14), the organic Rankine cycle module (40) containing a heat-transfer fluid (54) and the adiabatic compressor comprising N adiabatic gas compression stages (14A, 14B, 14C), N being greater than or equal to 2, and, downstream of each adiabatic gas compression stage (14A, 14B, 14C), two heat exchangers, a first heat exchanger (50A, 50B, 50C) configured to extract heat from the gas leaving the adiabatic compression stage (14A, 14B, 14C) and to heat the heat-transfer fluid (54) passing through the first heat exchanger (50A, 50B, 50C), and a second heat exchanger (52A, 52B, 52C) configured to extract heat from the gas leaving the first heat exchanger (50A, 50B, 50C) towards a cold source (58) passing through the second heat exchanger (52A, 52B, 52C). Liquefier comprising such a system and method for recovering compression energy of a gas.
F01K 25/10 - Plants or engines characterised by use of special working fluids, not otherwise provided forPlants operating in closed cycles and not otherwise provided for using special vapours the vapours being cold, e.g. ammonia, carbon dioxide, ether
F25J 1/00 - Processes or apparatus for liquefying or solidifying gases or gaseous mixtures
F25J 1/02 - Processes or apparatus for liquefying or solidifying gases or gaseous mixtures requiring the use of refrigeration, e.g. of helium or hydrogen
77.
BLIND CUTTING METHOD USING A HIGH-PRESSURE JET FOR AN ENGINE BODY
The invention relates to a method for blind cutting, by water jets, of a motor case of an aerospace vehicle, the method comprising a plurality of passes (210, 230) of a high-pressure water jet along the same cutting path travelling across the outer perimeter of the motor case, the cutting path describing a closed-loop circuit, and each pass of the water jet starting from a starting point located on the cutting path and stopping just after passing back over the starting location. The starting point of each pass of the high-pressure water jet is different from the starting points of the other passes of the water jet.
B24C 1/04 - Methods for use of abrasive blasting for producing particular effectsUse of auxiliary equipment in connection with such methods for treating only selected parts of a surface, e.g. for carving stone or glass
B26F 3/00 - Severing by means other than cuttingApparatus therefor
Method for hydrogen liquefaction comprising at least a pre-cooling step, wherein a hydrogen feed flow is cooled by a first refrigerant, a cooling step, wherein the hydrogen feed flow is cooled by a second refrigerant, and a step of expanding the hydrogen feed flow. Each of the first and second refrigerants is successively subjected to at least one compression and to at least one expansion in order to cool it, and a liquid phase of the first refrigerant cools the second refrigerant between at least three stages of said compression so that the second refrigerant does not exceed a temperature of 150 K, preferably 113 K, during said compression of the second refrigerant. A plant for the implementation of this method comprises a first refrigerant circuit (R1) containing a first refrigerant and a second refrigerant circuit (R2) containing a second refrigerant and comprising one or more compressors (C21, C22, C23) and a cooling device arranged together, and one or more expansion valves (JT2, E21, E22, E23). The cooling device is configured to cool the second refrigerant in the second refrigerant circuit (R2) with a liquid phase of the first refrigerant in the first refrigerant circuit (R1).
F25J 1/00 - Processes or apparatus for liquefying or solidifying gases or gaseous mixtures
F25J 1/02 - Processes or apparatus for liquefying or solidifying gases or gaseous mixtures requiring the use of refrigeration, e.g. of helium or hydrogen
Nozzle of a spacecraft engine, comprising a nozzle body extending along a main direction, from a proximal end secured to the engine of the spacecraft, and a free distal end, said nozzle body having a plurality of stiffeners extending from an outer surface of the nozzle body, radially with respect to the main direction, said nozzle comprising a thermal insulation system, comprising at least one strip of insulating material disposed so as to surround the outer surface of the nozzle body over at least part of the height of said nozzle body, said thermal insulation system comprising a plurality of holding elements, each holding element being positioned so as to surround said strips of insulating material, and being disposed between two stiffeners of the nozzle body.
09 - Scientific and electric apparatus and instruments
38 - Telecommunications services
42 - Scientific, technological and industrial services, research and design
Goods & Services
Optical telescopes augmented for low (LEO), medium (MEO), geostationary (GEO) and high (HEO) earth orbits; Intelligence sensors. Access to global computer networks using access codes for use in the aerospace field; Data transmission, Via a network of secure computer systems using access codes for use in the aerospace field. Scientific research and Engineering services In the field of orbit surveillance namely low (LEO), medium (MEO), geostationary (GEO) and high (HEO) earth orbits.
12 - Land, air and water vehicles; parts of land vehicles
37 - Construction and mining; installation and repair services
39 - Transport, packaging, storage and travel services
42 - Scientific, technological and industrial services, research and design
Goods & Services
Apparatus for locomotion by air in particular Aerospace vehicles, Rocket propulsion apparatus and rockets equipped with space vehicles and Vehicles for use in space, Vehicles and spacecraft suitable for atmospheric reentry; Apparatus for locomotion in outer space, Aerospace vehicles and Multi-mission spacecraft, namely: All the aforesaid goods being for use in freight, stationing of satellites, manned flight or space exploration; Vehicles and spacecraft, being in particular reusable, and Parts and fittings for the aforesaid goods; Air vehicles and craft, in particular being reusable, and Parts and fittings for the aforesaid goods; Crew return vehicles, for use in relation to the following goods: Air vehicles and craft, in particular being reusable; Crew return vehicles, for use in relation to the following goods: Vehicles and spacecraft, being in particular reusable; Air and space vehicles and craft incorporating a crew return vehicle; launch vehicles, for use in relation to the following goods: Aerospace vehicles and Rockets; Braking devices for air vehicles, brake actuators, for use in relation to the following goods: Vehicles and spacecraft suitable for atmospheric reentry. Repair and maintenance services, In connection with the following goods: aerospace vehicles and Aerospace craft, Especially Reusable aerospace vehicles and craft; Maintenance, Repair, Refurbishment and Reconditioning, conversion, In connection with the following goods: Reusable aerospace vehicles and craft, all the aforesaid services enabling the reuse of the aforesaid goods. space transport services, Air transport Via aerospace vehicles and craft; Launching of air vehicles, space vehicles, rocket thrusters, aerospace vehicles and spacecraft suitable for atmospheric reentry; Space transport of goods, passengers, satellites and aerospace craft; Parking, mooring, stowage and Car parking, in relation to the following goods: Space vehicles and Spacecraft; Aircraft chartering, Freighting of aerospace vehicles; Launching of satellites; recovery, in relation to the following goods: Aerospace vehicles and craft, being in particular reusable; Refuelling of spacecraft and space stations via pressurised and non-pressurised space cargo, namely Transport and delivery, in relation to the following goods: Merchandise, Products, Food, Water, clothing, Waste, Fuel, Carburants, Gas, Fluids, satellite, Scientific equipment for conducting experiments, maintenance equipment, materials and equipment, space module. Engineering services, in relation to the following fields: Aeronautics, Aerospace, aerospace vehicles and craft, space transport vehicles Especially Reuse of space vehicles and craft suitable for atmospheric reentry, on-board propulsion systems, composite materials, energy equipment, guiding, navigation and trajectory control (GNC) and landing systems, personal security and protection systems during flights; Analysis and surveys, in relation to the following fields: Aeronautics, Aerospace, space transport vehicles Especially Reuse of space vehicles and craft suitable for atmospheric reentry, on-board propulsion systems, composite materials, energy equipment, guiding, navigation and trajectory control (GNC) and landing systems; Scientific and industrial research, in relation to the following fields: Aerospace, Aeronautics, Space transport vehicles Especially Reuse of space vehicles and craft suitable for atmospheric reentry, on-board propulsion systems, composite materials, energy equipment, guiding, navigation and trajectory control (GNC) and landing systems; Conducting technical project studies; Testing of machines; Material testing; Flight testing of aircraft and Flight testing of spacecraft; Testing of spacecraft systems, equipment and parts; Technical inspection of aerospace vehicle parts, equipment and systems; Analysis, surveying and acquisition processing of technical data recorded during testing of systems, during air and space missions, equipment and parts of aerospace vehicles; Development and Design, In connection with the following goods: Reusable space transport vehicles, space vehicles and craft suitable for atmospheric reentry, on-board propulsion systems, Composites, Guiding, navigation and trajectory control (GNC) and landing systems; Design, In connection with the following goods: space ships.
A gas-generating pyrotechnic composition has a high gas yield while having reduced generation of condensable species and a limited combustion temperature.
Regulating valve (1) with rack/pinion transmission system for an aircraft or spacecraft, comprising a valve body (10), a transmission shaft (40), a throttling element (30), a rack (32) of the throttling element being engaged with a pinion (42) of the shaft (40), a first end of the throttling element being guided in translational movement by a first bearing (51), and a second end of the throttling element being guided in translational movement by a second bearing (52), the valve comprising an annular connecting flange (20) fixed to the valve body (10), the annular connecting flange (20) extending radially between an internal face (22) that exhibits symmetry of revolution about a second axis (X') of the throttling element (30) and an external face (24) that exhibits symmetry of revolution about a central axis (X), the internal face (22) comprising a radially internal housing (26) in which the second bearing (52) is housed, the second axis (X') being offset radially from the central axis (X).
F16K 31/54 - Mechanical actuating means with toothed gearing with pinion and rack
F16K 3/26 - Gate valves or sliding valves, i.e. cut-off apparatus with closing members having a sliding movement along the seat for opening and closing with sealing faces shaped as surfaces of solids of revolution with cylindrical valve members with fluid passages in the valve member
A space aircraft including a fuselage, two wings arranged on either side of the fuselage, and two nacelles arranged at the ends of the wings and each carrying a horizontal tail and a vertical tail, the fuselage having a cross section of variable size along the longitudinal axis with a maximum cross section being located in a longitudinal position located in front of the longitudinal position of the leading edges of the wings at the fuselage, making it possible in particular to help prevent the space aircraft from losing longitudinal static stability, the space aircraft thus having an optimized design and architecture which are suitable for the severe conditions encountered by such a space aircraft, in particular during atmospheric re-entry.
The invention relates to a hypersonic transport system (1) comprising: - an aircraft (2) with a hypersonic lift-to-drag ratio greater than or equal to 2.5, the aircraft (2) comprising a secondary propulsion device (21) and position sensors, the aircraft (2) also comprising a variable-shape aerodynamic surface (22); - a main propulsion device (3) which is fixed removably to the aircraft (2); - a control unit (4) which is configured to control the aircraft (2) and the main propulsion device (3) so as to perform the following steps while keeping the loading factor below 1.5G: *a step of taking off and climbing up to an altitude greater than or equal to 30km at a speed greater than or equal to 3000m/s, the main propulsion device (3) being separated from the aircraft (2) at the end of the takeoff and climb step; * a step of cruising by bouncing off the earth's atmosphere, during which step the control unit (4) controls the secondary propulsion device (21) in order to maintain the speed of the aircraft (2) and maintain the aircraft (2) on a predefined flight path; * a descent and landing step during which the control unit (4) controls the change of shape of the variable-shape aerodynamic surface (22) of the aircraft (2) in order to achieve a dissipative descent, the control unit (4) then controlling the secondary propulsion device (21) in order to actively slow the aircraft (2) after the dissipative descent.
The invention relates to a transport system (1) intended to be installed on a space launcher (100, figure 1) and comprising: • - an aircraft (2) which comprises propulsion means configured to propel the aircraft (2) in a direction of flight, and at least one seat (4) intended for receiving a passenger who is rotationally movable about an axis (Θ) perpendicular to the direction of flight of the aircraft (2), an acceleration sensor being installed on each at least one seat (4) to measure the acceleration of each at least one seat (4); • - a passenger interface for each at least one seat (4), comprising a screen (51) intended to display images to the passenger installed in said at least one seat (4), the screen (51) being coupled to said at least one seat (4) so as to remain stationary relative to said at least one seat (4); • - a control unit (6) which is connected to the acceleration sensor and to said at least one seat (4), the control unit (6) being configured to calculate a load factor experienced by the passenger installed in the at least one seat (4) based on the acceleration of said at least one seat (4), the control unit (6) being configured to control the rotation of the at least one seat (4) while the transport system (1) is in operation so as to keep the position of the seat (4) stationary relative to the load factor experienced by the passenger throughout the flight.
Gas liquefaction device (10) comprising an outer casing (12) and at least one removable module (M1, M2, M3) disposed inside the outer casing (12), the at least one removable module (M1, M2, M3) being configured to liquefy a gas, wherein the outer casing (12) comprises at least one removable cover (12A) used for reversibly closing the outer casing (12) and configured to insert/extract the at least one removable module (M1, M2, M3) into/from the interior of the outer casing (12), the outer casing (12) equipped with its at least one removable cover (12A) delimiting a closed chamber housing the at least one removable module (M1, M2, M3).
The invention relates to a maintenance method for a gas liquefaction device (10) which comprises an outer casing (12) delimiting a closed chamber (C) and having at least one removable cover (12A, 12B), and at least one removable module (M1, M2, M3) disposed inside the outer casing (12) and configured to liquefy a gas, the method comprising: removing at least one of the removable covers (12A, 12B), extracting at least one removable module (M1, M2, M3) from the outer casing (12), performing at least one maintenance operation on the at least one removable module (M1, M2, M3) extracted from the outer casing (12), disposing the at least one removable module (M1, M2, M3) inside the outer casing (12), and closing the outer casing (12) by returning the at least one removable cover (12A, 12B).
A pyrotechnic cut-off device includes: a pyrotechnic igniter, a conductive portion and a movable piston, the piston being able to be displaced in a cavity along a direction of displacement following the actuation of the pyrotechnic igniter between a first position of passage of the current in the conductive portion and a second position of cut-off of the current, wherein the piston defines a first sealing portion having a narrowing of section along the direction of displacement, and the cavity has a wall defining a second sealing portion which extends on either side of the conductive portion and which has a narrowing of section along the direction of displacement, the first sealing portion being in contact with the second sealing portion along a contact surface extending on either side of the conductive portion when the piston is in the second position.
A multilayer strip intended to be wound on a form to manufacture a part in composite material, includes superposed fibrous layers, at least one of these layers being pre-impregnated, the superposed fibrous layers including a first layer including a first material on a first side of the width of the strip and a second material, differing from the first material, on a second side of the width of the strip opposite the first side, and a second layer superposed on the first layer and including the first material on the first side and the second material on the second side, with overlapping of a material of the second layer over a different material of the first layer.
B29C 53/56 - Winding and joining, e.g. winding spirally
B29C 53/00 - Shaping by bending, folding, twisting, straightening or flatteningApparatus therefor
B29C 70/20 - Fibrous reinforcements only characterised by the structure of fibrous reinforcements using fibres of substantial or continuous length oriented in a single direction, e.g. roving or other parallel fibres
B29C 70/22 - Fibrous reinforcements only characterised by the structure of fibrous reinforcements using fibres of substantial or continuous length oriented in at least two directions forming a two dimensional structure
B29C 70/30 - Shaping by lay-up, i.e. applying fibres, tape or broadsheet on a mould, former or coreShaping by spray-up, i.e. spraying of fibres on a mould, former or core
B29C 70/32 - Shaping by lay-up, i.e. applying fibres, tape or broadsheet on a mould, former or coreShaping by spray-up, i.e. spraying of fibres on a mould, former or core on a rotating mould, former or core
B29L 31/30 - Vehicles, e.g. ships or aircraft, or body parts thereof
B32B 3/14 - Layered products comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar shapeLayered products comprising a layer having particular features of form characterised by a discontinuous layer, i.e. apertured or formed of separate pieces of material characterised by a face layer formed of separate pieces of material
B32B 5/02 - Layered products characterised by the non-homogeneity or physical structure of a layer characterised by structural features of a layer comprising fibres or filaments
B32B 5/26 - Layered products characterised by the non-homogeneity or physical structure of a layer characterised by the presence of two or more layers which comprise fibres, filaments, granules, or powder, or are foamed or specifically porous one layer being a fibrous or filamentary layer another layer also being fibrous or filamentary
91.
Multilayer multi-width strip for winding with progressive change in the deposition angle
A multilayer strip intended to be wound on a form, includes pre-impregnated fiber layers superimposed along a stacking direction, each layer extending widthwise along a transverse direction perpendicular to the stacking direction between a first and a second edge, wherein on at least a portion of the multilayer strip the first edges of the pre-impregnated fiber layers are aligned with each other in the stacking direction, and each second edge is recessed relative to the second edge of the underlying layer in the transverse direction.
B32B 5/12 - Layered products characterised by the non-homogeneity or physical structure of a layer characterised by structural features of a layer comprising fibres or filaments characterised by the relative arrangement of fibres or filaments of adjacent layers
B29B 11/16 - Making preforms characterised by structure or composition comprising fillers or reinforcements
B29L 31/30 - Vehicles, e.g. ships or aircraft, or body parts thereof
B32B 3/02 - Layered products comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar shapeLayered products comprising a layer having particular features of form characterised by features of form at particular places, e.g. in edge regions
B32B 5/26 - Layered products characterised by the non-homogeneity or physical structure of a layer characterised by the presence of two or more layers which comprise fibres, filaments, granules, or powder, or are foamed or specifically porous one layer being a fibrous or filamentary layer another layer also being fibrous or filamentary
B32B 37/06 - Methods or apparatus for laminating, e.g. by curing or by ultrasonic bonding characterised by the heating method
09 - Scientific and electric apparatus and instruments
37 - Construction and mining; installation and repair services
39 - Transport, packaging, storage and travel services
42 - Scientific, technological and industrial services, research and design
Goods & Services
Motors and engines (other than for land vehicles); engines
for air locomotion vehicles; rocket engines; reusable rocket
engines; space launch vehicle engine; airplane engines;
aircraft engines; space vehicle engines; propulsion systems
and mechanisms and component parts thereof for vehicles
(except those for land vehicles); turbines other than for
land vehicles; turbochargers; air nozzles. Measuring apparatus and instruments, notably apparatus and
instruments for measuring the weight and resistance of
materials, and pressure measuring sensors; control apparatus
and instruments, notably electronic control systems for
launching rockets and satellites; electrical, electronic and
magnetic pressure, velocity, displacement, temperature,
position or vibration sensors; apparatus and instruments for
measuring the mechanical properties of materials; apparatus
and instruments for measuring and monitoring the aging of
materials; measuring and detection apparatus and instruments
for tracking and monitoring the aging of materials; data
processing apparatus and computer hardware; computers;
software; software for predicting the flight of aerospace
propulsion systems and means; software for electrical or
electronic control of propulsion systems, propulsion bays,
motors and engines and power drive units; diagnostic
software for propulsion systems, propulsion bays, motors and
engines and power drive units. Repair, maintenance, integration and dismantling of
propulsion systems, propulsion bay, motors and engines and
power drive units, reusable motors and engines and power
drive units, for launch vehicles, aerospace vehicles and
machines; repair, maintenance, integration and dismantling
services in the field of propulsion systems, propulsion bay,
motors and engines and power drive units, reusable motors
and engines and power drive units, for launch vehicles,
aerospace vehicles and machines; repair, maintenance,
integration and dismantling services in the field of
equipment and systems for the pressurization of propellant
stages and propellant stage tanks, propulsion bay equipment,
jet pipe, vehicle fuel tanks and space transportation
apparatus as well as the motors, engines and component parts
thereof, control valve, turbines, turbocompressor other than
for land vehicles; services for the manufacture, repair,
maintenance, servicing of additive manufacturing equipment,
components and parts; installation, maintenance and repair
of data processing equipment for the control and diagnosis
of propulsion systems, propulsion bays, motors and engines
or power drive units for aerospace vehicles and machines;
installation, maintenance, inspection and repair of computer
hardware for the control and diagnosis of propulsion
systems, propulsion bays, motors and engines or power drive
units for space vehicles and machines; logistics services
and means for transporting propulsion systems, propulsion
bays, motors and engines and power drive units for aerospace
vehicles and machines. Rental of means of transport; rental service for propulsion
units and means of propulsion for launch vehicles, aerospace
vehicles and machines; providing services pertaining to the
launch of satellites and recovery thereof. Engineering; engineering services in the field of aerospace,
aeronautics, composite materials, means and systems of
propulsion, propulsion bay, motors and engines and power
drive units, equipment for such propulsion systems, motors
and engines and reusable motors and engines, additive
manufacturing for such equipment; engineering services in
the fields of integration of such propulsion systems on
launch vehicles, space vehicles and machines; analysis and
expert appraisal services in the fields of aerospace,
aeronautics; analysis and expert appraisal services in the
fields of composite materials, means and systems of
propulsion, propulsion bay, motors and engines and power
drive units, equipment for such propulsion systems, motors
and engines and reusable motors and engines; analysis and
expert appraisal services in the fields of additive
manufacturing for propulsion bay equipment, jet pipe, tanks,
space transportation vehicles and apparatus as well as the
motors and engines and component parts thereof, control
valve, turbines, turbocompressor other than for land
vehicles; scientific and industrial research in the fields
of aerospace, aeronautics, composite materials, means and
systems of propulsion, propulsion bay, motors and engines
and power drive units, equipment for such propulsion
systems, motors and engines and reusable motors and engines,
additive manufacturing for such equipment; technical project
studies; testing of machines; testing of materials; engine
testing for launch vehicles, space vehicles and machines;
testing of propulsion systems, equipment and parts for
propulsion systems, propulsion bay, motors and engines and
power drive units for launch vehicles, space vehicles and
machines; technical inspection service for systems,
equipment and parts of aerospace vehicles and machines;
technical inspection and production control service for
additive manufacturing; service for qualifying systems,
equipment and parts of aerospace vehicles and machines;
service for the analysis, expert appraisal and processing of
the acquisition of technical data recorded during testing
campaigns for systems, equipment and parts of aerospace
vehicles and machines; designing propulsion systems and
propellant stages for launch vehicles, space vehicles and
machines; design, installation, maintenance, updating and
rental of software; computer programming; design and
maintenance of databases; research and development of new
products for third parties.
The invention relates to a fire extinguishing device (1) comprising: - a body (2) defining a storage chamber (4) containing an extinguishing composition, and - a distribution system (20) configured to distribute the extinguishing composition outside the body through an outlet port (10), characterised in that the extinguishing composition has, at an operating temperature and at 1 bar, a saturated vapour concentration greater than or equal to its extinguishing concentration as determined according to the standard ISO 14520 for a heptane fire at 1 bar, the operating temperature being less than or equal to -10°C, and the extinguishing composition comprising at least one perfluoroketone and/or at least one perfluoronitrile.
A nozzle comprises a combustion chamber having a downstream end and a divergent formed of a cone-shaped wall extending between an upstream end and a downstream end. The upstream end of the divergent is connected to the downstream end of the combustion chamber by an intermediate ring having an upstream flange fixed on a fixing flange secured to the combustion chamber and a downstream flange connected to the upstream end of the divergent. The intermediate ring having an inner channel present between the upstream and downstream flanges of the intermediate ring. A material able to take heat from the ring is present in the inner channel.
The invention relates to a cutoff device comprising a conductive element (40) and a mobile piston (30), the piston (30) being able to move between a first position in which current flows in the conductive element (40) and a second position in which the current is cut off, the piston (30) being designed to break the conductive element (40) when it moves from its first position to its second position, the piston (30) being positioned in a reception cavity (12a) of a reception element (12) when said piston (30) is in its second position, the reception cavity (12a) being delimited by at least one internal wall (120) of the reception element (12), and the internal wall (120) being made of electrically insulating material. The reception element (12) furthermore comprises vanes (60) made of electrically insulating material and extending within the reception cavity (12a) from the at least one internal wall (120) of the reception element (12).
A process for manufacturing a polybenzoxazine monomer, crosslinking the latter, and using the crosslinked product to form an ablative thermal protection system for a thruster nozzle or atmospheric reentry body.
C07D 265/16 - 1,3-OxazinesHydrogenated 1,3-oxazines condensed with carbocyclic rings or ring systems condensed with one six-membered ring with only hydrogen or carbon atoms directly attached in positions 2 and 4
B64G 99/00 - Subject matter not provided for in other groups of this subclass
C07D 413/06 - Heterocyclic compounds containing two or more hetero rings, at least one ring having nitrogen and oxygen atoms as the only ring hetero atoms containing two hetero rings linked by a carbon chain containing only aliphatic carbon atoms
C07D 413/14 - Heterocyclic compounds containing two or more hetero rings, at least one ring having nitrogen and oxygen atoms as the only ring hetero atoms containing three or more hetero rings
A space transportation system (1) intended to be mounted on a space launcher (100) comprising a re-ignitable propulsion device (2) and orientable flaps (3) located at a second end (12) and a control unit (4), each flap (3) comprising activation means configured to modify the orientation of said flap (3), the control unit (4) being configured to control the activation of the propulsion device (2) and to individually control the orientation of the flaps (3) in order to implement the following steps: a launch step, during which the propulsion device (2) is turned off and the flaps (3) are in a retracted position; a return step, during which the control unit (4) deploys the flaps (3) and individually controls the orientation of the flaps (3) in order to slow down the system (1), the propulsion device (2) being turned off; a landing step, during which the control unit (4) controls the propulsion device (2) and the activation means for orienting the flaps (3) in order to slow down and turn around the system (1).
A space transportation system (1) intended to be mounted on a space launcher (100) comprising a re-ignitable propulsion device (2) and orientable flaps (3) located at a second end (12) and a control unit (4), each flap (3) comprising activation means configured to modify the orientation of said flap (3), the control unit (4) being configured to control the activation of the propulsion device (2) and to individually control the orientation of the flaps (3) in order to implement the following steps: a launch step, during which the propulsion device (2) is turned off and the flaps (3) are in a retracted position; a return step, during which the control unit (4) deploys the flaps (3) and individually controls the orientation of the flaps (3) in order to slow down the system (1), the propulsion device (2) being turned off; a landing step, during which the control unit (4) controls the propulsion device (2) and the activation means for orienting the flaps (3) in order to slow down and turn around the system (1).
A process for removing webs formed on a wall of a central channel of a propellant charge, the process including removing webs by levelling the wall of the central channel of the propellant charge with a levelling tool installed on an articulated robotic arm during which the movements of the robot arm are controlled by a user interface which includes a controller configured to be used by a user; a force sensor measures the force applied by the levelling tool; a control unit connected to the force sensor regulates the movements of the robot arm by maintaining the force applied by the levelling tool below a first predetermined force threshold, the control unit also regulating the movements of the robot arm by maintaining a movement speed of the levelling tool which is below a predetermined speed threshold value.
TA method for treating an aqueous solution containing ammonium perchlorate and optionally nitrate ions, the method having a nitrification/denitrification sequence then a step of reducing perchlorates, the liquid effluent obtained at the end of this step of reducing perchlorates being subjected to a first membrane filtration, the liquid effluent obtained following this first membrane filtration being put into contact, in a reactor in aerobic conditions, with microorganisms able to carry out the oxidation of organic materials, then the liquid effluent leaving this reactor being subjected to a second membrane filtration, the first membrane filtration and the second membrane filtration being carried out on the same membrane filtration unit.
