Abstract

The invention relates to a transport system (1) intended to be installed on a space launcher (100) 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 to receive a passenger which is movable in rotation about an axis (0) 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) which comprises a screen intended to display images to the passenger installed on said at least one seat (4), the screen being coupled to said at least one seat (4) so to remain fixed 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 on the at least one seat (4) from the acceleration of said at least one seat (4), the control unit (6) being configured to monitor the rotation of the at least one seat (4) during the operation of the transport system (1) in order to maintain the position of the seat (4) fixed relative to the load factor experienced by the passenger throughout the flight.

IPC Classes  ?

• B64G 1/60 - Crew or passenger accommodations
• B64G 1/00 - Cosmonautic vehicles
• B64G 1/54 - Protection against radiation

Abstract

A process for the synthesis of a compound of formula (I): A process for the synthesis of a compound of formula (I): wherein w, x, y and z are as defined in the description. A process for the synthesis of a compound of formula (I): wherein w, x, y and z are as defined in the description. The process includes reacting a compound of formula (II): A process for the synthesis of a compound of formula (I): wherein w, x, y and z are as defined in the description. The process includes reacting a compound of formula (II): with carbonyldiimidazole, and reacting the resulting compound with propargylamine.

IPC Classes  ?

• C08F 8/32 - Introducing nitrogen atoms or nitrogen-containing groups by reaction with amines
• C08F 220/44 - Acrylonitrile

Abstract

The invention relates to a nozzle (100) comprising a needle (110) that is movable between a first position and a second position, a stop (113) secured to the needle (110), and an annular system (150) for retaining the needle, the annular system comprising at least one first ring (161), a second ring (162) that is movable relative to the first ring (161), and at least one seal (171), such that when the needle (110) is in the first position, the first ring (161) is in contact with the stop (113) and the second ring (162) is at a non-zero distance from the stop (113), and such that, when the needle (110) is in the second position, the first and second rings (161, 162) are in contact with the stop (113).

IPC Classes  ?

• F02K 1/08 - Varying effective area of jet pipe or nozzle by axially moving or transversely deforming an internal member, e.g. the exhaust cone
• F02K 9/86 - Rocket-engine plants, i.e. plants carrying both fuel and oxidant thereforControl thereof characterised by thrust or thrust vector control using nozzle throats of adjustable cross-section

Abstract

Device for separating a second part from a first part, including a first interface intended to be fixed to the first part and a second interface intended to be fixed to the second part, a docking stud passing through the first and second interfaces and being held at the first interface by a separation nut and at the second interface by a first nut/locknut assembly, the docking stud being covered by a cap secured to the second interface and intended to receive it once the separation nut has broken and the first and second interfaces have been separated, and a retraction spring is provided to extract the docking stud from the first interface, propel it towards a damping material fixed at the bottom of the cap and hold it there by its residual holding force alone.

IPC Classes  ?

• B64G 1/64 - Systems for coupling or separating cosmonautic vehicles or parts thereof, e.g. docking arrangements

Abstract

The invention relates to a cryogenic propellant tank for a spacecraft engine, the tank comprising a wall that defines a storage volume for the cryogenic propellant, the wall being made of a composite material and comprising a fibrous reinforcement in the form of a fibrous stack (110) which is densified by an organic matrix, the fibrous stack comprising at least in succession and in this order in the direction of the thickness (E) of the wall: (a) a first ply (113) having unidirectional fibres oriented at an angle of –α; (b) a second ply (115) having unidirectional fibres oriented at an angle of -β°; (c) a third ply (117) having unidirectional fibres oriented at an angle of +α; and (d) a fourth ply (119) having unidirectional fibres oriented at an angle of +β°, with α ranging from 5° to 20° and β ranging from 40° to 50°, wherein each angle is taken with respect to a longitudinal axis of the tank.

IPC Classes  ?

• B64G 1/40 - Arrangements or adaptations of propulsion systems
• 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
• B32B 1/00 - Layered products having a non-planar shape
• F17C 13/00 - Details of vessels or of the filling or discharging of vessels

Abstract

The invention relates to a method for cleaning a gas jet (J) ejected by a rocket engine, comprising at least passing the gas jet successively through treatment zones (10; 20) positioned in series in which water is sprayed onto the gas jet, the flow rates of water feeding the nozzles (B1; B2) and the water ejection speed being calibrated.

IPC Classes  ?

• F02K 99/00 - Subject matter not provided for in other groups of this subclass
• B01D 47/06 - Spray cleaning
• B01D 53/00 - Separation of gases or vapoursRecovering vapours of volatile solvents from gasesChemical or biological purification of waste gases, e.g. engine exhaust gases, smoke, fumes, flue gases or aerosols

Abstract

A method for determining a program of displacement and orientation of a needling head for making a textile preform by needling a textile strip on a support tooling, includes determining a set of triplets of coordinates of the points of passage of the needling head as a function of the positions of the fibers along the Z axis in the textile preform to be made, of its local geometry and of a predetermined minimum distance to be met between the needling head and the support tooling or the preform making it possible to avoid a collision with the latter, and determining the angular orientation of the needling head for each point of passage as a function of the angular orientation of the textile strip and of the Z fibers in the textile preform to be made, and determining a local speed of displacement of the needling head.

IPC Classes  ?

• D04H 18/02 - Needling machines with needles
• D04H 1/46 - Non-woven fabrics formed wholly or mainly of staple fibres or like relatively short fibres from fleeces or layers composed of fibres without existing or potential cohesive properties the fleeces or layers being consolidated by mechanical means, e.g. by rolling by needling or like operations to cause entanglement of fibres

Abstract

Method for controlling a synchronous electric motor including a generation of a torque reference from a mechanical setpoint, a measurement of the position and a determination of the speed of the motor, a measurement of the current generated by the motor, a generation of the voltage references from the torque reference, and a generation of the control voltages from the reference voltages. It includes a monitoring of an anomaly in the position measurement, an adaptation of the electrical control gains as a function of the detection or non-detection of an anomaly in the measurement of the position of the electric motor, and in that the voltage references depend on the values of the electrical control gains.

IPC Classes  ?

• H02P 21/00 - Arrangements or methods for the control of electric machines by vector control, e.g. by control of field orientation
• H02P 21/18 - Estimation of position or speed
• H02P 25/022 - Synchronous motors

Abstract

The laser source (220) generates a first laser beam with a wavelength less than an eye-safe subset of the near-infrared spectrum. The laser source (220) is independent of the mount (230) by virtue of an offset comprising a hollow-core optical fibre (223). A hollow-core fibre-based wavelength matching device (221) converts the first laser beam into a second laser beam the wavelength of which is within the eye-safe subset of the near-infrared spectrum. The second laser beam is transmitted to the beam expander (210) via the hollow-core optical fibre (223) in order to be emitted into space.

IPC Classes  ?

• G01S 7/484 - Transmitters
• G01S 7/497 - Means for monitoring or calibrating
• G01S 17/04 - Systems determining the presence of a target
• G01S 7/481 - Constructional features, e.g. arrangements of optical elements

Abstract

The invention relates to an antenna (100) comprising at least: - an electrically conductive enclosure (110) formed by a lower surface (111) surrounded by side edges (112) and closed by a cover (140), an outer surface of which is partially reflective; - a substrate (120) placed at the bottom of the enclosure on the lower surface of the enclosure; and - a radome (150) placed inside the enclosure opposite the substrate and capable of protecting the antenna from temperatures above 1000°C; characterised in that the antenna also comprises a radiating element (130) placed on the substrate inside the enclosure and capable of emitting a signal at at least a first frequency, and a grid (160) placed on a surface of the radome opposite the radiating element so as to form an air gap (170) between the grid and the substrate.

IPC Classes  ?

• H01Q 1/28 - Adaptation for use in or on aircraft, missiles, satellites, or balloons
• H01Q 1/42 - Housings not intimately mechanically associated with radiating elements, e.g. radome
• H01Q 13/20 - Non-resonant leaky-waveguide or transmission-line antennas Equivalent structures causing radiation along the transmission path of a guided wave
• H01Q 15/00 - Devices for reflection, refraction, diffraction or polarisation of waves radiated from an antenna, e.g. quasi-optical devices

Abstract

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.

IPC Classes  ?

• B64G 5/00 - Ground equipment for vehicles, e.g. starting towers, fuelling arrangements
• F16L 3/01 - Supports for pipes, cables or protective tubing, e.g. hangers, holders, clamps, cleats, clips, brackets for supporting or guiding the pipes, cables or protective tubing, between relatively movable points, e.g. movable channels

Abstract

The present disclosure relates to a thermosetting resin that can be obtained by carrying out a reaction between 9,10-dihydro-9-oxa-10-phosphaphenanthrene-10-oxide and a mixture of divanillic alcohol ethers. The present disclosure also provides a thermoset resin obtained from said thermosetting resin.

IPC Classes  ?

• C08G 59/06 - Polycondensates containing more than one epoxy group per molecule of polyhydroxy compounds with epihalohydrins or precursors thereof of polyhydric phenols
• C08G 59/32 - Epoxy compounds containing three or more epoxy groups
• C08G 59/38 - Epoxy compounds containing three or more epoxy groups together with di-epoxy compounds

Abstract

A pump for cryogenic fluid, comprising a compressor (31) configured to draw in an incoming flow (E) of cryogenic fluid arriving upstream and to deliver, downstream, a delivery flow having a pressure greater than the pressure of the incoming flow (E), a motor (41) configured to drive the compressor (31), and a service line (60) configured to withdraw part of the delivery flow, forming a service flow (R) and circulating in and/or along the motor (41) in order to cool the motor (41), wherein the service line (60) comprises at least one pressure loss device (64, 65) configured to reduce the pressure and/or increase the temperature of the service flow (R) so as to cause at least 50%, possibly at least 80%, possibly even at least 90%, of the service flow (R) to pass from the liquid state to the gaseous state.

IPC Classes  ?

• F04D 7/02 - Pumps adapted for handling specific fluids, e.g. by selection of specific materials for pumps or pump parts of centrifugal type
• F04B 15/08 - Pumps adapted to handle specific fluids, e.g. by selection of specific materials for pumps or pump parts for liquids near their boiling point, e.g. under subnormal pressure the liquids having low boiling points
• F04D 29/58 - CoolingHeatingDiminishing heat transfer
• F04B 35/04 - Piston pumps specially adapted for elastic fluids and characterised by the driving means to their working members, or by combination with, or adaptation to, specific driving engines or motors, not otherwise provided for the means being electric
• F04B 37/18 - Pumps specially adapted for elastic fluids and having pertinent characteristics not provided for in, or of interest apart from, groups for special use for specific elastic fluids

Abstract

A pump for cryogenic fluid and an assembly comprising a tank and such a pump, comprising an intake duct (21), a compressor (31) configured to draw in an incoming flow (E) of cryogenic fluid arriving upstream through the intake duct (21) and to deliver, downstream, a delivery flow having a pressure greater than the pressure of the incoming flow (E), and an insulation cavity (71) completely surrounding at least part of the intake duct (21).

IPC Classes  ?

• F04D 7/02 - Pumps adapted for handling specific fluids, e.g. by selection of specific materials for pumps or pump parts of centrifugal type
• F04B 15/08 - Pumps adapted to handle specific fluids, e.g. by selection of specific materials for pumps or pump parts for liquids near their boiling point, e.g. under subnormal pressure the liquids having low boiling points
• F04D 29/42 - CasingsConnections for working fluid for radial or helico-centrifugal pumps
• F04D 29/58 - CoolingHeatingDiminishing heat transfer
• F04D 13/06 - Units comprising pumps and their driving means the pump being electrically driven
• F04B 35/04 - Piston pumps specially adapted for elastic fluids and characterised by the driving means to their working members, or by combination with, or adaptation to, specific driving engines or motors, not otherwise provided for the means being electric
• F04B 37/18 - Pumps specially adapted for elastic fluids and having pertinent characteristics not provided for in, or of interest apart from, groups for special use for specific elastic fluids

Abstract

The invention relates to a transport and release system (100a) for a stack (50) of satellites (52a-c) and comprising a base (102); a set of connecting rods (108), each of which is mounted on the base (102) so as to be able to rotate about a first axis of rotation (10); for each connecting rod (108), an arm (104) with a proximal end (104a) fixed to a distal end (108b) of the connecting rod (108) so as to be able to rotate freely; for each arm (104), securing means (106) securing a distal end (104b) of said arm (104) to the stack (50); an actuating system (110) connected to a proximal end (108a) of each connecting rod (108) and moving each proximal end (108a); and, for each connection between a distal end (108b) of a connecting rod (108) and a proximal end (104a) of an arm (104), a drive system (112) arranged to rotate the arm (104).

IPC Classes  ?

• B64G 1/64 - Systems for coupling or separating cosmonautic vehicles or parts thereof, e.g. docking arrangements

Abstract

A device for monitoring objects in space orbit around the Earth, the device including a chassis, a plate, at least three optical survey modules, and a power supply and control block housed at least partially inside the chassis, the plate being mounted on the chassis, and each optical survey module being mounted on the plate and including a rotating turret, an image sensor mounted on the rotating turret, and a passive optical system mounted on the inlet of the image sensor, the rotating turret being configured to pivot over more than 360° about a first axis perpendicular to the plane in which the plate extends and to pivot over 90° about a second axis perpendicular to the first axis and parallel to the plane in which the plate extends.

IPC Classes  ?

• H04N 23/695 - Control of camera direction for changing a field of view, e.g. pan, tilt or based on tracking of objects
• B64G 3/00 - Observing or tracking cosmonautic vehicles
• H04N 23/51 - Housings
• H04N 23/54 - Mounting of pick-up tubes, electronic image sensors, deviation or focusing coils
• H04N 23/55 - Optical parts specially adapted for electronic image sensorsMounting thereof
• H04N 23/90 - Arrangement of cameras or camera modules, e.g. multiple cameras in TV studios or sports stadiums

Abstract

A braiding machine includes a plurality of yarn feed spindles movable along a guide path so as to participate in the braiding, a reserve zone able to receive at least one spindle such that its participation in the braiding is interrupted.

IPC Classes  ?

• 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
• D04C 3/18 - Spool carriers for vertical spools

Abstract

A valve suitable for high flow rates and high pressures, and a rocket engine including such a valve, the valve including a valve body, including a first fluidway and a second fluidway, a movable shutter, configured to adjust the flow area between the first fluidway and the second fluidway, and an actuator, of electrical type, configured to adjust the position of the shutter, wherein the shutter is able to move linearly between a first position and a second position, wherein the actuator includes a rotor installed in a service cavity of the valve body, the service cavity being in fluid communication with the first fluidway or the second fluidway, and wherein the actuator is configured to drive the movement of the shutter by way of a rotary-to-linear transmission member.

IPC Classes  ?

• F16K 3/24 - 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
• F02K 9/58 - Propellant feed valves
• F16K 3/30 - Gate valves or sliding valves, i.e. cut-off apparatus with closing members having a sliding movement along the seat for opening and closing Details
• F16K 31/04 - Operating meansReleasing devices electricOperating meansReleasing devices magnetic using a motor
• F16K 31/50 - Mechanical actuating means with screw-spindle

Abstract

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.

IPC Classes  ?

• 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
• B64D 37/08 - Internal partitioning
• B29L 31/00 - Other particular articles
• B29D 23/00 - Producing tubular articles

Abstract

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.

IPC Classes  ?

• 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
• B64D 37/08 - Internal partitioning
• B29L 31/00 - Other particular articles
• B29D 23/00 - Producing tubular articles

Abstract

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.

IPC Classes  ?

• 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
• B64D 37/08 - Internal partitioning
• B64G 1/22 - Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
• 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
• B64G 1/40 - Arrangements or adaptations of propulsion systems
• B29C 53/82 - Cores or mandrels
• F17C 1/12 - Pressure vessels, e.g. gas cylinder, gas tank, replaceable cartridge with provision for thermal insulation
• B29L 31/00 - Other particular articles

Abstract

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.

IPC Classes  ?

• B29C 70/38 - Automated lay-up, e.g. using robots, laying filaments according to predetermined patterns
• B29C 53/82 - Cores or mandrels
• 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
• B64D 37/08 - Internal partitioning
• B29L 31/00 - Other particular articles
• F17C 1/12 - Pressure vessels, e.g. gas cylinder, gas tank, replaceable cartridge with provision for thermal insulation

Abstract

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.

IPC Classes  ?

• B64G 1/24 - Guiding or controlling apparatus, e.g. for attitude control
• B64G 1/10 - Artificial satellitesSystems of such satellitesInterplanetary vehicles
• B64G 1/26 - Guiding or controlling apparatus, e.g. for attitude control using jets
• B64G 1/40 - Arrangements or adaptations of propulsion systems
• B64G 1/64 - Systems for coupling or separating cosmonautic vehicles or parts thereof, e.g. docking arrangements

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.

Abstract

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.

IPC Classes  ?

• F02C 7/22 - Fuel supply systems
• F23R 3/28 - Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply

Abstract

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.

IPC Classes  ?

• B64C 30/00 - Supersonic type aircraft
• B64D 27/02 - Aircraft characterised by the type or position of power plants

Abstract

A method for preparing 3,5-dinitropyrazole, includes obtaining N-acetyl-3-nitropyrazole from pyrazole, and a sigmatropic rearrangement of the compound obtained.

IPC Classes  ?

• C07D 231/38 - Nitrogen atoms

Abstract

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.

IPC Classes  ?

• F42D 5/04 - Rendering explosive charges harmless, e.g. destroying ammunitionRendering detonation of explosive charges harmless
• F42D 5/045 - Detonation-wave absorbing or damping means

Abstract

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).

IPC Classes  ?

• 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 31/00 - Operating meansReleasing devices
• B64D 37/30 - Fuel systems for specific fuels
• 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

Abstract

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.

IPC Classes  ?

• 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 31/00 - Operating meansReleasing devices
• F16K 31/126 - Operating meansReleasing devices actuated by fluid the fluid acting on a diaphragm, bellows, or the like
• F16K 41/10 - Spindle sealings with diaphragm, e.g. shaped as bellows or tube
• B64D 37/30 - Fuel systems for specific fuels
• 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

Abstract

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.

IPC Classes  ?

• G06V 10/62 - Extraction of image or video features relating to a temporal dimension, e.g. time-based feature extractionPattern tracking
• G06T 7/20 - Analysis of motion
• G06V 10/82 - Arrangements for image or video recognition or understanding using pattern recognition or machine learning using neural networks
• G06V 20/52 - Surveillance or monitoring of activities, e.g. for recognising suspicious objects
• B64G 3/00 - Observing or tracking cosmonautic vehicles

Abstract

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.

IPC Classes  ?

• 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

Abstract

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.

IPC Classes  ?

• B09C 1/02 - Extraction using liquids, e.g. washing, leaching
• B03B 5/28 - Washing granular, powdered or lumpy materialsWet separating by sink-float separation
• B03B 9/00 - General arrangement of separating plant, e.g. flow sheets
• C06B 21/00 - Apparatus or methods for working-up explosives, e.g. forming, cutting, drying
• F42B 33/06 - Dismantling fuzes, cartridges, projectiles, missiles, rockets, or bombs

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.

IPC Classes  ?

• C01B 21/00 - NitrogenCompounds thereof
• C06B 43/00 - Compositions characterised by explosive or thermic constituents not provided for in groups

Abstract

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.

IPC Classes  ?

• F04D 29/42 - CasingsConnections for working fluid for radial or helico-centrifugal pumps
• B33Y 80/00 - Products made by additive manufacturing
• F01D 25/24 - CasingsCasing parts, e.g. diaphragms, casing fastenings
• F04D 29/52 - CasingsConnections for working fluid for axial pumps

Abstract

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.

IPC Classes  ?

• F16L 23/032 - Flanged joints the flanges being connected by members tensioned axially characterised by the shape or composition of the flanges

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.

IPC Classes  ?

• G16C 20/30 - Prediction of properties of chemical compounds, compositions or mixtures
• G16C 20/70 - Machine learning, data mining or chemometrics

Abstract

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.

IPC Classes  ?

• 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
• B29L 31/00 - Other particular articles

Abstract

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.

IPC Classes  ?

• F17C 3/00 - Vessels not under pressure
• 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
• B29L 31/00 - Other particular articles

Abstract

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.

IPC Classes  ?

• 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

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.

IPC Classes  ?

• H01Q 5/30 - Arrangements for providing operation on different wavebands
• H01Q 1/28 - Adaptation for use in or on aircraft, missiles, satellites, or balloons

Abstract

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.

IPC Classes  ?

• 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

Abstract

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.

IPC Classes  ?

• 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
• F16K 3/316 - Guiding of the slide
• F16K 3/34 - Arrangements for modifying the way in which the rate of flow varies during the actuation of the valve

Abstract

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) .

IPC Classes  ?

• B64D 37/30 - Fuel systems for specific fuels
• B64D 37/34 - Conditioning fuel, e.g. heating
• 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

Abstract

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.

IPC Classes  ?

• G01R 19/165 - Indicating that current or voltage is either above or below a predetermined value or within or outside a predetermined range of values
• G01R 31/34 - Testing dynamo-electric machines
• 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

Abstract

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.

IPC Classes  ?

• 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

Abstract

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.

IPC Classes  ?

• B64G 1/64 - Systems for coupling or separating cosmonautic vehicles or parts thereof, e.g. docking arrangements

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.

Abstract

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).

IPC Classes  ?

• B64G 1/00 - Cosmonautic vehicles
• B64G 1/64 - Systems for coupling or separating cosmonautic vehicles or parts thereof, e.g. docking arrangements
• B64G 1/62 - Systems for re-entry into the earth's atmosphereRetarding or landing devices

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.

IPC Classes  ?

• 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
• G06V 20/10 - Terrestrial scenes

Abstract

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.

IPC Classes  ?

• B64G 1/52 - Protection, safety or emergency devicesSurvival aids
• B60N 2/30 - Non-dismountable seats storable in a non-use position, e.g. foldable spare seats

Abstract

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).

IPC Classes  ?

• B64G 1/00 - Cosmonautic vehicles
• B64G 1/52 - Protection, safety or emergency devicesSurvival aids
• B64G 1/62 - Systems for re-entry into the earth's atmosphereRetarding or landing devices
• B64G 1/14 - Space shuttles
• B64G 1/64 - Systems for coupling or separating cosmonautic vehicles or parts thereof, e.g. docking arrangements
• B64G 1/60 - Crew or passenger accommodations

Abstract

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.

IPC Classes  ?

• B64G 1/00 - Cosmonautic vehicles
• B64G 1/62 - Systems for re-entry into the earth's atmosphereRetarding or landing devices
• B64G 1/40 - Arrangements or adaptations of propulsion systems

Abstract

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.

IPC Classes  ?

• D04C 3/22 - Guides or track plates
• D04C 3/40 - Braiding or lacing machines for making tubular braids by circulating strand supplies around braiding centre at equal distances

Abstract

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.

IPC Classes  ?

• D04C 3/24 - Devices for controlling spool carriers to obtain patterns, e.g. devices on guides or track plates
• D04C 3/48 - Auxiliary devices
• D04C 3/18 - Spool carriers for vertical spools
• 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

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.

Goods & Services

Downloadable computer software and executable computer software for threat analysis, namely, tracking, locating, characterizing, and describing airborne and space objects, trajectories and launches, in the aerospace and aeronautical field; Downloadable computer software and executable computer software for threat analysis, namely, tracking, locating, characterizing, and describing airborne and space objects, trajectories and launches, in the field of propelled projectiles, machinery or vehicles for civil or military use; none of the foregoing goods are related to the fields of electro-mechanics and structural, vibrational, and heat transfer analysis Computer engineering; design, development, maintenance and updating of software for threat analysis, namely, tracking, locating, characterizing, and describing airborne or space objects, trajectories and launches in the aerospace and aeronautical field and of software in the field of propelled projectiles, machinery or vehicles for civil or military use; none of the foregoing services are related to the fields of electro-mechanics and structural, vibrational, and heat transfer analysis

Abstract

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.

IPC Classes  ?

• B22F 10/80 - Data acquisition or data processing
• B33Y 50/00 - Data acquisition or data processing for additive manufacturing
• B22F 10/28 - Powder bed fusion, e.g. selective laser melting [SLM] or electron beam melting [EBM]
• G06T 7/00 - Image analysis

Abstract

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.

IPC Classes  ?

• B64G 3/00 - Observing or tracking cosmonautic vehicles

Abstract

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.

IPC Classes  ?

• B29C 65/00 - Joining of preformed partsApparatus therefor
• B64C 7/02 - Nacelles
• B29C 65/02 - Joining of preformed partsApparatus therefor by heating, with or without pressure
• B29C 65/48 - Joining of preformed partsApparatus therefor using adhesives

Abstract

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.

IPC Classes  ?

• 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

Abstract

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.

IPC Classes  ?

• F17C 1/12 - Pressure vessels, e.g. gas cylinder, gas tank, replaceable cartridge with provision for thermal insulation

Abstract

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.

IPC Classes  ?

• G01S 17/66 - Tracking systems using electromagnetic waves other than radio waves
• G01S 7/481 - Constructional features, e.g. arrangements of optical elements
• G01S 17/58 - Velocity or trajectory determination systemsSense-of-movement determination systems
• G01S 17/86 - Combinations of lidar systems with systems other than lidar, radar or sonar, e.g. with direction finders

Abstract

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.

IPC Classes  ?

• H02P 21/00 - Arrangements or methods for the control of electric machines by vector control, e.g. by control of field orientation
• H02P 21/12 - Stator flux based control involving the use of rotor position or rotor speed sensors
• H02P 21/14 - Estimation or adaptation of machine parameters, e.g. flux, current or voltage
• H02P 21/18 - Estimation of position or speed
• 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

Abstract

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.

IPC Classes  ?

• D04H 18/02 - Needling machines with needles
• 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

Abstract

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.

IPC Classes  ?

• F02K 9/60 - Constructional partsDetails not otherwise provided for
• F02K 9/44 - Feeding propellants
• 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
• F02C 7/22 - Fuel supply systems
• B64D 37/00 - Arrangements in connection with fuel supply for power plant
• F16L 3/00 - Supports for pipes, cables or protective tubing, e.g. hangers, holders, clamps, cleats, clips, brackets

Abstract

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.

IPC Classes  ?

• H01H 39/00 - Switching devices actuated by an explosion produced within the device and initiated by an electric current
• H01H 1/66 - Contacts sealed in an evacuated or gas-filled envelope, e.g. magnetic dry-reed contacts
• H01H 9/04 - Dustproof, splashproof, drip-proof, waterproof, or flameproof casings
• H01H 9/30 - Means for extinguishing or preventing arc between current-carrying parts

Abstract

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.

IPC Classes  ?

• B29C 70/74 - Moulding material on a relatively small portion of the preformed part, e.g. outsert moulding
• 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
• B64C 1/06 - FramesStringersLongerons
• H01Q 1/28 - Adaptation for use in or on aircraft, missiles, satellites, or balloons
• B29K 101/10 - Thermosetting resins
• B29K 105/08 - Condition, form or state of moulded material containing reinforcements, fillers or inserts of continuous length, e.g. cords, rovings, mats, fabrics, strands or yarns
• B29L 31/34 - Electrical apparatus, e.g. sparking plugs or parts thereof

Abstract

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.

IPC Classes  ?

• 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
• H01Q 15/14 - Reflecting surfacesEquivalent structures

Abstract

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).

IPC Classes  ?

• 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

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.

Abstract

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.

IPC Classes  ?

• 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

Abstract

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).

IPC Classes  ?

• B64G 1/40 - Arrangements or adaptations of propulsion systems
• B64G 1/22 - Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
• B64G 1/26 - Guiding or controlling apparatus, e.g. for attitude control using jets
• B64G 1/00 - Cosmonautic vehicles
• B64G 1/64 - Systems for coupling or separating cosmonautic vehicles or parts thereof, e.g. docking arrangements

Abstract

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.

IPC Classes  ?

• C06B 21/00 - Apparatus or methods for working-up explosives, e.g. forming, cutting, drying
• C06B 29/22 - Compositions containing an inorganic oxygen-halogen salt, e.g. chlorate, perchlorate the salt being ammonium perchlorate

Abstract

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.

IPC Classes  ?

• B29C 65/00 - Joining of preformed partsApparatus therefor
• B29C 65/56 - Joining of preformed partsApparatus therefor using mechanical means
• B22F 5/00 - Manufacture of workpieces or articles from metallic powder characterised by the special shape of the product
• B22F 10/25 - Direct deposition of metal particles, e.g. direct metal deposition [DMD] or laser engineered net shaping [LENS]
• F02K 9/34 - CasingsCombustion chambersLiners thereof

Abstract

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.

IPC Classes  ?

• F25J 1/00 - Processes or apparatus for liquefying or solidifying gases or gaseous mixtures

Abstract

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.

IPC Classes  ?

• 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

Abstract

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.

IPC Classes  ?

• C25B 1/28 - Per-compounds
• C25B 9/07 - Common duct cells
• C25B 9/13 - Single electrolytic cells with circulation of an electrolyte
• C25B 9/17 - Cells comprising dimensionally-stable non-movable electrodesAssemblies of constructional parts thereof
• C25B 11/03 - ElectrodesManufacture thereof not otherwise provided for characterised by shape or form perforated or foraminous
• C25B 11/043 - Carbon, e.g. diamond or graphene
• C25B 11/046 - Alloys
• C25B 15/08 - Supplying or removing reactants or electrolytesRegeneration of electrolytes
• C25B 11/036 - Bipolar electrodes

Abstract

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.

IPC Classes  ?

• C07D 231/16 - Halogen atoms or nitro radicals

Abstract

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.

IPC Classes  ?

• H01H 39/00 - Switching devices actuated by an explosion produced within the device and initiated by an electric current

Abstract

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.

IPC Classes  ?

• F02K 9/97 - Rocket nozzles
• B33Y 80/00 - Products made by additive manufacturing
• F02K 9/34 - CasingsCombustion chambersLiners thereof
• F02K 9/62 - Combustion or thrust chambers
• B22F 10/25 - Direct deposition of metal particles, e.g. direct metal deposition [DMD] or laser engineered net shaping [LENS]
• B33Y 10/00 - Processes of additive manufacturing

Abstract

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.

IPC Classes  ?

• F02K 9/34 - CasingsCombustion chambersLiners thereof
• F02K 9/62 - Combustion or thrust chambers
• 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

Abstract

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.

IPC Classes  ?

• F16L 9/19 - Multi-channel pipes or pipe assemblies
• F16L 59/14 - Arrangements for the insulation of pipes or pipe systems
• F16L 9/00 - Rigid pipes
• B33Y 80/00 - Products made by additive manufacturing

Abstract

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).

IPC Classes  ?

• 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
• G01K 19/00 - Testing or calibrating calorimeters

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.

IPC Classes  ?

• G16C 20/30 - Prediction of properties of chemical compounds, compositions or mixtures
• G16C 20/40 - Searching chemical structures or physicochemical data
• G16C 20/70 - Machine learning, data mining or chemometrics

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.

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

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

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).

IPC Classes  ?

• 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

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.

IPC Classes  ?

• C07D 259/00 - Heterocyclic compounds containing rings having more than four nitrogen atoms as the only ring hetero atoms
• C06B 43/00 - Compositions characterised by explosive or thermic constituents not provided for in groups

Abstract

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.

IPC Classes  ?

• F42D 5/045 - Detonation-wave absorbing or damping means

Abstract

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.

IPC Classes  ?

• 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

Abstract

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.

IPC Classes  ?

• 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
• F42B 33/06 - Dismantling fuzes, cartridges, projectiles, missiles, rockets, or bombs

Abstract

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).

IPC Classes  ?

• 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

Abstract

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.

IPC Classes  ?

• F02K 9/97 - Rocket nozzles

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.

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.

Abstract

A gas-generating pyrotechnic composition has a high gas yield while having reduced generation of condensable species and a limited combustion temperature.

IPC Classes  ?

• C06D 5/06 - Generation of pressure gas, e.g. for blasting cartridges, starting cartridges, rockets by reaction of two or more solids
• A62C 35/02 - Permanently-installed equipment with containers for delivering the extinguishing substance

Abstract

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).

IPC Classes  ?

• 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
• F16K 3/316 - Guiding of the slide

Abstract

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.

IPC Classes  ?

• B64G 1/14 - Space shuttles
• B64G 1/62 - Systems for re-entry into the earth's atmosphereRetarding or landing devices
• B64G 1/36 - Guiding or controlling apparatus, e.g. for attitude control using sensors, e.g. sun-sensors, horizon sensors
• B64G 1/40 - Arrangements or adaptations of propulsion systems