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Matches 1 - 50 out of 9,501

Document Document Title
WO/2019/097170A1
The invention relates to an aircraft propulsion assembly with an engine provided with a cascade-type thrust reverser with cascades of mobile deflection vanes (43). The cascades of deflection vanes (43) are connected to cascade rails (45)...  
WO/2019/097159A1
Disclosed is a pipe/flange assembly intended for use with a pressurization system of an aeronautical vessel, said assembly comprising a flange (10) having a main part (12) with an orifice (11) and a sleeve (14) projecting from the main p...  
WO/2019/098473A1
The present invention relates to a partial structure of a rocket, which includes a satellite launcher engine and an auxiliary engine added thereto, to enable continuous ignition by a spark method, and more specifically, proposes a contin...  
WO/2019/092383A1
The present invention relates to a thrust reverser (6) for a turbojet engine nacelle (1), comprising at least one movable cover (20) mounted on a fixed structure of the reverser (6), moveable between a closed position, in which it ensure...  
WO/2019/086616A1
The present invention relates to a swirling element for swirling a fluid flow for a rotating aerodynamic profile or a turbine, comprising: a fastening portion, which is designed for fastening to a profile surface; and a flow-active porti...  
WO/2019/086647A1
A device serves for the repeated generation of explosions, in particular for the drive of an aircraft. It comprises: ∙ a combustion chamber (21), ∙ at least one feed line for feeding a flowable, explosive material or components which...  
WO/2019/081865A1
The lock for a cowl (1) of a thrust reverser borne by a nacelle (4) comprises: a catch (16) fixed on the cowl; and a hook (12) that is configured to engage in the catch and is elastically returned (15) towards engagement with the catch; ...  
WO/2019/081864A1
The invention relates to a propulsion unit (1) for an aircraft, comprising a nacelle (2) comprising a turbojet (8) supported by a pylon (3), the nacelle (2) comprising: an outer shroud (9), a fixed internal structure (4) defining, with t...  
WO/2019/077365A1
An emergency landing apparatus (100) for an aircraft and a method of operating the emergency landing apparatus is provided. The emergency landing apparatus comprises: one or more rocket motors (30) arranged to eject efflux in order to pr...  
WO/2019/079137A1
A control system for a satellite comprises a power source and control system, a propulsion system having individually selectable solid fuel motors, a communication interface and an attitude determination and control system (ADCS). The AD...  
WO/2019/076524A1
The invention relates to an injector (1) for metering liquid and gaseous fuel, comprising an injector body (2) in which a pressure chamber (3) is formed that can be filled with gaseous fuel, wherein a piston-shaped outer nozzle needle (5...  
WO/2019/075051A1
A thruster has a first stage and a second stage. The first stage is a plasma source that outputs a plasma. The second stage is an accelerator. In one embodiment, the second stage is a plasma accelerator that accelerates the plasma. In an...  
WO/2019/071289A1
A polymer composite composition for use in high temperature applications such as furnaces, heat shields and aeronautical jet and rocket motors. In a particular application, the disclosed composition is applied to the manufacture of rocke...  
WO/2019/073436A1
An inner coating layer for solid-propellant rocket engines, constituted by a material comprising from 45% to 55% wt. of a a cross-linkable, unsaturated-chain polymer base, from 11% to 13% wt. of silica, from 15% to 25% wt. of vulcanizing...  
WO/2019/073437A1
A solid-propellant rocket engine (1) has a casing (2) and a thermal protection (15) internally coating the casing and delimiting a housing (17), which contains a mass of solid propellant (3); the thermal protection has a fixed portion (2...  
WO/2019/073167A1
The invention relates to thermal protection (18) comprising, superposed on one another in order, a metal plate, a first layer of insulating material, a layer of refractory fibres, and a second layer of insulating material, the metal plat...  
WO/2019/068996A1
The invention concerns the production in composite material of a lobed structure (10) of a mixer, which comprises a portion having a plurality of lobes (17,19). For this purpose, a fibrous preform is produced containing a resin, in a sim...  
WO/2019/069306A1
A pulsejet engine is provided, comprising a combustion chamber spanning between an inlet and end and an outlet end for combustion therein of a mixture of fuel and air, an intake regulator configured to selectively open and close one or m...  
WO/2019/063938A1
The invention relates to an assembly having a holder (10) configured to be fastened to a spacecraft, a thruster, a damping device (50), the damping device (50) having at least two electrodes (50b) and at least one electroactive polymer (...  
WO/2019/063935A1
The invention relates to an injection wall (10) for a rocket engine combustion chamber, said wall being provided with a plurality of injection orifices (20), wherein the majority of said injection orifices (20) are arranged in an asymmet...  
WO/2019/063939A1
The invention relates to an assembly having a holder (10) configured to be fastened to a spacecraft, a thruster, an orientation device (40) having at least one actuator (44) that is able to modify the orientation of the thruster, the act...  
WO/2019/058054A1
A method for producing a part from composite material comprises the following steps: - injecting into a fibrous texture (10) a slurry (BC) comprising at least one powder of refractory ceramic particles (CR) suspended in a liquid phase, -...  
WO/2019/059401A1
The three-dimensional additively-formed product comprises: a body section; and a male threaded part integrally formed with the surface of the body section in a projecting manner. The male threaded part has a trailing flank forming a firs...  
WO/2019/058069A1
The invention relates to a method for manufacturing a part using CMC, i.e. a ceramic matrix composite material, as well as such a part made of CMC, the method comprising the following steps: providing (E1) a fibrous reinforcement (10); i...  
WO/2019/052886A1
In an exhaust gas duct for exhaust gases of gas turbines (1) having a housing (6) made of metal, an inner lining (30) made of metal and supported by the housing (6), and insulation (9) arranged between the housing (6) and the inner linin...  
WO/2019/050511A1
An internal combustion engine with a piston having a piston head with a resonance cavity opening onto the head, and where a fuel nozzle located in a cylinder head is positioned to inject a fuel such as natural gas into the combustion cha...  
WO/2019/045997A1
A disc turbine engine with a multi disc engine where each disc engine includes a turbine blade, a low-pressure compressor blade, a high-pressure compressor blade, and a bearing. Each disc engine runs freely and individually, counter-rota...  
WO/2019/045669A1
A pulsed compressive detonation device comprises a piston compressor (1) consisting of at least a cylinder (2) that houses a piston (3) provided with a reciprocating motion actuator (4), an intake manifold (6) connected to the cylinder (...  
WO/2019/043343A1
The invention relates to a thrust reverser for a turbojet engine nacelle, comprising thrust reversal cascade vanes (10) arranged about an annular flow duct comprising a stationary front casing (2); at least one movable cover (4) moving b...  
WO/2019/043326A1
Disclosed is a method for managing the thrust of a rocket engine (100) by which an initial thrust setpoint (PGCc ini) is computed. Taking into account at least one limitation of the electrical power supply (104), a filtered thrust setpoi...  
WO/2019/043342A1
The invention relates to a sealing device (6) for an aircraft turbojet engine nacelle, comprising a seal (61) provided with a tubular part (611), a support element (62) accepting this seal (61) in a sealing position, and an attachment sy...  
WO/2019/038510A1
The invention relates to a twin-spool turbojet engine (1) comprising: – a low-pressure spool (3), comprising a low-pressure compressor (31), a low-pressure turbine (32) and a low-pressure shaft (33) connecting the low-pressure turbine ...  
WO/2019/038501A1
A supply system (1) for supplying a rocket engine with at least one propellant, the supply system (1) comprising at least one supply circuit (10) able to circulate the propellant and at least one tank (20) in fluid communication with the...  
WO/2019/038503A1
An assembly for the rear of a bypass turbomachine (10) comprises a primary nozzle (11) comprising a trailing edge defining a primary flow path portion and a secondary nozzle (110) defining a secondary flow path portion, defined about a l...  
WO/2019/038505A1
A panel (3) for a nacelle of an aircraft propulsion assembly, comprising two skins (31, 32) and a cell structure provided with transverse partitions defining cells (344, 345). The cell structure comprises folds (35) each comprising at le...  
WO/2019/037816A1
The invention relates to a jet engine, which has a stationary housing, in which housing a primary flow is formed, in which inflowing air is burned in at least one combustion chamber, and in which housing a secondary flow is formed, in wh...  
WO/2019/036053A1
A system that includes a turbofan engine, a nacelle surrounding the engine and defining an annular bypass duct through the engine to define a generally forward-to-aft bypass air flow path, a thrust reverser movable to and from a reversin...  
WO/2019/034851A1
The present invention provides a vehicle comprising: a rotor and a stator; at least one planar control surface coupled to the rotor, wherein the rotor is configured to rotate relative to the stator such that, in use, the at least one pla...  
WO/2019/030462A1
A method for manufacturing a fibrous tubular structure (11) comprising lobes (9), in which fibres (13, 15) are draped/deposited on a mandrel (19) having a shape corresponding to that of this fibrous structure (11), this draping/depositio...  
WO/2019/030454A1
The invention relates to a thrust reverser cascade (1) for an aircraft nacelle, comprising a plurality of blades (2) having a first (6a) and a second surface (6b), the blades (2) being connected to members (3, 4) connected to attachment ...  
WO/2019/021234A1
A space propulsion system (1), having reduced sizes, is designed specifically for the application on miniaturised satellites, but it can be scaled easily based upon a wide range of sizes of the target vehicle, and it comprises: a combust...  
WO/2019/020995A1
A nacelle for an aircraft having a thrust reverser including a translating cowl and a blocking panel. The blocking panel is connected by a pivot connection and is connected to the translating cowl by a sliding connection including an eng...  
WO/2019/020951A1
Method for detecting ignition in a combustion chamber (10) of a rocket motor, in which : A) for each of the propellants (H,O), values are acquired for parameters that make it possible to calculate the mean values PGC_H0, PGC_H1 and the s...  
WO/2019/014386A1
A system for enhancing the thrust produced by an aircraft propulsion element having a propulsion fluid outlet includes a shroud element having an inlet, an outlet and a diffusing section positioned between the shroud element inlet and sh...  
WO/2019/009235A1
This combustion chamber cooling mechanism is provided with: a bottom wall in contact with a combustion chamber; an upper wall disposed on the opposite side of the combustion chamber from the bottom wall; and a plurality of sidewalls whic...  
WO/2019/005937A1
A vehicle, includes a main body. A fluid generator is coupled to the main body and produces a fluid stream. At least one tail conduit is fluidly coupled to the generator. First and second fore ejectors are coupled to the main body and re...  
WO/2019/002753A1
The invention relates to a nacelle for a turbojet comprising a thrust reverser comprising cascades (14), movable cowls adjacent to these cascades (14) in a closed position, connection systems for connecting the cowls and the cascades (14...  
WO/2019/000932A1
An inter-stage segment structure for a carrier and a carrier. The inter-stage segment structure for a carrier comprises an annular skin (1). A first edge of the skin (1) is provided with a lower end frame (6); a middle frame (8) is provi...  
WO/2018/234766A1
A rocket motor for a vertical take-off and landing (VTOL) aircraft is provided, along with control circuitry and computer programs for controlling the rocket motor, the methods of using the rocket motor. The rocket motor may define an el...  
WO/2018/229317A4
A jet engine (1) with continuous and discontinuous impulse, which comprises a diffuser (2) with a cylindrical exterior shape, a combustion chamber (3), and several fuel injection means (19) and a nozzle (4), both with same exterior shape...  

Matches 1 - 50 out of 9,501