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.

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.

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.

Abstract: A process for removing webs formed on a wall of a central channel of a propellant charge, the process including removing webs by levelling the wall of the central channel of the propellant charge with a levelling tool installed on an articulated robotic arm during which the movements of the robot arm are controlled by a user interface which includes a controller configured to be used by a user; a force sensor measures the force applied by the levelling tool; a control unit connected to the force sensor regulates the movements of the robot arm by maintaining the force applied by the levelling tool below a first predetermined force threshold, the control unit also regulating the movements of the robot arm by maintaining a movement speed of the levelling tool which is below a predetermined speed threshold value.

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.

Abstract: A multilayer strip intended to be wound on a form, includes pre-impregnated fiber layers superimposed along a stacking direction, each layer extending widthwise along a transverse direction perpendicular to the stacking direction between a first and a second edge, wherein on at least a portion of the multilayer strip the first edges of the pre-impregnated fiber layers are aligned with each other in the stacking direction, and each second edge is recessed relative to the second edge of the underlying layer in the transverse direction.

Abstract: A multilayer strip intended to be wound on a form to manufacture a part in composite material, includes superposed fibrous layers, at least one of these layers being pre-impregnated, the superposed fibrous layers including a first layer including a first material on a first side of the width of the strip and a second material, differing from the first material, on a second side of the width of the strip opposite the first side, and a second layer superposed on the first layer and including the first material on the first side and the second material on the second side, with overlapping of a material of the second layer over a different material of the first layer.

Abstract: A method for determining a fault for a set of sensors, comprising: obtaining data, said data comprising a plurality of measurements returned respectively by the sensors and a plurality of estimates determined respectively by a plurality of estimators taking as input different subsets of said measurements, at least one of the estimators comprising an artificial neural network; calculating residuals representative of the deviation between data representing the same physical quantity; 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.

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.

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.

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.

Abstract: A process for manufacturing a polybenzoxazine monomer, crosslinking the latter, and using the crosslinked product to form an ablative thermal protection system for a thruster nozzle or atmospheric reentry body.

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.

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.

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.

Abstract: An acoustic attenuation panel including: a main layer made of a porous material and having two opposite faces; a coating layer arranged on one of the two faces of the main layer; an adhesive film, arranged at the interface between the main layer and the coating layer to assemble same. The main layer is a body made of melamine resin foam having a density between 6 and 6.8 kg/m3 and a porosity rate between 0.978 and 0.984; the coating layer is a fabric with a density between 484 and 526 kg/m3 and a porosity rate between 0.771 and 0.817; the adhesive film is a film made of a thermoplastic material provided with holes passing through and having a surface density between 40 g/m2 and 56 g/m2.

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.

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.

Abstract: TA method for treating an aqueous solution containing ammonium perchlorate and optionally nitrate ions, the method having a nitrification/denitrification sequence then a step of reducing perchlorates, the liquid effluent obtained at the end of this step of reducing perchlorates being subjected to a first membrane filtration, the liquid effluent obtained following this first membrane filtration being put into contact, in a reactor in aerobic conditions, with microorganisms able to carry out the oxidation of organic materials, then the liquid effluent leaving this reactor being subjected to a second membrane filtration, the first membrane filtration and the second membrane filtration being carried out on the same membrane filtration unit.

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.