Abstract: A fueling device for fueling the thrusters of a launcher is disclosed. The device includes a ground module and an on-board module. The ground module having at least: a ground pipe; a ground valve; and a ground plate provided with a ground passage, and the on-board module having at least: an on-board pipe; an on-board valve; and an onboard plate provided with an on-board passage. The device also includes a hydraulic coupling system between the onboard module and the ground module enabling fluid communication to be established between the ground passage and the on-board passage. A first annular enclosure is situated between the on-board plate and the ground plate around the hydraulic coupling system that, when connected to suction, enables the on-board plate and the ground plate to be held in a connected-together position.

Abstract: A Hall effect plasma thruster including an annular discharge channel around a main axis presenting an open downstream end and defined between an inner wall and an outer wall, at least one cathode, a magnetic circuit for creating a magnetic field in the channel, a pipe for feeding ionizable gas to the channel, an anode, and a manifold placed in the upstream end of the channel. The manifold is connected to the pipe and enables the ionizable gas to flow into the ionization zone of the channel in concentric manner around the main axis. The anode acts as a manifold, and the manifold includes a directional mechanism that gives rise at an outlet from the manifold to swirling motion of the gas around the main axis.

Abstract: The invention relates to a separator device for separating the on-board and ground portions of a launcher fueling module, the device comprising: a locking system having a locking finger (50) mounted on the ground portion (22) and having a blocking portion (523), and a locking pin (42) on the on-board portion (21) co-operating by engaging with the blocking portion (523) in order to hold the on-board portion (21) and the ground portion (22) in a locking position. The separator system further comprises an actuation system that, under vertical movement of the launcher (10), enables the blocking portion (523) to be disengaged from the locking pin (42), whereby the on-board portion (21) is suitable for being separated from the ground portion (22). The invention also provides a method of separating the on-board and ground portions of a launcher fueling module, which method is implemented by means of such a separator device.

Abstract: A Hall effect plasma thruster including an annular discharge channel around a main axis presenting an open downstream end and defined between an inner wall and an outer wall, at least one cathode, a magnetic circuit for creating a magnetic field in the channel, a pipe for feeding ionizable gas to the channel, an anode, and a manifold placed in the upstream end of the channel. The manifold is connected to the pipe and enables the ionizable gas to flow into the ionization zone of the channel in concentric manner around the main axis. The anode acts as a manifold, and the manifold includes a directional mechanism that gives rise at an outlet from the manifold to swirling motion of the gas around the main axis.

Abstract: The invention relates to a separator device for separating the on-board and ground portions of a launcher fueling module, the device comprising: a locking system having a locking finger (50) mounted on the ground portion (22) and having a blocking portion (523), and a locking pin (42) on the on-board portion (21) co-operating by engaging with the blocking portion (523) in order to hold the on-board portion (21) and the ground portion (22) in a locking position. The separator system further comprises an actuation system that, under vertical movement of the launcher (10), enables the blocking portion (523) to be disengaged from the locking pin (42), whereby the on-board portion (21) is suitable for being separated from the ground portion (22). The invention also provides a method of separating the on-board and ground portions of a launcher fueling module, which method is implemented by means of such a separator device.

Abstract: The invention relates to a fueling device for fueling the thrusters of a launcher. In characteristic manner, the device comprises: a ground module (20) comprising at least: a ground pipe (22); a ground valve (21); and a ground plate (26) provided with a ground passage (28); an on-board module (30) comprising at least: an on-board pipe (38); an on-board valve (36); and an on-board plate (32) provided with an on-board passage (34); and a hydraulic coupling system (40) between the on-board module (30) and the ground module (20) enabling fluid communication to be established between the ground passage (28) and the on-board passage (34), and a first annular enclosure (50) situated between the on-board plate (32) and the ground plate (26) around the hydraulic coupling system (40) that, when connected to suction, it enables the on-board plate (32) and the ground plate (26) to be held in a connected-together position.

Abstract: The invention provides a control valve device enabling the positioning precision of its abutment to be reduced without reducing the overall control precision of the valve. For this purpose, the valve device comprises a valve body defining a fluid flow duct in which there is disposed a shutter element turned by an actuator by means of a drive shaft. The shutter element is formed by a skirt presenting a notch forming an opening in the wall of the skirt. The notch is shaped in such a manner as to define a variable flow passage in the duct as a function of the angular position of the shutter element between an open position in which the notch co-operates in full with the duct, and a closed position in which said skirt closes the duct.

Abstract: The invention provides a cryogenic valve device comprising a valve body in which a cryogenic fluid flows, and a valve member disposed in the duct and connected to a control rod for moving the valve member between a closed position and an open position so as to control the flow rate of the cryogenic fluid. The device further comprises a pneumatic actuator having a chamber containing a piston in connection with the control rod, the chamber being fed with control gas to position the piston in a determined position. The actuator is fixed to the valve body via a chamber interposed between the actuator and the valve body in such a manner as to decouple the actuator thermally from the valve body so as to maintain the temperature of the actuator, and consequently the temperature of the control gas, at a temperature that is intermediate between the temperature of the valve body and ambient temperature.

Abstract: The present invention relates to an electrically controlled leakproof valve having a fluid feed channel and at least one channel for delivering said fluid, rotary displacement of a distributor plug in said valve being under the control of an actuator. The actuator comprises an axially pierced rotor through which the fluid from the feed channel flows without headloss, the actuator being connected to the valve body in leakproof manner without using dynamic sealing devices. The present leakproof valve is particularly suitable for use in corrosive environments, and in particular under cryogenic conditions.