Abstract: A control arrangement for a vehicle motion system including a braking function, comprising motion actuators with one or more brake actuators pertaining to the braking function, a first vehicle motion management controller (VMM1) and a second vehicle motion management controller (VMM2), forming a redundant assembly to control the braking function, wherein, in riding conditions, the first vehicle motion management controller controls the brake actuators with a current nominal expected braking performance, while the second vehicle motion management controller (VMM2) is in a waiting-to-operate mode, the control arrangement comprising a hot swap functionality in which the second vehicle motion management controller (VMM2) is configured to take over control of the brake actuators from the first vehicle motion management controller, with the current nominal expected braking performance, in a short time period (SWT) less than one second, preferably less than 0.5 second, preferably less than 0.

Abstract: The invention relates to a method of controlling a heavy-duty vehicle in a slope when the vehicle has come to a standstill due to service brakes of the vehicle having applied a service brake force, the method comprising determining a total brake force required for maintaining the vehicle at standstill, activating at least one park brake for providing a park brake force, gradually increasing the park brake force, and, while the park brake force is gradually increased, gradually reducing the service brake force while maintaining the sum of the service brake force and the park brake force at least equal to the determined total brake force.

Abstract: A control arrangement for a vehicle motion system including a braking function, comprising motion actuators with one or more brake actuators pertaining to the braking function, a first vehicle motion management controller (VMM1) and a second vehicle motion management controller (VMM2), forming a redundant assembly to control the braking function, wherein, in riding conditions, the first vehicle motion management controller controls the brake actuators with a current nominal expected braking performance, while the second vehicle motion management controller (VMM2) is in a waiting-to-operate mode, the control arrangement comprising a hot swap functionality in which the second vehicle motion management controller (VMM2) is configured to take over control of the brake actuators from the first vehicle motion management controller, with the current nominal expected braking performance, in a short time period (SWT) less than one second, preferably less than 0.5 second, preferably less than 0.

Abstract: A radial magnetic bearing having an inner rotor including a central shaft having a ferromagnetic armature mounted on the shaft and an outer stator providing a plurality of electromagnets including poles made of ferromagnetic material which project radially inwardly towards the rotor is provided. As such, air-gaps (e) are left between end faces of the poles and the ferromagnetic armature, and coils wound around the poles. The poles are extended through outer portions attached to a supporting member. Each pole and the corresponding outer portion are included in an angularly segmented module providing a stack of laminations made of ferromagnetic material. The outer portion defines shoulders with respect to the corresponding pole, the outer portion contacting outer portions of neighboring segmented modules and the outer portions of all segmented modules being assembled by clamping rings, wherein the coils located in free spaces around the poles are mounted in a string.

Abstract: A reaction propulsion device in which a first feed circuit for feeding a main thruster with a first propellant includes a branch connection downstream from a pump of a first turbopump, which branch connection passes through a first regenerative heat exchanger and a turbine of a first turbopump, and in which a second feed circuit for feeding the main thruster with a second propellant includes, downstream from a pump of a second turbopump, a branch-off passing through a second regenerative heat exchanger and a turbine of the second turbopump. At least one secondary thruster is connected downstream from the turbines of the first and second turbopumps.

Abstract: An electrical device comprising a housing having cooling fins located in a central portion along an exterior surface of the housing and a laminated magnetic stack disposed within the housing and interfacing with an interior surface of the housing at the central portion. The cooling fins are configured alternatively higher and smaller on an inlet manifold and in opposition on an outlet manifold.

Abstract: A spacecraft including at least one main propellant tank, a main engine fed with propellant by the main tank, and a de-orbiting device. The de-orbiting device includes a detonation engine fed with propellant by the main tank.

Abstract: A combined engine includes a turbopump including a pump injecting hydrogen into a heater arranged in an outer casing downstream from a central body, and a subsonic turbine driving the pump, which turbine receives partially-expanded hydrogen collected at an outlet from the heater to apply the hydrogen to a supersonic turbine to operate the engine as a turbojet. The hydrogen from the supersonic turbine is collected in tubes inside the central body to be sent to a combustion chamber defined downstream from the central body, while the hydrogen that is partially expanded in the subsonic turbine is sent directly to the combustion chamber via injectors to operate the engine as a ramjet.

Abstract: A spacecraft including at least one main propellant tank, a main engine fed with propellant by the main tank, and a de-orbiting device. The de-orbiting device includes a detonation engine fed with propellant by the main tank.

Abstract: An electrical device comprising a housing having cooling fins located in a central portion along an exterior surface of the housing and a laminated magnetic stack disposed within the housing and interfacing with an interior surface of the housing at the central portion. The cooling fins are configured alternatively higher and smaller on an inlet manifold and in opposition on an outlet manifold.

Abstract: A radial magnetic bearing having an inner rotor including a central shaft having a ferromagnetic armature mounted on the shaft and an outer stator providing a plurality of electromagnets including poles made of ferromagnetic material which project radially inwardly towards the rotor is provided. As such, air-gaps (e) are left between end faces of the poles and the ferromagnetic armature, and coils wound around the poles. The poles are extended through outer portions attached to a supporting member. Each pole and the corresponding outer portion are included in an angularly segmented module providing a stack of laminations made of ferromagnetic material. The outer portion defines shoulders with respect to the corresponding pole, the outer portion contacting outer portions of neighboring segmented modules and the outer portions of all segmented modules being assembled by clamping rings, wherein the coils located in free spaces around the poles are mounted in a string.

Abstract: A rocket engine comprises a prechamber and a combustion chamber, two respective feed pipes of the engine, and two turbopumps. The engine is a staged combustion engine. A jet pump is arranged in at least a first feed pipe. After being pressurized, a portion of the fluid flowing in the first feed pipe is directed to the jet pump in order to enable the jet pump to entrain the fluid flowing in said feed pipe to the admission orifice of said first pump, thereby raising the pressure at the feed orifice of the pump.

Abstract: A reaction propulsion device in which a first feed circuit for feeding a main thruster with a first propellant includes a branch connection downstream from a pump of a first turbopump, which branch connection passes through a first regenerative heat exchanger and a turbine of a first turbopump, and in which a second feed circuit for feeding the main thruster with a second propellant includes, downstream from a pump of a second turbopump, a branch-off passing through a second regenerative heat exchanger and a turbine of the second turbopump. At least one secondary thruster is connected downstream from the turbines of the first and second turbopumps.

Abstract: A combined engine includes a turbopump including a pump injecting hydrogen into a heater arranged in an outer casing downstream from a central body, and a subsonic turbine driving the pump, which turbine receives partially-expanded hydrogen collected at an outlet from the heater to apply the hydrogen to a supersonic turbine to operate the engine as a turbojet. The hydrogen from the supersonic turbine is collected in tubes inside the central body to be sent to a combustion chamber defined downstream from the central body, while the hydrogen that is partially expanded in the subsonic turbine is sent directly to the combustion chamber via injectors to operate the engine as a ramjet.