Abstract: An electrodynamic assembly for propelling a spacecraft in orbit around a celestial body having a magnetic field is disclosed. The assembly includes a plurality of coaxial cables for an electrodynamic assembly for propelling a spacecraft in orbit around a celestial body having a magnetic field. Each coaxial cable includes an electrically conductive core surrounded by a first electrically insulating sheath, and an electrically conductive current return circuit mounted outside the first electrically insulating sheath. The current return circuit includes a first end electrically connected to a first end of the core of the coaxial cable.

Abstract: There is provided a hygiene monitoring device including a sensing panel. The sensing panel has an elongate flexible panel defining a longitudinal axis. The elongate flexible panel includes a first pair of plates spaced apart from each other in a direction crossing the longitudinal axis. The elongate flexible panel also includes a second pair of plates spaced apart from each other in a direction crossing the longitudinal axis. The first pair of plates and the second pair of plates are disposed on a flexible substrate of the elongate flexible panel. Each plate of the first pair of plates and each plate of the second pair of plates is elongate along the longitudinal axis of the elongate flexible panel. The hygiene monitoring device is configured to measure the impedance between two of the plates.

Abstract: There is provided a system including a wearable absorbent hygiene article defining a front waist region, a back waist region, a crotch region and a longitudinal axis. The wearable absorbent hygiene article includes a liquid permeable top layer, a back layer opposite to the top layer, and an absorbent core in the crotch region and located between the top layer and the back layer. The absorbent core has a core length along the longitudinal axis. The system further includes a hygiene monitoring device including a sensing panel, which has an elongate flexible panel defining a longitudinal axis and having plates. The hygiene monitoring device is configured to measure the impedance between two of the plates. The extent of the plates along the longitudinal axis of the elongate flexible panel defines a sensing length. The sensing length is 50% to 100% of the core length.

Abstract: A flow rate regulator device is provided, including an upstream chamber, a downstream chamber, a plurality of electrically conductive capillary ducts providing parallel fluid flow connections between the upstream chamber and the downstream chamber, first and second electrical terminals configured to be connected to an electric current source, and at least one electric switch configured to connect one or more of the capillary ducts selectively between the electrical terminals. A system for feeding propellant gas to a space electric thruster is also provided, including at least one such flow rate regulator device to regulate a propellant gas flow rate. And, a flow rate regulation method is provided, using the flow rate regulator device.

Abstract: An electrodynamic assembly for propelling a spacecraft in orbit around a celestial body having a magnetic field is disclosed. The assembly includes a plurality of coaxial cables for an electrodynamic assembly for propelling a spacecraft in orbit around a celestial body having a magnetic field. Each coaxial cable includes an electrically conductive core surrounded by a first electrically insulating sheath, and an electrically conductive current return circuit mounted outside the first electrically insulating sheath. The current return circuit includes a first end electrically connected to a first end of the core of the coaxial cable.

Abstract: A flow rate regulator device is provided, including an upstream chamber, a downstream chamber, a plurality of electrically conductive capillary ducts providing parallel fluid flow connections between the upstream chamber and the downstream chamber, first and second electrical terminals configured to be connected to an electric current source, and at least one electric switch configured to connect one or more of the capillary ducts selectively between the electrical terminals. A system for feeding propellant gas to a space electric thruster is also provided, including at least one such flow rate regulator device to regulate a propellant gas flow rate. And, a flow rate regulation method is provided, using the flow rate regulator device.

Abstract: A Hall effect thruster includes at least one tank of gas under high pressure, a pressure regulator module, a gas flow rate control device, an ionization channel, a cathode placed in a vicinity of an outlet from the ionization channel, an anode associated with the ionization channel, an electrical power supply unit, an electric filter, coils for creating a magnetic field around the ionization channel, and an additional electrical power supply unit for applying a pulsating voltage between the anode and the cathode.

Abstract: A Hall effect thruster including: a discharge channel with an open downstream end; a cathode situated outside the discharge channel; an injector system configured to inject atoms of gas into the discharge channel, the injector system situated at an upstream end of the discharge channel and also forming a cathode; a heater device configured to heat the cathode; a measurement mechanism measuring temperature of the heater device, and a regulator circuit regulating the temperature such that the heater device heats so long as its temperature is less than a threshold temperature from which the thruster is capable of starting, and ceases to heat shortly after the threshold temperature has been reached.

Abstract: An electric thruster includes at least one electric engine, a feed system for the engine including a high-pressure tank of ionizable gas, a low-pressure buffer tank connected to the high-pressure tank by a valve, and a system of pipes for conveying the gas from the low-pressure buffer tank to an anode and to a cathode of the engine. The low-pressure buffer tank is in open connection with the engine. The thruster detects that a magnitude of the discharge current between the anode and the cathode is less than a threshold value and switches off the discharge voltage as a result of the detection. The thruster can be for use in a satellite.

Abstract: A Hall effect thruster includes at least one tank of gas under high pressure, a pressure regulator module, a gas flow rate control device, an ionization channel, a cathode placed in a vicinity of an outlet from the ionization channel, an anode associated with the ionization channel, an electrical power supply unit, an electric filter, coils for creating a magnetic field around the ionization channel, and an additional electrical power supply unit for applying a pulsating voltage between the anode and the cathode.

Abstract: An electric thruster includes at least one electric engine, a feed system for the engine including a high-pressure tank of ionizable gas, a low-pressure buffer tank connected to the high-pressure tank by a valve, and a system of pipes for conveying the gas from the low-pressure buffer tank to an anode and to a cathode of the engine. The low-pressure buffer tank is in open connection with the engine. The thruster detects that a magnitude of the discharge current between the anode and the cathode is less than a threshold value and switches off the discharge voltage as a result of the detection.

Abstract: A Hall effect thruster including: a discharge channel with an open downstream end; a cathode situated outside the discharge channel; an injector system configured to inject atoms of gas into the discharge channel, the injector system situated at an upstream end of the discharge channel and also forming a cathode; a heater device configured to heat the cathode; a measurement mechanism measuring temperature of the heater device, and a regulator circuit regulating the temperature such that the heater device heats so long as its temperature is less than a threshold temperature from which the thruster is capable of starting, and ceases to heat shortly after the threshold temperature has been reached.

Abstract: A method and system for determining a deviation of a vehicle from a desired course are described. The method includes receiving bearing signals from a transmitter, accessing a database, on the vehicle, to obtain transmitter position information identifying a position of the transmitter, obtaining vehicle position information using GPS identifying a current position of the vehicle, and determining a deviation of the vehicle from the desired course utilizing the transmitter position information, the vehicle position information, and the bearing signal.

Abstract: A method and system for determining a deviation of a vehicle from a desired course are described. The method includes receiving bearing signals from a transmitter, accessing a database, on the vehicle, to obtain transmitter position information identifying a position of the transmitter, obtaining vehicle position information using GPS identifying a current position of the vehicle, and determining a deviation of the vehicle from the desired course utilizing the transmitter position information, the vehicle position information, and the bearing signal.