A rotor, a magnetic bearing, and a drive unit that rotationally drives the rotor. The magnetic bearing includes a bearing stator and a ring-shaped bearing rotor member. The drive unit has a drive stator and a ring-shaped drive rotor member. The bearing stator has a plurality of bearing stator cores consisting of a magnetic material, disposed on an outer peripheral side of the bearing rotor member. The bearing stator core has a first portion extending in a first direction orthogonal to a direction facing the bearing rotor member, and a pair of second portions extending to a bearing rotor member side from both end portions in the first direction of the first portion. The drive stator is formed so as to pass through a position between an outer peripheral surface of the rotor and the first portion core and between the pair of second portions.

The invention discloses a position measuring mechanism and a measuring method of a linear motion system in which two sensors are respectively disposed on two sides of a stator, in addition to allowing a moving portion to perform bidirectional movement, under a premise of not increasing a quantity of the sensors, a measuring range of the sensors can be calculated based on information measured by the sensors themselves. Furthermore, the invention further combines measurement sections respectively measured by the two sensors to ensure an accuracy of position feedback, instead of the conventional technique using an operational method of combining sinusoidal and cosine signals.

The invention discloses a position measuring mechanism and a measuring method of a linear motion system in which two sensors are respectively disposed on two sides of a stator, in addition to allowing a moving portion to perform bidirectional movement, under a premise of not increasing a quantity of the sensors, a measuring range of the sensors can be calculated based on information measured by the sensors themselves. Furthermore, the invention further combines measurement sections respectively measured by the two sensors to ensure an accuracy of position feedback, instead of the conventional technique using an operational method of combining sinusoidal and cosine signals.

A lubricant supported electric motor includes an outer stator and an inner stator each extending around an axis in radially spaced relationship with one another. A rotor is rotatably disposed between the inner and outer stators to define an inner gap extending radially between the rotor and the inner stator and an outer gap extending radially between the rotor and the outer stator. A lubricant is disposed in both of the inner and outer gaps for supporting the rotor radially between the inner and outer stators. The lubricant supported motor with a two-sided radial flux configuration results in improved rotor-to-stator system stiffness to allow the lubricant supported electric motor to be used in high shock and high vibration environments, while also providing high torque in a small and lightweight design package.

An electric motor includes a cylindrical rotor with a plurality of wires parallel to the cylindrical axis nested between two cylinders of magnets in a stator. The cylinders of magnets may be a solid magnet, a plurality of bar magnets, a plurality of coils generating magnetic fields or other magnets or generated magnetic fields. A nested electric motor includes a first electric motor additionally including a first shaft, which first electric motor nests within the hollow center of a second larger electric motor additionally including a second shaft. The first shaft is coaxial with the second shaft.

An electric motor includes a cylindrical rotor with a plurality of wires parallel to the cylindrical axis nested between two cylinders of magnets in a stator. The cylinders of magnets may be a solid magnet, a plurality of bar magnets, a plurality of coils generating magnetic fields or other magnets or generated magnetic fields. A nested electric motor includes a first electric motor additionally including a first shaft, which first electric motor nests within the hollow center of a second larger electric motor additionally including a second shaft. The first shaft is coaxial with the second shaft.

A three-dimensional magnet structure (6) made up of a plurality of individual magnets (4), the magnet structure (6) having a thickness that forms its smallest dimension, the magnet structure (6) incorporating at least one mesh (5a) exhibiting mesh cells each one delimiting a housing (5) for a respective individual magnet (4), each housing (5) having internal dimensions just large enough to allow an individual magnet (4) to be inserted into it, the mesh cells being made from a fibre-reinforced insulating material, characterized in that a space is left between the housing (5) and the individual magnet (4), which space is filled with a fibre-reinforced resin, the magnet structure (6) comprising a non-conducting composite layer coating the individual magnets (4) and the mesh structure (5a).

A three-dimensional magnet structure (6) made up of a plurality of individual magnets (4), the magnet structure (6) having a thickness that forms its smallest dimension, the magnet structure (6) incorporating at least one mesh (5a) exhibiting mesh cells each one delimiting a housing (5) for a respective individual magnet (4), each housing (5) having internal dimensions just large enough to allow an individual magnet (4) to be inserted into it, the mesh cells being made from a fibre-reinforced insulating material, characterized in that a space is left between the housing (5) and the individual magnet (4), which space is filled with a fibre-reinforced resin, the magnet structure (6) comprising a non-conducting composite layer coating the individual magnets (4) and the mesh structure (5a).

An electromechanical actuator for electrical flight controls of an aircraft, the actuator comprising a transmission shaft, four electromechanical conversion members, each having a respective stator and rotor secured to the transmission shaft, and four control systems, each dedicated to respective ones of the electromechanical conversion members. The stator has teeth and windings surrounding at least one tooth, whereas the rotor is provided with permanent magnets. Each electromechanical conversion member is a flux-concentrating member and each winding is concentric and has a single layer. The electromechanical actuator is intended in particularly for controlling a hydraulic actuator via a mechanical transmission within an electrical flight control device of an aircraft.

An electromechanical actuator for electrical flight controls of an aircraft, the actuator comprising a transmission shaft, four electromechanical conversion members, each having a respective stator and rotor secured to the transmission shaft, and four control systems, each dedicated to respective ones of the electromechanical conversion members. The stator has teeth and windings surrounding at least one tooth, whereas the rotor is provided with permanent magnets. Each electromechanical conversion member is a flux-concentrating member and each winding is concentric and has a single layer. The electromechanical actuator is intended in particularly for controlling a hydraulic actuator via a mechanical transmission within an electrical flight control device of an aircraft.