The invention relates to an autonomous device (10) for storing and releasing energy in order to power a piece of electrical equipment (12), in particular a piece of electrical equipment (12) of an aircraft, characterised in that said device comprises: a first means (16), configured to transform a variation in the surrounding pressure (P) to which the device (10) is subject into mechanical energy, at least one second means (20, 22), configured to mechanically store said mechanical energy by transforming same into the form of mechanical potential energy, a third means (24), configured to control the release of the mechanical potential energy contained in said second means (20, 22) and transform same into restored mechanical energy, a fourth means (28), configured to transform the restored mechanical energy into electrical energy suitable for powering said piece of electrical equipment (12).

The invention relates to an autonomous device (10) for storing and releasing energy in order to power a piece of electrical equipment (12), in particular a piece of electrical equipment (12) of an aircraft, characterised in that said device comprises: a first means (16), configured to transform a variation in the surrounding pressure (P) to which the device (10) is subject into mechanical energy, at least one second means (20, 22), configured to mechanically store said mechanical energy by transforming same into the form of mechanical potential energy, a third means (24), configured to control the release of the mechanical potential energy contained in said second means (20, 22) and transform same into restored mechanical energy, a fourth means (28), configured to transform the restored mechanical energy into electrical energy suitable for powering said piece of electrical equipment (12).

A non-reverse ratchet assembly includes a stationary ring with a plurality of saw teeth equally distributed over an outer surface of the stationary ring; a rotating housing with a rotating ring surrounding the stationary ring; and a plurality of ratchet elements equally distributed and positioned between the rotating ring and the stationary ring, wherein each ratchet element is configured to engage with or disengage from the plurality of saw teeth, and wherein each ratchet element comprises a slot for a distributed load sharing of the plurality of ratchet elements when engaging with the plurality of saw teeth. Furthermore, a vertical shaft motor including a non-reverse ratchet assembly is described.

A non-reverse ratchet assembly includes a stationary ring with a plurality of saw teeth equally distributed over an outer surface of the stationary ring; a rotating housing with a rotating ring surrounding the stationary ring; and a plurality of ratchet elements equally distributed and positioned between the rotating ring and the stationary ring, wherein each ratchet element is configured to engage with or disengage from the plurality of saw teeth, and wherein each ratchet element comprises a slot for a distributed load sharing of the plurality of ratchet elements when engaging with the plurality of saw teeth. Furthermore, a vertical shaft motor including a non-reverse ratchet assembly is described.

Provided are an actuator and a vehicle transmission including the same. The actuator includes a magnet gear unit which transmits a driving force and a driving unit which drives the magnet gear unit. The magnet gear unit includes a first magnet, a second magnet disposed outside the first magnet to face the first magnet, and a pawl member inserted in parallel between the first magnet and the second magnet. The driving unit includes a circular rotor on a central axis, and any one of the first magnet, the second magnet or the pawl member is mounted to the rotor; a third magnet mounted along a circumference of the rotor; and a stator including an annular core having a plurality of protrusions that face the third magnet and coils connected to the protrusions.

Provided are an actuator and a vehicle transmission including the same. The actuator includes a magnet gear unit which transmits a driving force and a driving unit which drives the magnet gear unit. The magnet gear unit includes a first magnet, a second magnet disposed outside the first magnet to face the first magnet, and a pawl member inserted in parallel between the first magnet and the second magnet. The driving unit includes a circular rotor on a central axis, and any one of the first magnet, the second magnet or the pawl member is mounted to the rotor; a third magnet mounted along a circumference of the rotor; and a stator including an annular core having a plurality of protrusions that face the third magnet and coils connected to the protrusions.

A linear actuator (10) for use in a modular assembly of such actuators comprises an actuator body (11), a shaft (12) guided by the body to be displaceable relative thereto in the sense of the longitudinal axis (13) of the shaft and a drive motor enclosed in the body and operable to axially displace the shaft relative to the body in two mutually opposite directions. The body has two mutually opposite sides (15a, 15b) respectively lying in two substantial parallel spaced-apart planes, which each represent a reference plane for positioning the body side-by-side with the body of another such actuator, and a further side (17b) connecting the two mutually opposite sides and stepped to form a projection (18) receiving the shaft (12) with the axis (13) parallel to the two planes and a rebate (19) beside the projection to permit the body to interlock with the body of another such actuator at that further side. The projection (18) and rebate (19) are of substantially the same width in the sense of the spacing of the two planes and the shaft (12) is disposed substantially centrally of the projection (18) so that when the body (11) is interlocked with that of another such actuator the pitch of the shaft axes (13) is equal to that width.

A linear actuator (10) for use in a modular assembly of such actuators comprises an actuator body (11), a shaft (12) guided by the body to be displaceable relative thereto in the sense of the longitudinal axis (13) of the shaft and a drive motor enclosed in the body and operable to axially displace the shaft relative to the body in two mutually opposite directions. The body has two mutually opposite sides (15a, 15b) respectively lying in two substantial parallel spaced-apart planes, which each represent a reference plane for positioning the body side-by-side with the body of another such actuator, and a further side (17b) connecting the two mutually opposite sides and stepped to form a projection (18) receiving the shaft (12) with the axis (13) parallel to the two planes and a rebate (19) beside the projection to permit the body to interlock with the body of another such actuator at that further side. The projection (18) and rebate (19) are of substantially the same width in the sense of the spacing of the two planes and the shaft (12) is disposed substantially centrally of the projection (18) so that when the body (11) is interlocked with that of another such actuator the pitch of the shaft axes (13) is equal to that width.

The invention relates to an autonomous device (10) for storing and releasing energy in order to power a piece of electrical equipment (12), in particular a piece of electrical equipment (12) of an aircraft, characterised in that said device comprises: a first means (16), configured to transform a variation in the surrounding pressure (P) to which the device (10) is subject into mechanical energy, at least one second means (20, 22), configured to mechanically store said mechanical energy by transforming same into the form of mechanical potential energy, a third means (24), configured to control the release of the mechanical potential energy contained in said second means (20, 22) and transform same into restored mechanical energy, a fourth means (28), configured to transform the restored mechanical energy into electrical energy suitable for powering said piece of electrical equipment (12).

The invention relates to an autonomous device (10) for storing and releasing energy in order to power a piece of electrical equipment (12), in particular a piece of electrical equipment (12) of an aircraft, characterised in that said device comprises: a first means (16), configured to transform a variation in the surrounding pressure (P) to which the device (10) is subject into mechanical energy, at least one second means (20, 22), configured to mechanically store said mechanical energy by transforming same into the form of mechanical potential energy, a third means (24), configured to control the release of the mechanical potential energy contained in said second means (20, 22) and transform same into restored mechanical energy, a fourth means (28), configured to transform the restored mechanical energy into electrical energy suitable for powering said piece of electrical equipment (12).