A rotor for an aircraft is described having: a support angularly fixed with respect to an axis and housing a power source; a unit rotatable about axis and housing an electrical load of the resistive type; and a power supply system for the electrical load and comprising: a first transformer electrically interposed between the power source and the load; the first transformer comprises: a first winding arranged on the support and a second winding arranged on the unit, a stator carried by the support, rotationally fixed with respect to axis and to which the first winding is fixed; and a rotor operatively connected to the unit and to which the second winding is fixed; the power supply system comprises a capacitive circuit electrically connected to the first transformer, so as to reduce the reactive power absorbed by the rotary transformer.

An anti-torque rotor is described for a helicopter, comprising: a mast rotatable about a first axis; a plurality of blades hinged on the mast, extending along respective second axes transversal to said first axis and rotatable about respective said second axes to alter the respective angles of attack; a control element sliding and rotating with respect to the mast, and operatively connected to said blades to cause the rotation of said blades about respective second axes following a translation of said element along the first axis; a control rod sliding axially along first axis with respect to the mast and angularly fixed with respect to the first axis; and a bearing interposed between the control rod and the control element, sliding along the first axis with respect to the mast and integrally with the control rod; the anti-torque rotor further comprises an interface made of an antifriction material interposed between said control rod and said bearing.

A transmission structure of a helicopter according to one aspect is a transmission structure that transmits power from a prime mover to a rotary wing in the helicopter. The transmission structure includes: a housing; an input shaft that transmits the power of the prime mover to a gear arranged in the housing; a bearing supporting the input shaft in the housing such that the input shaft is rotatable, the bearing including an annular inner ring that holds the input shaft, an annular outer ring that is arranged outside the inner ring in a radial direction and fixed to the housing, and rolling elements sandwiched between the inner ring and the outer ring; and a sleeve that is sandwiched between an inner peripheral surface of the inner ring and the input shaft and is lower in heat conductivity than the inner ring and the input shaft.

Rolling bearing with three contact points, wherein the inner raceway, the third contact point being located in a sector of the outer raceway delimited by a proximal end of the outer raceway on the one hand, and by the rolling plane on the other hand, characterized in that the outer ring comprises a drain provided in the outer raceway, and opening from an outer surface of the outer ring, said drain opening eccentrically on the outer raceway with respect to the rolling plane, in a sector of the outer raceway delimited by the rolling plane on the one hand, and a distal end of the outer raceway on the other hand, the drain and the third contact point being disjoint.

Example torque tube assemblies for use with aircraft high lift devices are described herein. An example apparatus includes a spline coupling having a first yoke, a sliding splined shaft having a second yoke and a torque tube having a first end and a second end opposite the first end. A first fitting with a third yoke is coupled to the first end of the torque tube, and a second fitting with a fourth yoke is coupled to the second end of the torque tube. The third yoke is coupled to the first yoke to form a first U-joint, and the fourth yoke is coupled to the second yoke to form a second U-joint. The spline coupling is to be coupled to a first high lift device drive shaft and the sliding splined shaft is to be coupled to a second high lift device drive shaft.

An aircraft seat module includes an enclosure unit which delimits a flight passenger seating region at least partially, and includes a door unit which at least closes a passage region to the flight passenger seating region in one or more operation states. The aircraft seat module further includes a bearing device which supports the door unit movably relative to the enclosure unit and has for this purpose a bearing module having a first bearing element and a second bearing element which are supported such that they are movable relative to each other.

A shackle for fastening an aircraft engine including a ball joint with a pin including a ring including a first bore and a sleeve assembled in the first bore and having a second bore configured to receive the pin and the diameter of which progressively increases to have a flared inner surface at each of its ends, the fastening shackle being arranged such that a spherical outer surface of the ring bears an anti-friction coating produced on a region extending beyond the contact region with the body of the shackle, this first region being bordered by rims forming a projection around the coating, and/or the second bore bears an anti-friction coating on a region extending beyond its contact region with the pin, this region being bordered by rims forming a projection around this anti-friction coating, at the ends of the flared inner surface.

A transmission shaft is provided comprising an input side for inputting torque, an output side for outputting torque, and a rod extending in a longitudinal direction between the input side and the output side to transfer torque along the transmission shaft. The rod comprises a first end provided at the input side, a second end provided at the output side and a torsional compliant section extending therebetween providing the transmission shaft with a torsional stiffness. The torsional compliant section comprises a cross-section which extends in the longitudinal direction to define a central core for transmitting torque directly from the first end to the second end and a radially outer section. This section also comprises a plurality ribs which extend radially and longitudinally from an outer periphery of the central core for increasing transverse stiffness of the rod.

A journal bearing for centering a misaligned pin is disclosed. The journal bearing includes an outer bushing defining an outer bore. The outer bore is offset with respect to an axis of rotation of the journal bearing by a misalignment distance. The misalignment distance represents a distance between the axis of rotation of the journal bearing and a center axis of the misaligned pin. The journal bearing further includes an inner bushing defining an inner bore. The inner bore is offset with respect to the axis of rotation of the journal bearing by the misalignment distance. The inner bushing is seated within the outer bore of the outer bushing. The inner bushing and the outer bushing are both configured to rotate relative to one another to center an inner periphery of the inner bushing around the misaligned pin.

To prove a motor capable of suppressing labor and costs even when the motor may be subjected to a large impact be used for a floating mobile body such as a drone. The motor (1) includes a shaft (41), a cartridge (4) including a plurality of bearings (42) that support the shaft (41), and a sleeve (43) that surrounds the bearings (42), and a housing (5) including a bottom portion (51) for receiving an impact from outside and an attaching portion (54) provided in the bottom portion (51). The bottom portion (51) of the housing (5) extends in a direction intersecting with respect to a longitudinal direction of the shaft (41), and the cartridge (4) is removably attached to the attaching portion (54).