Abstract: A piece of rotary equipment for a drone, the rotary equipment having a rotary assembly including at least one blade. The rotary assembly includes at least one furrow that extends in a skin from a first end to a second end, the at least one furrow being at least arranged over the blade, the at least one furrow presenting at least one change of direction on the blade, the rotary assembly including at least one deicer having an electrically conductive track that extends in the at least one furrow, the electrically conductive track extending from a first terminal to a second terminal, the first terminal being present at the first end and the second terminal being present at the second end, the deicer including a protective layer covering the electrically conductive track.

Abstract: An industrial activity drone comprising an aerial vehicle having at least one rotor, an activity system, and a fastener device for fastening the activity system to the aerial vehicle. The activity system includes a structure, a computer, a work camera that is stationary relative to the aerial vehicle and that provides a view of a work zone, a distribution device having a plurality of compartments, and a turning motor enabling the distribution device to turn relative to the aerial vehicle. The industrial activity drone performs hovering flight so that the work camera faces a work zone and the distribution device is turned so that the compartment that is to be used faces the work zone, thereby performing one or more tasks.

Abstract: A piece of rotary equipment for a drone, the rotary equipment having a rotary assembly including at least one blade. The rotary assembly includes at least one furrow that extends in a skin from a first end to a second end, the at least one furrow being at least arranged over the blade, the at least one furrow presenting at least one change of direction on the blade, the rotary assembly including at least one deicer having an electrically conductive track that extends in the at least one furrow, the electrically conductive track extending from a first terminal to a second terminal, the first terminal being present at the first end and the second terminal being present at the second end, the deicer including a protective layer covering the electrically conductive track.

Abstract: A piece of rotary equipment for a drone, the rotary equipment having a rotary assembly including at least one blade. The rotary assembly includes at least one furrow that extends in a skin from a first end to a second end, the at least one furrow being at least arranged over the blade, the at least one furrow presenting at least one change of direction on the blade, the rotary assembly including at least one deicer having an electrically conductive track that extends in the at least one furrow, the electrically conductive track extending from a first terminal to a second terminal, the first terminal being present at the first end and the second terminal being present at the second end, the deicer including a protective layer covering the electrically conductive track.

Abstract: An industrial activity drone comprising an aerial vehicle having at least one rotor, an activity system, and a fastener device for fastening the activity system to the aerial vehicle. The activity system includes a structure, a computer, a work camera that is stationary relative to the aerial vehicle and that provides a view of a work zone, a distribution device having a plurality of compartments, and a turning motor enabling the distribution device to turn relative to the aerial vehicle. The industrial activity drone performs hovering flight so that the work camera faces a work zone and the distribution device is turned so that the compartment that is to be used faces the work zone, thereby performing one or more tasks.

Abstract: A piece of rotary equipment for a drone, the rotary equipment having a rotary assembly including at least one blade. The rotary assembly includes at least one furrow that extends in a skin from a first end to a second end, the at least one furrow being at least arranged over the blade, the at least one furrow presenting at least one change of direction on the blade, the rotary assembly including at least one deicer having an electrically conductive track that extends in the at least one furrow, the electrically conductive track extending from a first terminal to a second terminal, the first terminal being present at the first end and the second terminal being present at the second end, the deicer including a protective layer covering the electrically conductive track.

Abstract: The present invention relates to a rotorcraft rotor (1) having a plurality of blades (3) movably mounted on a hub (2) via blade roots (4) that are respectively associated therewith. The rotor (1) is fitted with an information capture appliance having at least one measurement assembly (E1) comprising a flexible bar (11) interposed in engagement at its respective ends between the hub (2) and a blade root (4) that is allocated thereto. A strain gauge (7, 8) formed of a SAW transducer is implanted on the bar (11) and generates information relative to the bending of the bar (11) following tilting orientations of the blade root (4) in flapping (B) and/or in lag (T).

Abstract: A device (50) for feeding electricity to equipment (3) of a vehicle (1), the device including a harness (5), a socket (6) electrically connected to said harness (5), and a plug (9) electrically connected to said equipment (3) and co-operating with said socket (6) to provide the electrical connection between said harness (5) and said equipment (3). The device (50) provides for said harness (5) to run in the thickness of a floor (2) of the vehicle (1), said socket (6) being embedded in the thickness of said floor (2) so that the top surface of said floor (2) does not present any projecting portion. The device (50) includes a movable protection cap (7) for opening and closing said socket (6), together with opening means (40) driven by mounting said equipment (3) on said floor (2), thereby causing said movable protection cap (7) to open.

Abstract: An aircraft comprising a mechanical connection device including a body that extends along a longitudinal axis. The body comprises two opposite end portions disposed along the longitudinal axis and adapted to receive external axial loads in compression and in tension, a spring member that is adapted to be compressed axially, and a mechanism which, in the event of external axial loads in compression or in tension on the end portions, is able to transmit to the spring member compression forces oriented in opposite directions according to whether the external axial loads are in compression or in tension. This device forms a flexible connection that accommodates equally well external loads in compression and in tension.

Abstract: An aircraft comprising a mechanical connection device including a body that extends along a longitudinal axis. The body comprises two opposite end portions disposed along the longitudinal axis and adapted to receive external axial loads in compression and in tension, a spring member that is adapted to be compressed axially, and a mechanism which, in the event of external axial loads in compression or in tension on the end portions, is able to transmit to the spring member compression forces oriented in opposite directions according to whether the external axial loads are in compression or in tension. This device forms a flexible connection that accommodates equally well external loads in compression and in tension.

Abstract: A rotor (10) provided with a hub (11) and a plurality of blades (12), said rotor (10) including a mast (15) secured to said hub (11) and protection means (30) for providing protection against lightning. The protection means (30) comprise rotary electric current conduction means (32) constrained to rotate with said mast (15) and connected to each of the blades (12) via a respective first electrical connection member (31), said protection means (30) including non-rotary electric current conduction means (33) facing said rotary conduction means (32) while not being constrained to rotate with said mast (15), said protection means (30) including electrical connection trigger means (35), said non-rotary conduction means (33) being provided with a second electrical connection member (34) suitable for being electrically connected to a target member (38) external to said rotor (10).

Abstract: A communication device (20) for communication between a movable piece of equipment (101) of a rotary rotor (5) and a stationary piece of equipment (102). Said communication device (20) is fitted with a set (10) of controlling swashplates including a rotary swashplate (11) and a non-rotary swashplate (12), the communication device (20) comprising a movable transfer unit (21) and a stationary transfer unit (22) for exchanging information respectively with the movable equipment (101) and with the stationary equipment (102). Each transfer unit (21, 22) is connected to a respective transmit-and-receive antenna (31, 32), including a movable antenna (31) connected to the movable transfer unit (21) and fastened to the rotary swashplate (11) and a stationary antenna (32) connected to the stationary transfer unit (22) and fastened to the non-rotary swashplate (12), the movable antenna (31) and the stationary antenna (32) being suitable for communicating with each other wirelessly.

Abstract: A de-icing system for a fixed or rotary aircraft wing. The system is capable of generating ultrasound that is transmitted at least locally to an outside surface of the wing, wherein the system comprising a base structure (2) covered at least locally with at least one leading edge (3), an elastomer structure (1) arranged and secured between the base structure (2) and the leading edge (3), housings (4) defined in the elastomer structure (1) and open towards the leading edge (3), piezoelectric actuators arranged in at least some of the housings (4) in order to generate ultrasound, wiring (10) connecting the piezoelectric actuators to an electrical control and power supply unit, and a fastener for fastening the leading edge (3) onto the base structure (2) while coming into contact with the piezoelectric actuators (4a) arranged in their respective housings (4).

Abstract: An electrical power supply device (10) for electrically powering equipment on a rotary rotor (2) of an aircraft (1), which rotor is driven by a shaft (5), said device (10) comprising a removable stick (11). The stick (11) includes an upper alternator (20) and an upper tube (12) secured to said shaft (5) so as to be constrained in rotation therewith, said upper alternator (20) having a plurality of upper coils (21) fastened to an upper inside peripheral surface (12?) of said upper tube (12), said stick (11) having a rod (13) carrying an upper permanent magnet (22), said device (10) having a mechanism (30) so that said rod (13) and said upper tube (12) move with distinct rotary movements, said mechanism (30) having connection means (31) so as to be connectable to a reference member (8, 9) of an aircraft (1).

Abstract: The present invention relates to an electrical power supply and control device (10) for equipment (9) of a rotor (5), the device having a three-phase AC generator (20) in a stationary frame of reference. The device (10) comprises a rotary field transformer (30) having a stationary portion (31) connected to said generator (20) and a rotary portion (32) connected to a sequencer (50) that is arranged in a rotary frame of reference, said device (10) including control means (51) for controlling the sequencer (50) and located in said stationary frame of reference, the control means being connected to the sequencer (50) via contactless connection means (200), said sequencer (50) being suitable for electrically powering said equipment (9) on order of said control means (51).

Abstract: The present invention relates to a rotorcraft rotor (1) having a plurality of blades (3) movably mounted on a hub (2) via blade roots (4) that are respectively associated therewith. The rotor (1) is fitted with an information capture appliance having at least one measurement assembly (E1) comprising a flexible bar (11) interposed in engagement at its respective ends between the hub (2) and a blade root (4) that is allocated thereto. A strain gauge (7, 8) formed of a SAW transducer is implanted on the bar (11) and generates information relative to the bending of the bar (11) following tilting orientations of the blade root (4) in flapping (B) and/or in lag (T).

Abstract: An electrical power supply device (10) for electrically powering equipment on a rotary rotor (2) of an aircraft (1), which rotor is driven by a shaft (5), said device (10) comprising a removable stick (11). The stick (11) includes an upper alternator (20) and an upper tube (12) secured to said shaft (5) so as to be constrained in rotation therewith, said upper alternator (20) having a plurality of upper coils (21) fastened to an upper inside peripheral surface (12?) of said upper tube (12), said stick (11) having a rod (13) carrying an upper permanent magnet (22), said device (10) having a mechanism (30) so that said rod (13) and said upper tube (12) move with distinct rotary movements, said mechanism (30) having connection means (31) so as to be connectable to a reference member (8, 9) of an aircraft (1).

Abstract: A de-icing system for a fixed or rotary aircraft wing, the system including means for generating ultrasound that is transmitted at least locally to an outside surface of the wing, which means comprise a base structure (2) covered at least locally with at least one leading edge (3), wherein the system comprises: an elastomer structure (1) arranged and secured between the base structure (2) and the leading edge (3); housings (4) defined in the elastomer structure (1) and open towards the leading edge (3); piezoelectric actuators arranged in at least some of the housings (4) in order to generate ultrasound; wiring (10) connecting the piezoelectric actuators to an electrical control and power supply unit; and fastener means for fastening the leading edge (3) onto the base structure (2) while coming into contact with the piezoelectric actuators (4a) arranged in their respective housings (4).

Abstract: The present invention relates to an electrical power supply and control device (10) for equipment (9) of a rotor (5), the device having a three-phase AC generator (20) in a stationary frame of reference. The device (10) comprises a rotary field transformer (30) having a stationary portion (31) connected to said generator (20) and a rotary portion (32) connected to a sequencer (50) that is arranged in a rotary frame of reference, said device (10) including control means (51) for controlling the sequencer (50) and located in said stationary frame of reference, the control means being connected to the sequencer (50) via contactless connection means (200), said sequencer (50) being suitable for electrically powering said equipment (9) on order of said control means (51).

Abstract: A rotor (10) provided with a hub (11) and a plurality of blades (12), said rotor (10) including a mast (15) secured to said hub (11) and protection means (30) for providing protection against lightning. The protection means (30) comprise rotary electric current conduction means (32) constrained to rotate with said mast (15) and connected to each of the blades (12) via a respective first electrical connection member (31), said protection means (30) including non-rotary electric current conduction means (33) facing said rotary conduction means (32) while not being constrained to rotate with said mast (15), said protection means (30) including electrical connection trigger means (35), said non-rotary conduction means (33) being provided with a second electrical connection member (34) suitable for being electrically connected to a target member (38) external to said rotor (10).