US 12,325,511 B2
Landing gear actuating device with double-star motor
Foly Selom Marius Attivi, Moissy-Cramayel (FR); François-Noel Leynaert, Moissy-Cramayel (FR); and Steve Coustenoble, Moissy-Cramayel (FR)
Assigned to SAFRAN LANDING SYSTEMS, Velizy Villacoublay (FR)
Appl. No. 18/025,564
Filed by SAFRAN LANDING SYSTEMS, Velizy-Villacoublay (FR)
PCT Filed Sep. 9, 2021, PCT No. PCT/EP2021/074863
§ 371(c)(1), (2) Date Mar. 9, 2023,
PCT Pub. No. WO2022/053583, PCT Pub. Date Mar. 17, 2022.
Claims priority of application No. 2009185 (FR), filed on Sep. 10, 2020.
Prior Publication US 2023/0331375 A1, Oct. 19, 2023
Int. Cl. B64C 25/26 (2006.01); B64C 25/24 (2006.01)
CPC B64C 25/26 (2013.01) [B64C 25/24 (2013.01)] 13 Claims
OG exemplary drawing
 
1. A device for actuating an aircraft undercarriage leg, the device comprising:
an electronic controller; and
an actuator comprising a three-phase electric motor connected to the electronic controller, wherein the device is arranged to authorize a gravity deployment of the aircraft undercarriage leg,
wherein the motor includes a stator having at least first and second star-coupled three-phase windings,
wherein the electronic controller comprises a first control channel connected to the first three-phase winding, and a second control channel connected to the second three-phase winding,
wherein each of the first and second control channels comprises a controller that generates a high-level control instruction, a driver that generates a low-level driver instruction from the high-level control instruction, and at least one braking circuit that brakes the motor during the gravity deployment of the aircraft undercarriage leg by using energy produced by the motor, and
wherein the device is arranged to use the first and second control channels as a function of the availabilities of the components of each control channel.