# US 11,305,892 B2 · Unit for handling an aircraft turbojet engine > Agents: this data is available as JSON from the patentgrep API and MCP server — see https://patentgrep.com/llms.txt - Number: US 11,305,892 B2 - Document ID: US11305892B2 - Status: Granted - Kind: B2 - Application number: 16/730,434 - Filed: 2019-12-30 - Published: 2020-09-17 - Granted: 2022-04-19 - Earliest claimed: 2017-06-29 - Assignees: Safran Nacelles - Applicants: Safran Nacelles - Inventors: Patrice Chantal; Thierry Drieu - Web page: https://patentgrep.com/patent/US11305892B2 ## CPC - B64F 5/50: Handling or transporting aircraft components - B66F 5/025: {screw-actuated} - F01D 25/285: {Temporary support structures, e.g. for testing, assembling, installing, repairing; Assembly methods using such structures} - B64F: GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR - B66F: HOISTING, LIFTING, HAULING OR PUSHING, NOT OTHERWISE PROVIDED FOR, e.g. DEVICES WHICH APPLY A LIFTING OR PUSHING FORCE DIRECTLY TO THE SURFACE OF A LOAD ({invalid lifting devices A61G7/10; } mounting artificial islands on piles or like supports E02B17/00; scaffolding combined with lifting devices E04G1/22; lifting devices for sliding forms E04G11/24; lifting of buildings E04G23/06; shores or struts E04G25/00; lifts or other hoisting devices on ladders E06C7/12; props for mining E21D15/00) - F01D: NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES (machines or engines for liquids F03; non-positive displacement pumps F04D) ## Abstract A unit for handling an aircraft turbojet engine includes a frame, a front cradle and a rear cradle designed for supporting the turbojet engine, and a plurality of electric actuators. The cradles include devices for securing the turbojet engine. The plurality of electric actuators includes three electric actuators, where a first one and second one are arranged opposite each other, on either side of a longitudinal axis of the frame, connected to the front cradle and arranged for moving same in vertical translation, and where a third actuator is connected to the rear cradle and arranged for moving the same in vertical translation. The handling unit further includes a device for rotary driving of the front cradle about a longitudinal axis of the turbojet engine. ## Claims ### Claim 1 A handling unit for an aircraft turbojet engine comprising: a chassis; a front cradle positioned forward of the handling unit and a rear cradle positioned rearward of the handling unit, adapted to support the aircraft turbojet engine to be maintained, each of the cradles including two fastening devices for fastening the aircraft turbojet engine; a plurality of electric actuators, wherein the plurality of electric actuators includes: two electric actuators disposed on either side of a longitudinal axis of the chassis, wherein one of the two electric actuators is connected to the front cradle and arranged to displace the front cradle in vertical translation, and the other of the two actuators is connected to the rear cradle and arranged to displace the rear cradle in vertical translation, or three electric actuators including a first actuator and a second actuator facing one another, on either side of a longitudinal axis of the chassis, connected to the front cradle and arranged to displace the front cradle in vertical translation, and including a third actuator connected to the rear cradle and arranged to displace the rear cradle in vertical translation; and wherein the handling unit further comprises a rotational driving device for driving in rotation the front cradle only about a longitudinal axis of the handling unit. ### Claim 2 (depends on 1) The handling unit according to claim 1, wherein each of the front cradle and the rear cradle includes: a fastening arm for fastening the aircraft turbojet engine, elongated in a transverse direction of the chassis, substantially semicircular, supporting the aircraft turbojet engine fastening devices; and a connecting arm adapted to connect the fastening arm to the electric actuators, and wherein the rotational driving device includes: a notched wheel extending along the fastening arm of the front cradle; a pinion, engaged with the notched wheel and supported by the connecting arm; and an actuator for driving the pinion in rotation. ### Claim 3 (depends on 1) The handling unit according to claim 1, wherein the plurality of electric actuators comprise a screw-nut system adapted to drive the front cradle and the rear cradle in vertical translation. ### Claim 4 (depends on 3) The handling unit according to claim 3, wherein the screw-nut system includes: a screw mounted on the chassis; a nut engaged with the screw and secured to a connecting arm of the front cradle or the rear cradle; and an actuator for driving the screw in rotation. ### Claim 5 (depends on 1) The handling unit according to claim 1, wherein the chassis is equipped with wheels and air cushions configured to allow the displacement of the chassis. ### Claim 6 (depends on 5) The handling unit according to claim 5, wherein the chassis includes at least one stabilization device. ### Claim 7 (depends on 6) The handling unit according to claim 6, wherein the at least one stabilization device includes: a stand made of elastomer material; and an actuator for actuating the stand between a retracted position authorizing displacement of the handling unit relative to a ground and a deployed position in which the stand abuts the ground. ### Claim 8 (depends on 7) The handling unit according to claim 7, wherein the at least one stabilization device further includes an adjustment device adapted to allow displacements in translation of the chassis on the ground in at least two directions of displacement. ### Claim 9 (depends on 8) The handling unit according to claim 8, wherein the adjustment device includes a set of balls arranged in the stand. ### Claim 10 (depends on 1) The handling unit according to claim 1, wherein the plurality of actuators include no more than three actuators for displacing the front cradle and the rear cradle in vertical translation. ### Claim 11 (depends on 10) The handling unit of claim 10, wherein the plurality of electric actuators include only two electric actuators. ### Claim 12 (depends on 10) The handling unit of claim 10, wherein the plurality of electric actuators include only three electric actuators. ### Claim 13 (depends on 12) The handling unit of claim 12, wherein in a case where the plurality of electric actuators include three electric actuators, the first actuator and the second actuator are arranged to displace only the front cradle only in the vertical translation, and the third actuator is arranged to displace only the rear cradle only in the vertical translation. ### Claim 14 (depends on 1) The handling unit of claim 1, wherein only the rear cradle or only the front cradle is equipped with the rotational driving device. ### Claim 15 (depends on 1) The handling unit of claim 1, wherein: in a case where the plurality of electric actuators include two electric actuators, the one of the two electric actuators is arranged to displace the front cradle only in the vertical translation, and the other of the two actuators is arranged to displace the rear cradle only in the vertical translation, and in a case where the plurality of electric actuators include three electric actuators, the first actuator and the second actuator are arranged to displace the front cradle only in the vertical translation, and the third actuator is arranged to displace the rear cradle only in the vertical translation. ### Claim 16 (depends on 1) The handling unit of claim 1, wherein: in a case where the plurality of electric actuators include two electric actuators, the other of the two actuators is the only actuator of the plurality of electric actuators connected to the rear cradle; and in a case where the plurality of electric actuators include three electric actuators, the third actuator is the only electric actuator of the plurality of electric actuators connected to the rear cradle. ### Claim 17 (depends on 1) The handling unit of claim 1, wherein the rotational driving device is a separate device from the plurality of electric actuators and controls rotation of the front cradle independently of the plurality of electric actuators. ### Claim 18 A handling unit for an aircraft turbojet engine, comprising: a chassis; a front cradle positioned forward of said handling unit and a rear cradle positioned rearward of said handling unit, adapted to support the aircraft turbojet engine to be maintained, each of the cradles including two fastening devices for fastening the aircraft turbojet engine; a plurality of electric actuators, wherein the plurality of electric actuators includes: two electric actuators, disposed on either side of a longitudinal axis of the chassis, wherein one of the two actuators is connected to the front cradle and arranged to displace the front cradle in vertical translation, and the other of said two actuators is connected to the rear cradle and arranged to displace said rear cradle in vertical translation, or three electric actuators including a first actuator and a second actuator facing one another, on either side of a longitudinal axis of the chassis, connected to the front cradle and arranged to displace the front cradle in vertical translation, and including a third actuator connected to the rear cradle and arranged to displace the rear cradle in vertical translation; and a rotational driving device for driving in rotation the front cradle about a longitudinal axis of the handling unit; wherein the chassis is equipped with wheels and air cushions configured to allow the displacement of the chassis; wherein the chassis includes at least one stabilization device; wherein the stabilization device includes: a stand made of elastomer material, and an actuator for actuating said stand, between a retracted position authorizing displacement of the handling unit relative to a ground, and a deployed position in which said stand abuts against the ground; wherein the at least one stabilization device further includes an adjustment device adapted to allow displacements in translation of the chassis on the ground in at least two directions of displacement; wherein the adjustment device includes a set of balls arranged in the stand. ### Claim 19 A handling unit for an aircraft turbojet engine comprising: a chassis; a front cradle positioned forward of the handling unit and a rear cradle positioned rearward of the handling unit, adapted to support the aircraft turbojet engine to be maintained, each of the cradles including two fastening devices for fastening the aircraft turbojet engine; a plurality of electric actuators, wherein the plurality of electric actuators include: two electric actuators disposed on either side of a longitudinal axis of the chassis, wherein one of the two electric actuators is connected to the front cradle and arranged to displace only the front cradle only in vertical translation, and the other of the two actuators is connected to the rear cradle and arranged to displace only the rear cradle only in vertical translation, or three electric actuators including a first actuator and a second actuator facing one another, on either side of a longitudinal axis of the chassis, connected to the front cradle and arranged to displace the front cradle in vertical translation, and including a third actuator connected to the rear cradle and arranged to displace the rear cradle in vertical translation; and wherein the handling unit further comprises a rotational driving device for driving in rotation the front cradle about a longitudinal axis of the handling unit.