Unit for handling an aircraft turbojet engine

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.

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.