Nose gear of an aircraft comprising a single control device for retraction and steering
View Patent ↗A landing gear of an aircraft, including a strut including two arms forming a rotational axis for retracting the gear, a rotating tube mounted in a mobile manner such that it rotates inside the strut about a pivoting axis, a sliding rod that is mobile in a translatory manner in the rotating tube along the pivoting axis, and carries wheels of the gear at one of its ends, and at least one bearing point that is located on one of the elements of the gear at a distance from the retraction axis and can bear necessary efforts for the retraction, the bearing point being located on the rotating tube.
1. An aircraft landing gear comprising:
a leg comprising two arms forming a pivot for retracting the landing gear;
a rotary tube mounted so that it can turn inside the leg about a pivot axis and extending beyond the retraction pivot with respect to a position of at least one wheel of the landing gear;
a sliding rod capable of translational movement inside the rotary tube along the pivot axis and bearing at one of its ends the at least one wheel of the landing gear; and
at least one means for rotating the leg about the retraction pivot through collaboration with the structure of the aircraft and with a fulcrum positioned on one of the elements of the landing gear distant from the retracting pivot,
wherein the fulcrum is positioned on the rotary tube, on the opposite side of the retraction pivot to the at least one wheel, and the fulcrum comprises two lateral extensions positioned one on each side of the pivot axis of the rotary tube and two actuators acting respectively on the lateral extensions, the landing gear being retracted or lowered by simultaneously elongating moving assemblies of the two actuators by a same amplitude and the landing gear being pivoted by elongating the moving assemblies in opposite directions but by the same amplitude.
2. The landing gear as claimed in claim 1 , wherein the fulcrum is positioned a distance from the pivot axis so as to allow the rotary tube to be rotated about its pivot axis by the means for rotating the leg.
3. The landing gear as claimed in claim 1 , wherein the lateral extensions form a tee fixed to the upper end of the rotary tube by fasteners.
4. The landing gear as claimed in claim 1 , wherein the actuators respectively comprise a first moving assembly defining a first elongation of the actuators and a second moving assembly defining a second elongation of the actuators, the two moving assemblies being positioned on the axis of one another and acting in series to define overall elongation of the actuators.
5. The landing gear as claimed in claim 4 , wherein the actuators are hydraulic actuating cylinders comprising a first and a second pressure chamber respectively actuating the first and second moving assemblies, the first moving assembly carrying the second pressure chamber.
6. The landing gear as claimed in claim 1 , wherein the landing gear further comprises a first device capable of blocking the rotation of the rotary tube about the pivot axis to allow the landing gear to be retracted and a second device capable of blocking the rotation of the leg about its retraction pivot to allow taxiing on the ground.
7. An aircraft comprising a landing gear as claimed in claim 1 .