CH215809A - Retractable landing gear for aircraft. - Google Patents

Description

Removable landing gear for aircraft. Conventional retractable landing gears usually include a leg carrying the wheel and a broken brace ensuring the locking of the landing gear in the extended position. Lifting is obtained by a cylinder usually placed either between the broken strut and the aircraft, or on the broken strut. These devices have an unnecessarily strong lifting torque when the first compass is unfolded.

The present invention, due to Mr. Jean 1Vlercier, aims to remedy 6 this drawback, and relates to a retractable landing gear for aircraft of the type comprising a broken strut articulated at one of its ends at a fixed point of the aircraft and at the other end at a point of the strut, which carries the wheel located in the vicinity of its lower end, and a jack controlling the folding of the landing gear. This landing gear is characterized by the fact that the jack is articulated at one of its ends to a fixed point of the aircraft and ii, the other to two rods, one of which is articulated to the other. end at the leg, which carries the wheel at a point above the point of articulation of the end of the strut, and the other at a point of the strut, located between the point of articulation of the end of the strut, articulation of the two parts of the strut and the articulation point of the lower part of the strut to the leg.

The appended drawing represents, by way of example, one form of execution of the object of the invention.

The single figure represents a longitudinally retractable landing gear, established in accordance with the invention.

In this form of execution, the first train is retractable around a transverse axis 9. A broken brace 1, 1a is articulated to the leg 7 at a point 2 located in the vicinity of its lower extremity carrying the wheel, and in 3 on the airframe of the aircraft. A cylinder 4 is articulated at one of its ends, at 6, on the cell, and its end S carries two rods, articulated on this one and acting one on the leg 7 or 7 (c above the point of articulation of the strut 1, lcs and the other On the strut 1, the, at a point 5 located between the first point of articulation of the two parts of the strut and the first point of articulation of the Lower part of the strut to the leg.

The functioning of this escaniotable gear is as follows: At the start of the lifting, the 1st cylinder 4 initiates the breaking of the counterfiehe 1, 1a, and subsequently the 1st unlocking of the gear, by soll action in 5, then exerts soll effort principal On the train to see its retraction in the position indicated in dotted lines in the first drawing.

In the exit position of the train, the first jack 4 is substantially parallel to h, the leg 7 which carries the wheel.

Of course, the invention is in no way limited to the embodiment shown and described. Thus, the first maneuvering jack can be mechanical, hydraulic, pneumatic, electric, etc.

Claims (1)

CLAIM Retractable landing gear for aircraft, comprising a broken coritie, hinged at one of its ends to a fixed point of the aircraft and at the other to a point of the strut, which carries the wheel located at the ground rim at the lower end, and a rod controlling the folding of the train, characterized in that the jack is articulated at one of its ends at a fixed point of 1' plane and on the other two rods, one is hinged at the end of the leg, which carries the wheel at a point above the point of articulation of the end of the leg. strut, and the other at a point on the strut situated between the point of articulation of the two parts of the strut and the point of articulation of the lower part of the strut. on my leg. SUB-REV ENDKATION Landing gear according to claim, characterized in that in the extended position of the gear, the jack is substantially parallel to the leg which carries the wheel.