RU2297366C1 - Aircraft landing gear main leg - Google Patents

Abstract

FIELD: alighting gears for flying vehicles.

SUBSTANCE: aircraft landing gear leg has lever 1 with wheel 2 articulated on fuselage, gas-and-hydraulic shock absorber 4 whose rod 5 is articulated with lever, down lock 9, up lock 11 mounted on fuselage, down lock shackle 10, up lock shackle 12 articulated on lever, leg retraction-extension hydraulic cylinder 13. In center part, shock absorber body is articulated to member 7 made in form of fork whose other end is articulated via ears to cardan 8 which is articulated on fuselage; down lock is mounted on the same member ; down lock shackle is articulated on upper part of shock absorber body.

EFFECT: reduced dimensions of leg, avoidance of bending load on member; reduced load on down lock; reduced mass of leg.

3 dwg

Description

The invention relates to aircraft, in particular to landing devices of aircraft and, in particular, to the main retractable landing gear support.

The main retractable landing gear support of the aircraft is known, which contains a lever with a wheel pivotally mounted on the fuselage, a remote gas-hydraulic unit, including a gas-hydraulic shock absorber, a support hydraulic-release cylinder, collet locks of the removed and released support position, pivotally connected to the lever and fuselage (See RU patent 2183179, CL B64C 25/10, 25/58).

The combination in the known construction of a gas-hydraulic shock absorber, a support harvesting-release hydraulic cylinder, a retracted and released support position collet locks leads to an increase in the length of the unit as a whole, since the support harvesting-release hydraulic cylinder in such an aggregate is much longer than the shock absorber stroke, which determines the length of a conventional shock absorber, except Moreover, in such a design, visual control of the operation and condition of the collet locks of the retracted and released position of the support is impossible, which reduces the reliability of the locks, it is impossible to connect the limit switch drives with the locking elements of the locks, the signals of which are used to signal the closed and open position of the locks, as well as for the operation of other chassis systems. The combination in the unit of the functions of the shock absorber, the cleaning-release hydraulic cylinder, the locks of the retracted and released position reduces the reliability of the unit as a whole, worsens its operational manufacturability, since failures in the shock absorber, hydraulic cylinder, locks of the removed and released position of the support lead to decommissioning expensive unit in general.

Also known multi-support chassis, consisting of several independent supports located one after another. Each support contains a lever with a wheel pivotally mounted on a beam mounted motionlessly on the fuselage, a remote gas-hydraulic shock absorber, the body of which ends with an eye, pivotally attached to the lever, and the rod is pivotally connected to the lower link eye, which is pivotally connected to the beam by the other eye, the cleaning cylinder - the release of the support pivotally connected to the beam and the details of the support release-release mechanism, the locking mechanism of the released position of the support (See patent FR 2702446, CL B64C 25/34, 25/22), while the decomposition unit supports a locking mechanism is held in a fixed position. During operation of the shock absorber, the link also remains stationary.

The reasons that impede the achievement of the technical result indicated below include the fact that attaching the shock absorber to the link increases the dimensions and weight of the support, in addition, during operation of the shock absorber, the link remains stationary, and the shock absorber rotates relative to the link (the longitudinal axes of the shock absorber and the link form an angle), and the link is loaded with a bending moment, which is also transmitted to the locking mechanism that holds the link in a fixed position, which leads to an increase in the dimensions and weight of the support.

The objective of the invention is to remedy these disadvantages, namely reducing the dimensions of the support, eliminating the loading of the link by a bending load, improving the working conditions of the locking mechanism of the released position of the support, reducing the weight of the support.

The task is achieved in that in the main landing gear of the aircraft, containing a lever with a wheel pivotally mounted on the fuselage, a remote gas-hydraulic shock absorber, the rod of which is pivotally connected to the lever, a lock of the released position, a lock of the retracted position mounted on the fuselage, an earring of the lock of the retracted position pivotally mounted on a lever, a support cylinder for harvesting and releasing, according to the invention, the shock absorber body in the middle part is pivotally attached to a link made in the form of a fork, the other end pivotally through the eyes with a cardan pivotally mounted on the fuselage, while the released position lock is placed on the same link, and the released position lock earring is pivotally mounted on the upper part of the shock absorber, and in the released position of the support, the shock absorber is rigidly fixed relative to the released position lock relative to the link so that the longitudinal axis of the link and the shock absorber coincide, and when cleaning the support, the shock absorber in the hinge of the suspension to the link rotates relative to the link.

The invention is illustrated by drawings, where

figure 1 - General view of the main landing gear;

figure 2 - Front view of figure 1;

figure 3 - General view of a multi-support chassis.

The support comprises a lever 1 with a wheel 2 pivotally mounted on the fuselage 3, a remote gas-hydraulic shock absorber 4, the rod 5 of which is pivotally connected to the lever 1, and the body through pins 6 located in the middle of the body is pivotally connected to the link 7 made in the form of a fork. articulated at the other end with a cardan 8 mounted pivotally on the fuselage, the released position lock 9, mounted on link 7, the released position lock earring 10, pivotally connected to the upper part of the shock absorber housing, the retracted position lock 11, anovlenny on the fuselage, the shackle lock of the retracted position 12, pivotally mounted on the arm 1, cylinder cleaning-release support 13 pivotally connected to the fuselage and the link.

The multi-support chassis consists of several supports proposed by the applicant.

The support works as follows. In the released position, the shock absorber 4 is fixed motionless relative to the link 7 using the lock of the released position 9, located on the link, and the lock earrings of the released position 10, pivotally mounted on the upper part of the shock absorber body. During the movement of the aircraft along the aerodrome, when the lever 1 is rotated, the shock absorber rod 4 moves, and the shock absorber 4 together with link 7 rotates relative to the axis of the hinge for attaching the cardan 8 to the fuselage. The longitudinal axis of the shock absorber 4 and link 7 with the released position of the support are always, including when the shock absorber is in operation, are on the same line (coincide). Due to this, the lock of the released position 9 is subject to a minimum load.

During the cleaning of the support, the lock of the released position 9 is opened, the lock earring of the released position 10 is released, and after applying pressure to the hydraulic cylinder for cleaning and releasing the support 13, the link 7 is rotated, while dragging the shock absorber 4, the lever 1 with the wheel 2. In the retracted position, the support locked by the lock of the removed position 11. The release process is in the reverse order.

Thus, the proposed design of the main retractable landing gear support of the aircraft, in which the lever with the wheel is pivotally mounted on the fuselage, the remote gas-hydraulic shock absorber is pivotally connected to the lever by the rod, and the joint in the middle part of the shock absorber is connected to the link made in the form of a fork located in the released position along the shock absorber, the other end pivotally connected to the cardan mounted pivotally on the fuselage, the released position lock is mounted on the link, the floor release lock earring The hinge is mounted pivotally on the upper part of the shock absorber body, the lock of the retracted position is mounted on the fuselage, the earring of the lock of the retracted position is hinged on the lever, the support release and release cylinder is pivotally connected to the fuselage and link, it allows to reduce the dimensions of the support, to exclude loading of the link by a bending load, to reduce the load by locking the released position of the support and reduce the weight of the support.

Claims (1)

The main landing gear support of the aircraft, comprising a lever with a wheel pivotally mounted on the fuselage, a remote gas-hydraulic shock absorber whose rod is pivotally connected to the lever, an unlocked position lock, a retracted position lock mounted on the fuselage, an unlocked position lock earring, a retracted position lock earring, articulated mounted on a lever, a support-release hydraulic cylinder, characterized in that the shock absorber body in the middle part is pivotally attached to a link made in the form of a fork connected the other end pivotally through the eyes with a cardan pivotally mounted on the fuselage, while the released position lock is placed on the same link, and the released position lock earring is pivotally mounted on the upper part of the shock absorber body.

Images