RU2545239C1 - Aircraft retractable landing gear leg - Google Patents

Abstract

FIELD: aircraft engineering.

SUBSTANCE: this leg comprises lever with wheel articulated with fuselage, extending shock absorber, leg retract-release cylinder, retracted-released position locks, link with one end coupled with gimbal articulated with fuselage and another end with shock absorber. Shock absorber rod is articulated with lever. Said retracted-released position locks are made integral and composed of interarticulated flexible link with retainer and pawl with roller arranged to swing from lock open cylinder arranged inside said link. Pawl roller is arranged to contact with release-retracted position grooves made in shock absorber lug.

EFFECT: simple design and reduced weight.

2 cl, 5 dwg

Description

The invention relates to aircraft, and more particularly to takeoff and landing devices of aircraft (hereinafter - LA).

A retractable landing gear support of the aircraft is known from the prior art, comprising a lever with a wheel pivotally mounted on the fuselage, a release and release hydraulic cylinder with collet locks of the released and retracted positions, the cavities of which are connected to the aircraft hydraulic system by means of hydraulic locks, and a remote gas-hydraulic shock absorber, the body of which is connected to leverage. In the body of the shock absorber, one end of the rod is movably mounted, the other in the body of the shock absorber (see RF patent No. 2183179, IPC B64C 25/10, B64C 25/58, publ. 10.06.2002).

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 this 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. Moreover, during the operation of the shock absorber, the lock of the released position is a loaded element and is involved in the transfer of loads to the aircraft, which significantly reduces the reliability of the circuit. 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 the other (see RF patent No. 2297366, IPC B64C 25/10, publ. 20.04.2007). Each support contains 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 support hydraulic cylinder, a link pivotally connected at one end to a cardan mounted pivotally on the fuselage, and the other to a shock absorber. Moreover, the known design involves the presence of individual locks that hold the retractable landing gear in the released and retracted position, which leads to an increase in the weight of the support.

This technical solution was adopted as a prototype for the claimed invention.

The technical problem underlying the present invention is to create a simple design retractable landing gear by eliminating some links and elements, allowing you to use it in the conditions of small available dimensions.

The technical result achieved by the implementation of the present invention is to simplify the design of the retractable landing gear and reduce its weight.

The task underlying the present invention is solved by the fact that in the retractable landing gear of the aircraft, comprising a lever with a wheel pivotally mounted on the fuselage, a remote shock absorber, the rod of which is pivotally connected to the lever, a support-release cylinder, locks of the released and retracted positions , a link, pivotally connected at one end to a cardan mounted pivotally on the fuselage, and at the other, to a shock absorber, that the locks of the released and retracted positions are made as a single unit in the form of kinematically connected between elastic traction with a clamp and a dog with a roller mounted with the possibility of rocking motion from the cylinder to open the lock located inside the link, while the roller of the dog is installed with the possibility of contact with the grooves of the released and retracted positions made in the shock absorber eye.

In addition, stops are placed on the shock absorber casing, limiting the deviation of the link relative to its longitudinal and transverse axes.

The execution of the locks of the released and retracted positions as a whole in the form of kinematically interconnected elastic traction with a lock and a dog with a roller mounted with the possibility of rocking motion from the lock opening cylinder located inside the link allows to simplify the design of the retractable landing gear of the aircraft and reduce its weight . Installation of the dog’s roller with the possibility of contact with the grooves of the released and retracted positions made in the shock absorber eye ensures that the support is held in the released and retracted position.

These signs are significant and interconnected with the formation of a stable set of essential features sufficient to obtain the specified technical result.

A comparative analysis of the proposed technical solution with identified analogues of the prior art, from which the invention does not explicitly follow for a specialist in the field of aircraft landing devices, showed that it is unknown, and given the possibility of industrial serial production of a retractable landing gear of the aircraft chassis, we can conclude about it eligibility criteria.

The present invention is illustrated by a specific example of the proposed retractable landing gear of the aircraft, which clearly demonstrates the possibility of obtaining the specified technical result. Various modifications and improvements are permitted without departing from the scope of the invention as defined by the appended claims.

The proposed retractable landing gear aircraft is described further on the basis of the drawings, where:

- figure 1 presents a diagram of a retractable landing gear aircraft;

- figure 2 shows the initial position of the elements of the lock retracted position when opened;

- figure 3 shows the opening of the lock released position;

- figure 4 shows the position of the elements of the castle in the state of cleaning support;

- figure 5 shows the elements of the lock in the closing state of the lock of the retracted position.

In graphic materials, the corresponding structural elements of the retractable landing gear of the aircraft chassis are indicated by the following positions:

1- wheel;

2 - lever;

3 - shock absorber;

4 - link;

5 - cardan;

6 - cylinder cleaning-release support;

7 - an eye of the shock absorber body;

8 - lock;

9 - emphasis;

10 - cylinder for opening the lock;

11 - rod cylinder lock opening;

12 - a clamp;

13 - latch latch;

14 - spring;

15 - elastic traction;

16 - dog;

17 - groove issued position;

18 - spring cylinder lock opening;

19 - dog roller;

20 - groove of the retracted position.

The retractable landing gear of the aircraft chassis comprises a lever 2 with a wheel 1 pivotally mounted on the fuselage, an external shock absorber 3, the rod of which is pivotally connected to the lever 2, a cylinder 6 for cleaning and releasing the support, locks of the released and retracted positions, made in the form of a single lock structure 8, a link 4, pivotally connected at one end to a cardan 5 mounted pivotally on the fuselage, and at the other end to a shock absorber 3.

The lock 8 includes kinematically interconnected elastic rod 15 with a latch 12 and a dog 16 with a roller 19, mounted with the possibility of swinging motion from the cylinder 10 to open the castle located inside the link 4. In this case, the roller 19 of the dog 16 is installed with the possibility of contact with the grooves 17 and 20 released and retracted positions made in the eye 7 of the shock absorber body. On the body of the shock absorber 3 placed stops 9, limiting the deviation of the link 4 relative to its longitudinal and transverse axes.

The shock absorber 3 is connected by an eye of the rod to the eye of the lever 2, the eye of the housing 7 is connected to the link 4. In the connection node of the eye 7 and link 4 there is a lock 8, which ensures the kinematic immutability of the shock absorber-link chain during the operation of the shock absorber and allows the latter to absorb loads. When cleaning the landing gear, the lock is unlocked and under the influence of the force from the support cleaning cylinder 6, the shock absorber 3 rotates relative to link 4 and the wheel 1 moves (Fig. 1).

Retractable landing gear LA works as follows.

When the support is in the "Opening the lock of the retracted position" mode, to open the lock in the retracted position of the support, fluid pressure is supplied to the cylinder 10 of the opening of the lock, the rod 11 of which will begin to extend until the stop pad touches the latch 12. In the closed lock state, the petals 13 of the latch 12 are not give turn around the dog 16 and thereby securing the lock. When exposed to the clamp 12, the force from the rod of the cylinder 11, it begins to rotate, while compressing the elastic rod 15 (figure 2). Compression of the elastic rod 15 occurs until the dog 16 is unlocked by the petals 13 of the latch 12, after which the dog roller 12 comes out of the groove 17 of the released position (figure 2).

When the support is in the “Cleaning the support” mode, after the lock is fully opened in the retracted position, fluid pressure is supplied to the support-release cylinder 6 of the support to the outlet, whereby the shock absorber 3 and link 4 begin to rotate relative to each other. In the position of the lock 8, when the dog 16 has left the zone of the groove 17 of the released position on the eye 7 of the shock absorber, the cavity of the cylinder 10 of the lock 8 is connected to the drain. Due to the spring 18 of the lock opening cylinder, the rod 11 of the lock opening cylinder 10 is removed (FIG. 3), with further cleaning of the support, the dog 16 slides along the shock absorber eye.

In the process of operation of the support in the "Closing the lock of the retracted position" mode, when the roller 19 of the dog 16 coincides with the groove of the retracted position 20 under the action of the spring 14, the dog 16 is rotated and the lock is closed. In this case, the angular movement of the dog will occur with a compressed elastic traction 15 (figure 5). As soon as the roller 19 of the dog 16 completely enters the groove 20 under the action of the compressed elastic traction 15, the latch 12 begins to rotate and the lock of the retracted position locks. Lock locked position closed.

A sample of the proposed retractable landing gear of the aircraft was developed on the basis of detailed experimental studies of the design parameters and the process of its operation.

The manufacture of the proposed retractable landing gear for the aircraft does not require the development of new equipment and the re-equipment of existing facilities, and the tools used are widely used in the aviation industry, which confirms the possibility of practical implementation and achievement of the technical result.

Claims (2)

1. A retractable landing gear support of the aircraft, comprising a lever with a wheel pivotally mounted on the fuselage, a remote shock absorber, the rod of which is pivotally connected to the lever, a cylinder for cleaning and releasing the support, locks of the released and retracted positions, a link, pivotally connected with a cardan installed at one end articulated on the fuselage, and the other with a shock absorber, characterized in that the locks of the released and retracted positions are made as a single unit in the form of kinematically interconnected elastic traction with a retainer and a dog with a roller, mounted with the possibility of swinging motion from the cylinder to open the lock located inside the link, while the roller of the dog is installed with the possibility of contact with the grooves of the released and retracted positions made in the eye of the shock absorber. 2. The support according to claim 1, characterized in that the stops are placed on the shock absorber body, limiting the deviation of the link relative to its longitudinal and transverse axes.

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