RU2415778C2 - Aircraft retractable landing gear - Google Patents

Abstract

FIELD: transport.

SUBSTANCE: invention relates to aircraft engineering, particularly, to retractable landing gear. Proposed landing gear comprises shock absorbing leg 1 with crosspiece 2 secured thereon and articulated with landing gear IN/OUT tie rod 5. Said tie rod 4 is articulated with IN/OUT drive and aircraft fuselage. Shock absorbing leg turn mechanism is made up of two tie rods 8 and 9 located on one plate and rocker 10 pivoted on aforesaid tie rod 5. First tie rod 8 has its one end secured to fuselage and its other end secured to first arm of rocker 10. Second tie rod 9 has its one end secured to shock absorbing leg 1 and its other end secured to second arm of rocker 10. To be locked in OUT position, shock absorbing leg 1 and crosspiece 2 are provided with detachable fasteners 7 that allow rigid attachment of shock absorbing leg 1 and crosspiece 2 to aircraft engine nacelle 6.

EFFECT: higher reliability of landing gear operation.

3 cl, 5 dwg

Description

The invention relates to the field of aviation technology and relates to a retractable landing gear of the aircraft.

Various chassis designs are known in the art with exhaust-release by rotation about an axis parallel to the longitudinal axis of the fuselage (SU 205716, B64C 25/12, 1968; US 3899147, 1975; US 4047681, 1977; US 4063698, 1977; US 5478030, 1995 ; US 5875994, 1999).

The closest analogue of the invention is an airplane landing gear, comprising a shock absorber pivotally attached to the airplane body, a landing gear power drive hinged to the shock absorber strut and the airplane body, a wheeled cart mounted on a frame, a stabilizing shock absorber connecting the cart to the shock absorber, the suspension strut is equipped with a first lever rigidly attached to it, the trolley frame is connected to the suspension strut with the possibility of rotation around its axis and It is equipped with a second lever rigidly mounted on the frame, which is connected with the first lever by the power cylinder, and the beams rigidly mounted on the frame are made with hinges at the ends, each of which is equipped with a lever connected to the corresponding beam by the power cylinder (RU 2099245, B64C 25 / 12, 1997).

The above analogues, including the closest one, provide for cleaning the chassis into the niche of the fuselage or wing by rotating the suspension strut relative to its attachment to the fuselage or wing, which does not allow to vary the location of the chassis relative to the niche for cleaning it.

The objective of the invention is to provide a retractable landing gear in the fuselage, in which the distance between the struts exceeds the diameter of the fuselage.

The problem is solved due to the fact that the chassis contains a cushioning strut with a traverse fixed to it, pivotally connected to the landing gear of the landing gear, which, in turn, is pivotally connected to the drive of the harvesting exhaust and the fuselage, as well as a mechanism for turning the cushioning strut in this case, in the extended position of the landing gear, the strut and traverse are rigidly fixed by a detachable connection to the nacelle of the aircraft engine, and the mechanism of rotation of the strut is made in the form of ca a flight of two rods and a rocker pivotally mounted on a chassis cleaning-release link, with the first link of the mechanism pivotally attached at one end to the fuselage and the second at the first shoulder of the rocker, the second link pivotally attached at one end to the suspension strut and the other at the second Shoulder two shoulders rocking.

The technical result from the use of the claimed invention is to increase the reliability of the chassis by increasing the distance between the uprights, while the chassis in the retracted position of the chassis occupies a minimum amount in the fuselage. The specified result is achieved due to the fact that the suspension strut and the traverse in the released position are rigidly fixed to the engine nacelle, and in the retracted position, the landing gear is disconnected from the engine nacelle and is located in the niche of the aircraft fuselage. Due to the fact that the suspension strut in the process of cleaning the chassis is rotated by a traction system relative to the harvesting-exhaust traction by an angle of more than 90 °, it was possible to minimize the volume occupied by the chassis in the retracted position. This embodiment allows, despite the large length of the thrust harvesting release, fit the chassis into a small niche in the fuselage.

The invention is illustrated by drawings, which depict:

figure 1 - diagram of a retractable landing gear;

figure 2 is the same side view;

figure 3 is a section aa from figure 2;

figure 4 - section bb in figure 2;

figure 5 is a General view of the niche of the landing gear (landing gear removed).

The retractable landing gear of an airplane, mainly supersonic, contains an amortization strut 1, a traverse 2, a wheeled trolley 3 connected by a splined hinge 4 with a strut 1, a landing gear 5 for landing gear cleaning, a cleaning and exhaust drive 11 and a suspension strut reversal mechanism.

The landing gear thrust rod 5 is pivotally attached to the fuselage at one end and pivotally connected to the yoke bracket 2 with the other. In addition, the thrust rod 5 is pivotally connected to the tailgate drive through an arm mounted at a distance from the hinge of the thrust 5 to the fuselage.

In the released position of the landing gear, the suspension strut 1 and the traverse 2 are rigidly fixed by detachable joints 7 on the nacelle 6 of the aircraft engine. The detachable connection may be an ear-to-finger or loop-hook connection. For example, for the suspension strut, the fastening can be made in the form of two loops interacting with two hooks of the engine nacelle 6, and for the traverse 2 - in the form of one loop on the traverse and one hook on the engine nacelle 6.

The rotation mechanism of the depreciation strut is made in the form of two rods 8 and 9 and a rocker 10 lying in a plane located at an angle to the transverse plane of the plane, pivotally mounted on the bracket of the rod 5 for landing gear cleaning. The first link 8 of the mechanism is pivotally fixed at one end to the fuselage, and the second at the first shoulder of the rocking chair 10, the second link 9 is pivotally attached at one end to the suspension strut 1, and the other at the second shoulder of the two-arm rocking chair 10.

The right and left landing gear in the retracted position are one after the other, which is achieved by the location in oblique planes of the rotation mechanisms of the suspension struts, while the elements of the mechanism (traction and rocking) of the right and left struts 1 lie in parallel planes.

The operation of the device is as follows.

When cleaning the chassis, a command is issued to disconnect the detachable joints 7 connecting the suspension strut 1 and the traverse 2 with the engine nacelle. The chassis harvesting-release drive acts on the thrust 5, as a result of which it rotates relative to the hinge of its attachment to the fuselage together with the suspension strut 1 and the traverse 2, while the suspension strut is simultaneously deployed to the required angle relative to the rod 5 by the turning system traction system. The rocking chair 10 of the rotation mechanism of the suspension strut, mounted on the rod 5, transfers its movement to the rods 8 and 9. As a result, the total movement from the rod 5 of the landing gear harvesting and from the first rod 8 of the rotation mechanism, which rotates relative to the axis of its attachment to the fuselage, the U-turn of the strut is carried out by the second thrust 9 of the rotation mechanism of the suspension strut, to which the total movement of the rods 5 and 8 is transmitted through the rocker 10.

Chassis release is carried out in the reverse order.

Claims (3)

1. A retractable landing gear of the aircraft, comprising a suspension strut with a traverse fixed to it, pivotally connected to the landing gear-release pull rod, which is pivotally connected to the harvesting-release drive and the fuselage, characterized in that it is equipped with a swing strut swing mechanism made in the form located in one plane of the rocker, pivotally mounted on the chassis cleaning-release link, and two rods, with the first link of the mechanism pivotally fixed at one end on the fuselage and the second on the first shoulder of the rocking, second link it is pivotally fixed at one end to the suspension strut and the other to the second shoulder of the two-shouldered rocking chair, while for fixing in the released position, the suspension strut and crosshead are equipped with detachable fasteners that allow rigidly fastening the suspension strut and crossarm to the gondola of the aircraft engine. 2. The retractable landing gear according to claim 1, characterized in that the rotation mechanisms of the right and left suspension struts are located in parallel planes. 3. The retractable landing gear according to claim 1, characterized in that the detachable connection of the strut and traverse with the nacelle of the engine of the aircraft is made in the form of a connection "ear-finger" or "loop-hook", while for the strut mount can be made in in the form of two detachable connections, and for the traverse - in the form of one.

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