RU2624949C1 - Aircraft plane gear leg bridge installation unit - Google Patents

Abstract

FIELD: aviation.

SUBSTANCE: aircraft plane gear leg bridge installation unit contains a bridge with operating pins installed in spherical bearings mounted in the seats fixed on the aircraft airframe carcase and also contains a unit for fixing the bridge in the axial direction. The unit is provided with an inner flipped side and is attached to the airframe carcase of one of the seats. In this case, the bridge is formed with an annular groove, and the inner flipped side of the unit for fixing the bridge in the axial direction is disposed in this groove. A radial clearance is provided between the surfaces of the flipped side and the bridge.

EFFECT: improvement of the structure reliability, ensured fixation of the bridge in the axial direction with the load only on one area of the airframe carcase and unobstructed turning of the bridge during the extension-retraction of landing gear.

6 cl, 3 dwg

Description

The invention relates to aircraft, specifically to the installation of a landing gear on an airframe.

State of the art

On modern heavy-duty aircraft, a landing gear is installed, the cleaning and release of the wheeled cart of which is carried out by turning the yoke of the landing gear (hereinafter - the yoke).

The trunnion trunnions are mounted in spherical (spherical) bearings (ball bearings), mounted in saddles fixed relative to the aircraft glider frame. For example: Mounting unit of the traverse of the aircraft landing gear to the wing frame, patent RU 2412865С1, IPC ВСС 25/04, publ. 02/27/2011. Spherical bearings include a spherical inner element having a convex outer surface. These bearings also include an outer member having a concave inner surface responsive to the outer surface of the inner member. Spherical bearings are widely used in the aviation industry, as well as in mechanical wiring and drives due to the fact that they are "self-aligning", allow you to compensate for the permissible deformation of the frame of the airframe and act as movable bearings, without perceiving the axial component Z.

During operation, the crossarm in a plane perpendicular to the geometric axis of rotation is affected by radial forces (X.Y) and axial forces (Z) directed along this axis.

To compensate for the axial forces Z, it is necessary to fix the yoke in the axial direction relative to the airframe of the aircraft.

A well-known installation of the beam, disclosed in the international application WO 2012095621 (A1), IPC: B64C 25/36, B64C 25/50, publ. 07/19/2012, in which the traverse is fixed in the axial direction by focusing the traverse beams in the frame through the brackets of the spherical supports, each of which receives and transfers axial compressive force to the frame in only one direction.

The disadvantage of the node is that it does not take into account the different stiffness of the frame of the airframe in the places of installation of bearings of spherical bearings.

Insufficient rigidity of one of the frame elements at the installation site of the support can lead to its unacceptable deformations and possible destruction of the less rigid part of the frame of the aircraft glider from the action of axial force.

Closest to the claimed invention is the installation site of the traverse of the landing gear of the aircraft, disclosed in patent US 6945496 B2, IPC: B64C 25/04, B64C 25/10, publ. 09/20/2005, containing a traverse with trunnions mounted in spherical bearings mounted in seats fixed relative to the aircraft glider frame, in order to fix the traverses in the axial direction, the trunnions are hollow and a transverse tensile shaft passing through them spherical is passed through them supports and fixed to each of the saddles. In this case, the seat located on a less rigid section of the glider is movable, which makes it possible to allow deformation under the action of axial force directed at it without breaking. After removing the load, the elastic rod returns the movable seat to its original position.

The disadvantage of the prototype is the loading of spherical bearings both axial and radial forces in the place of fastening of the rod, which can cause a mismatch of the spherical bearings, leading to jamming. Thus, unobstructed rotation of the traverse during the release - cleaning of the chassis is not ensured.

In addition, there is the possibility of fatigue failure under the influence of frequent axial loads.

Disclosure of invention

An object of the invention was the development of a simple assembly of the installation of the traverse of the landing gear of the aircraft, ensuring the fixation of the traverse in the axial direction with a load on only one area of the airframe and unobstructed rotation of the traverse during cleaning - the landing gear.

The problem is solved by creating a design

the assembly of the installation of the traverse of the landing gear of the aircraft, containing the traverse with pins mounted in spherical bearings mounted in seats fixed relative to the frame of the glider of the aircraft, and a node for fixing the traverse in the axial direction, equipped with an inner shoulder and fixed to the frame of the glider at one of the seats , while the traverse is made with an annular groove, and the inner flange of the node for fixing the traverse in the axial direction is placed in the annular groove of the traverse, and between the surfaces of Rutik and traverses provided radial clearance.

The technical result achieved by the implementation of the invention is to increase the reliability of the design of the installation site of the traverse of the landing gear of the aircraft, providing the axle fixation of the traverse with a load on only one area of the frame and unobstructed rotation of the traverse during cleaning - the landing gear.

In special cases, the execution in the installation node of the traverse:

- between at least one of the ends of the shoulder of the node for fixing the yoke in the axial direction and the lateral contour of the yoke at the place where the groove is made, at least one antifriction gasket is installed, while the thickness of the antifriction gasket is chosen equal to the gap between the ends of the bead and side contours traverses in the place of the groove;

- the node for fixing the traverse in the axial direction is made in the form of two half rings, equipped with internal flanges that, when installed, form an inner collar of the node for fixing the traverse in the axial direction, and elements for securing the half ring to the frame of the airframe, while the relief of the radial surface of the beads of the half rings in the form of a semicircular cylindrical surface, while the radii of this surface are equal for each semicircle;

- it is possible to move at least one of the pins relative to the beam in the direction of the axis of rotation, while at the end of the beam there is an axial cavity in which the pin is inserted with the ability to move along the axis of rotation inside this cavity.

Brief Description of the Drawings

The following graphic materials are used to explain the essence of the claimed utility model:

FIG. 1 - node installation of the traverse of the landing gear of the aircraft;

FIG. 2 is a section AA of FIG. one;

FIG. 3 is a diagram of the forces acting in the installation of the installation of the traverse of the rack of the axis of the chassis.

The implementation of the invention.

The installation site of the traverse of the landing gear of the aircraft (LA) allows the chassis to rotate relative to the axis of rotation (17) of the traverse (1) when cleaning - the landing gear.

The installation site of the traverse of the landing gear of the aircraft chassis (Fig. 1) contains a traverse (1) with trunnions (2, 3) mounted in spherical, such as spherical, bearings (4, 5), mounted in saddles (6, 7), fixed relative to frame of an airframe glider.

Saddles (seats for the outer rings of spherical bearings) (6, 7) can be fixed (directly made) in the frame of the glider of the aircraft (LA) or located in brackets that are fixed to this frame, for example, bolts. (Fig. 1, 2).

Also, the installation of the traverse contains a node for fixing the traverse in the axial direction (8), equipped with an inner collar (9) and fixed to the frame of the glider at one of the seats (7).

At the same time, the traverse is made with an annular groove (10), for example, a groove, while the inner collar (9) of the assembly for fixing the traverse in the axial direction is placed (inserted during assembly) in the annular groove of the traverse (10), and between the surfaces of the collar (11) and traverses (12) provided a radial clearance (13). The radial clearance is ensured by the design study of the layout with the determination of the required gap sizes or individual adjustment.

To eliminate the appearance of backlash in the axial direction, as well as impacts when there is a sharp occurrence of axial forces between the ends of the flange (9) of the assembly for fixing the yoke in the axial direction between at least one of the ends of the flange (9) of the assembly for fixing the yoke in the axial direction and at least one antifriction gasket (14), for example, made in the form of two half-rings from a metal-fluoroplastic tape, can be installed between the lateral contour of the traverse (1) in the place where the groove is made. As wear and axial play occur, the gaskets are replaced. The thickness of the antifriction gasket (14) is chosen equal to the gap between the ends of the shoulder and the lateral contours of the beam at the location of the groove, determined by the measurement results.

The assembly for fixing the yoke (8) is fixed directly to the glider frame or to the bracket of the corresponding seat at one of the seats (7) of the spherical bearing (5).

The assembly for fixing the yoke in the axial direction (8) can be made in the form of two half rings (15, 16), each of which is equipped with internal flanges that, when installed, form a common internal flange (9) of the device for fixing the yoke in the axial direction.

Fastening to the frame of the glider is carried out directly or by means of brackets, while the half rings are equipped with elements for securing the half rings to the frame of the glider, for example, flanges in the form of half rings with holes (18) located on the ends opposite to the inner shoulder (9), or seats (" legs ”) for connecting with transverse ribs made on an arm fixed to the frame of the airframe.

To increase the area for axial load distribution, it is preferable that the relief of the radial surface of the beads of the half rings be made in the form of a semi-circular cylindrical surface, with the radii of this surface for each half ring (15, 16) being equal.

The trunnions (2, 3) can be integral with the traverse or for the convenience of assembly and disassembly operations, it can be possible to move at least one of the trunnions relative to the traverse (2) in the direction of the rotation axis (17). In this case, an axial cavity (18) is executed at the end of the traverse, for example, an opening into which a movable trunnion (2, 3) is inserted, having the ability to move along the axis inside this cavity (18).

The assembly of the installation of the traverse (1) of the landing gear on LA can be carried out as follows: trunnions (2, 3) of the traverse (1) are introduced along the axis of the traverse (17) into the seats of spherical bearings (4, 5), mounted in saddles (6 , 7) fixed relative to the airframe of the aircraft. After that, the elements of the assembly are fixed to the frame for fixing the traverse in the axial direction (8) at one of the seats (7) of the spherical bearing (5), while the inner flanges of the half-rings of the assembly for fixing the traverse in the axial direction are inserted into the annular groove of the traverse (10) for the emphasis in its ends of the corresponding lateral contour of the traverse (1) at the place of execution of the groove in contact with its annular fixing collar with an annular groove.

The implementation of the invention

When cleaning - the landing gear is turning yoke (1) relative to the axis of rotation (17). Since a radial clearance (13) is provided between the surfaces of the shoulder (11) and the beam (12), the assembly for fixing the beam in the axial direction (8) does not interfere with the rotation. At the same time, during the design study, the gap value is selected taking into account the unimpeded change in the position of the axis of rotation (17) of the beam in the case of a change in the position of the saddles (6, 7) with permissible deformation of the airframe.

The compressive forces acting in a plane perpendicular to the axis of rotation of the beam, for example, vertical Υ and horizontal X, are perceived by the aircraft skeleton through the seats (6, 7) of spherical bearings (4, 5), which act as movable bearings without perceiving the axial component Ζ. (Fig. 3).

In case of axial load Ζ. depending on the direction of action of this force, the lateral contour of the yoke (19, 20) in contact with the groove (10) is in contact - it abuts against the end face (21, 22) of the shoulder (9), and a tensile or compressive force acting along the Z axis . through the assembly for fixing the yoke in the axial direction (8) to the fuselage body only in the place of its attachment to the airframe (23) at one of the seats (7) of the spherical bearing (6).

Obviously, when choosing a place for fixing the device for fixing the beam in the axial direction (8) along the axis of the beam in the forward and reverse directions, the requirement is sufficient rigidity of the body, the purpose of the perception of axial forces for only one of the mounting nodes of the beam, it is advisable to choose a place for fixing to the frame of the glider at the seat (7), which has greater rigidity, for example, in the case of constructive installation of the seats (6, 7) on the wing frame and the fuselage, the fixing point is determined at the seat 7 located on the fuselage.

Thus, as a result of the development, an assembly was obtained for the installation of the traverse of the landing gear of the aircraft, in which the axle is fixed in the axle by a device that excludes the action of axial force on spherical bearings and transfers axial loads to only one region of the aircraft glider frame located at the fixation point of one of seats for a spherical bearing, which increases reliability.

From the above it is obvious that the design of the assembly of the installation of the traverse of the landing gear of the aircraft, ensuring the fixation of the traverse in the axial direction, is simple in relation to the selected prototype, which improves the reliability of the structure and provides unobstructed rotation of the traverse during cleaning - the landing gear. In addition, the use of a node that secures the beam in the axial direction with a load of only one region of the airframe skeleton allows one to take into account the requirements for the rigidity of the body structure to compensate for the axial force for only one region of fixation of the spherical bearing seat in the place of greater rigidity.

Claims (6)

1. The installation site of the traverse of the landing gear of the aircraft, containing the traverse with pins mounted in spherical bearings mounted in seats fixed on the frame of the glider of the aircraft, characterized in that it contains a node for fixing the traverse in the axial direction, equipped with an inner collar and attached to the frame of the glider at one of the saddles, while the yoke is made with an annular groove, and the inner flange of the node for fixing the yoke in the axial direction is placed in this groove, and between the surface E bead and the radial clearance provided crosspiece. 2. The assembly of the traverse according to claim 1, in which between at least one of the ends of the inner flange and the side contour of the traverse at the location of the groove is installed at least one antifriction gasket. 3. The installation of the traverse according to claim 2, in which the thickness of the antifriction gasket is chosen equal to the gap between the ends of the shoulder and the side contours of the traverse at the location of the groove. 4. The assembly of the traverse according to any one of claims 1 to 3, in which the assembly for fixing the traverse in the axial direction is made in the form of two half rings equipped with internal collars and elements for securing the half ring to the glider frame. 5. The assembly of the traverse according to claim 4, in which the relief of the radial surface of the inner flanges of the half rings is made in the form of a semicircular cylindrical surface, while the radii of this surface for each half ring are equal. 6. The installation of the traverse according to any one of claims 1 to 3, in which an axial cavity is made in the end of the traverse, into which an axle is inserted with the ability to move along the axis of rotation inside this cavity.

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