CN216660282U

CN216660282U - Airplane flap double-track linear sliding rail

Info

Publication number: CN216660282U
Application number: CN202123441428.4U
Authority: CN
Inventors: 王志刚; 党乐; 朱江; 黎欣; 冯变变; 姜立峰
Original assignee: AVIC First Aircraft Institute
Current assignee: AVIC First Aircraft Institute
Priority date: 2021-12-31
Filing date: 2021-12-31
Publication date: 2022-06-03
Anticipated expiration: 2031-12-31

Abstract

The application provides an aircraft flap double track way linear slide rail, the slide rail includes slide rail body, slide rail dog and eccentric adjustment mechanism, wherein: the slide rail body comprises an I-shaped lower rail and an I-shaped upper rail to form a herringbone structure, the upper surface of the upper rail is at least provided with a T-shaped boss protruding out of the upper surface, the T-shaped boss is used for connecting a slide rail cover plate, and the front ends of the lower slide rail and the upper slide rail are respectively provided with a lower slide rail double-lug structure and an upper slide rail double-lug structure; the eccentric adjusting mechanism is arranged in the lower slide rail double-lug structure and/or the upper slide rail double-lug structure; and the slide rail stop block is arranged at the tail end of any one of the lower rail and the upper rail and is used for limiting the rollers which synchronously move in the lower rail and the upper rail. The application provides a wing flap double track way linear slide is buried in the wing flap box section, can realize the motion function of wing flap, can reduce the space that the slide rail breaks the wing flap structure again.

Description

Airplane flap double-track linear sliding rail

Technical Field

The application belongs to the technical field of aircraft flap structural design, and particularly relates to an aircraft flap double-track linear slide rail.

Background

The flap is a wing-shaped movable device at the edge of the wing, which can deflect downwards or slide backwards, due to the increased lift in flight. The slide rail for realizing the fullerene movement of the flap is generally arranged below the wing surface of the flap, the slide rail is in a circular arc shape or a broken line shape and is surrounded by a fairing, and the structural design is not beneficial to the optimization of aerodynamic shape. For an airplane with a thin wing flap, in order to meet the functional requirement of quick maneuvering, not allow the wing flap slide rail to protrude out of the lower wing surface and require the wing flap to move in a fullerene manner so as to provide lift force and resistance for taking off and landing, a new wing flap slide rail form is needed to meet the requirement of the airplane.

Disclosure of Invention

It is an object of the present application to provide an aircraft flap dual track linear slide to address or mitigate at least one of the problems of the background art.

The technical scheme of the application is as follows: the utility model provides an aircraft flap double track way linear slideway, the slide rail includes slide rail body, slide rail dog and eccentric adjustment mechanism, wherein:

the slide rail body comprises an I-shaped lower rail and an I-shaped upper rail to form a herringbone structure, the upper surface of the upper rail is at least provided with a T-shaped boss protruding out of the upper surface, the T-shaped boss is used for connecting a slide rail cover plate, and the front ends of the lower slide rail and the upper slide rail are respectively provided with a lower slide rail double-lug structure and an upper slide rail double-lug structure;

the eccentric adjusting mechanism is arranged in the lower slide rail double-lug structure and/or the upper slide rail double-lug structure; and

the slide rail stop block is arranged at the tail end of any one of the lower rail and the upper rail and used for limiting the rollers which synchronously move in the lower rail and the upper rail.

Further, the bottom surfaces and the side surfaces of the inner surfaces of the lower rail and the upper rail are sprayed with tungsten carbide through flame so as to enhance the wear resistance of the lower rail and the upper rail.

Furthermore, before the bottom surfaces and the side surfaces of the inner surfaces of the lower rail and the upper rail are sprayed with tungsten carbide through flame, shot peening strengthening is performed on the bottom surfaces and the side surfaces of the inner surfaces of the lower rail and the upper rail.

Furthermore, the number of the T-shaped bosses is multiple, and the areas of the T-shaped bosses are the same or different.

Further, the slide rail stop block is arranged at the tail end of the lower rail.

Furthermore, the slide rail stop block comprises a plane fixing part connected with the rail and a vertical limiting part which is positioned at the front end of the plane fixing part and is perpendicular to the plane fixing part, and the limiting of the rollers in the rail is realized through the vertical limiting part.

Further, eccentric adjustment mechanism includes interior plectrum, outer plectrum, interior eccentric bush and outer eccentric bush, and interior plectrum constitutes first eccentric adjusting part with interior eccentric bush, and outer plectrum constitutes second eccentric adjusting part with outer eccentric bush, and wherein, the one end of interior plectrum and outer plectrum all has interior tooth hole, interior eccentric bush and outer eccentric bush are outer wall and the structure of hole axle center decentraction, rotate interior eccentric bush through interior plectrum, rotate outer eccentric bush through outer plectrum, realize that the pivot axle center in interior eccentric bush and the outer eccentric bush is adjusted.

The utility model provides a wing flap double track way linear slide is embedded in wing flap box section, can realize the motion function of wing flap, can reduce the space that the slide rail breaks the wing flap structure again, and two mounting points of slide rail can reserve sufficient distance simultaneously, can satisfy the space of arranging of wing trailing edge.

Drawings

In order to more clearly illustrate the technical solutions provided in the present application, the drawings will be briefly described below. It is to be expressly understood that the drawings described below are only illustrative of some embodiments of the invention.

Fig. 1 is a schematic structural view of an aircraft flap double-track linear slide rail according to the present application.

Fig. 2 is a schematic structural diagram of the double eccentric adjustment mechanism of the present application.

Fig. 3 is a schematic view of the installation position of the stopper structure of the present application.

Detailed Description

In order to make the implementation objects, technical solutions and advantages of the present application clearer, the technical solutions in the embodiments of the present application will be described in more detail below with reference to the drawings in the embodiments of the present application.

In order to realize a track for supporting the flap and realizing the fullerene motion, the application provides a slide rail structure suitable for the thin-wing-surface fullerene motion flap.

As shown in fig. 1 to 3, the aircraft flap double-track linear sliding rail provided by the application comprises a sliding rail body 1, a sliding rail stop block 2 and an eccentric adjusting mechanism 3, and is implemented to provide support for bearing of a flap, provide a track for the retracting motion of the flap and provide debugging for the installation position of the flap.

The sliding rail body 1 comprises a groove-shaped lower rail 11 and an upper rail 12 to form a herringbone structure, and the pulley frame rollers move in the lower rail 11 and the upper rail 12. In the preferred embodiment of the present application, tungsten carbide coating is flame sprayed on the bottom and side surfaces of the lower rail 11 and the upper rail 12 to enhance the wear resistance thereof. Wherein, before the tungsten carbide coating is sprayed by flame, the bottom surface and the side surface of the inner surface of the lower rail 11 and the upper rail 12 are treated by shot peening. The upper surface 121 of the upper rail 12 is provided with at least one T-shaped boss 13 protruding out of the upper surface 121, the T-shaped boss 13 is used for connecting a slide rail cover plate, and a flap airfoil breaking part can be covered under a cruising state to maintain the integrity of an airfoil. In the embodiment shown in the drawings of the present application, the number of the T-shaped bosses 13 is three, i.e., T-shaped bosses 13A to 13B. In the preferred embodiment of the present application, the areas of the plurality of T-shaped bosses 13 may be the same or different. The front ends of the lower slide rail 11 and the upper slide rail 12 are respectively provided with a lower slide rail double-lug structure 15 and an upper slide rail double-lug structure 14, and the double-lug structures are connected with a fixed flap rear edge suspension joint through the eccentric adjusting mechanism 3, so that the postures of the slide rails can be adjusted.

Eccentric adjustment mechanism 3 includes interior plectrum 31, outer plectrum 32, interior eccentric bush 33, outer eccentric bush 34, and interior plectrum 31 and interior eccentric bush 33 constitute one set of eccentric adjustment mechanism, and interior plectrum 31 upper end has interior pin hole, and the lower extreme has a bar hole 311 that extends along length direction, and interior eccentric bush 33 has the tooth edge that adapts to interior plectrum pin hole, and interior eccentric bush 33 is the structure of outer wall and hole axle center decentraction. When the adjustable inner shifting piece 31 is used, the center of the inner eccentric bushing 33 penetrates through a bolt or a pin shaft, and the axis of the bolt or the pin shaft can be adjusted by rotating the inner shifting piece 31. The centering principle of the outer pulling piece 32 and the outer eccentric bushing 34 is the same, and will not be described in detail. After the adjustment is completed, the inner wave plate 31 and the inner eccentric bushing 33 are axially displaced, the outer wave plate 32 and the outer eccentric bushing 34 are axially displaced, and the inner wave plate 31 and the outer wave plate 32 are aligned in the strip-shaped holes 311/321 and then connected through the bolt assembly 35.

The rail stopper 2 is provided at the end of the upper rail 12, which is fixed by a connecting member, for limiting the position of the roller. It will be appreciated that, given the synchronous movement of the rollers in the lower and

upper tracks

11 and 12, the rollers in the lower track 11 will also be restrained when the position of the rollers in the upper track 12 is restrained. Therefore, in another embodiment of the present application, the rail stopper 2 may be disposed at the end of the lower rail 11. The slide rail stop block 2 comprises a plane fixing part 21, at least one through hole for a bolt to pass through is formed in the plane fixing part 21, a vertical limiting part 22 perpendicular to the plane fixing part 21 is arranged at the front end of the plane fixing part 21, and the vertical limiting part 22 can limit the position of the roller in the rail.

The utility model provides a slide rail structure is thin wing section fullerene flap motion's important component part, can realize the flap and retreat and the function of deflecting, and the binaural structure of track front end has two eccentric adjustment mechanism from top to bottom simultaneously, for the flap provides support and the regulation of gesture, and the upper surface of going up the track is equipped with one or more T type boss, can cover flap airfoil and break the part, maintains airfoil integrality under the aircraft state of cruising.

The above description is only for the specific embodiments of the present application, but the scope of the present application is not limited thereto, and any changes or substitutions that can be easily conceived by those skilled in the art within the technical scope of the present application should be covered within the scope of the present application. Therefore, the protection scope of the present application shall be subject to the protection scope of the claims.

Claims

1. The utility model provides an aircraft flap double track way linear slideway which characterized in that, the slide rail includes slide rail body (1), slide rail dog (2) and eccentric adjustment mechanism (3), wherein:

the sliding rail body (1) comprises an I-shaped lower rail (11) and an I-shaped upper rail (12) to form a herringbone structure, the upper surface (121) of the upper rail (12) is at least provided with a T-shaped boss (13) protruding out of the upper surface (121), the T-shaped boss (13) is used for connecting sliding rail cover plates, and the front ends of the lower rail (11) and the upper rail (12) are respectively provided with a lower sliding rail double-lug structure (15) and an upper sliding rail double-lug structure (14);

the eccentric adjusting mechanism (3) is arranged in the lower slide rail double-lug structure (15) and/or the upper slide rail double-lug structure (14); and

the slide rail stop block (2) is arranged at the tail end of any one of the lower rail (11) and the upper rail (12) and used for limiting rollers which synchronously move in the lower rail (11) and the upper rail (12).

2. The aircraft flap double-track linear slide rail of claim 1, wherein the inner surfaces of the lower track (11) and the upper track (12) are flame-sprayed with tungsten carbide on the bottom surface and the side surface to enhance the wear resistance.

3. The aircraft flap double-track linear slide rail of claim 2, further comprising shot peening the bottom and side surfaces of the inner surfaces of the lower track (11) and the upper track (12) before flame spraying tungsten carbide on the lower track (11) and the upper track (12).

4. The aircraft flap double-track linear slide rail of claim 1, characterized in that the number of the T-shaped bosses (13) is multiple, and the areas of the T-shaped bosses are the same or different.

5. The aircraft flap double track linear rail according to claim 1, characterized in that the rail stop (2) is arranged at the end of the lower rail (11).

6. The aircraft flap double-track linear slide rail of claim 1 or 5, wherein the slide rail stop block (2) comprises a plane fixing part (21) connected with a track and a vertical limiting part (22) which is arranged at the front end of the plane fixing part (21) and is vertical to the plane fixing part (21), and the limiting of the roller in the track is realized through the vertical limiting part (22).

7. The aircraft flap double-track linear sliding rail according to claim 1, wherein the eccentric adjusting mechanism (3) comprises an inner shifting block (31), an outer shifting block (32), an inner eccentric bushing (33) and an outer eccentric bushing (34), the inner shifting block (31) and the inner eccentric bushing (33) form a first eccentric adjusting assembly, the outer shifting block (32) and the outer eccentric bushing (34) form a second eccentric adjusting assembly, one end of each of the inner shifting block (31) and the outer shifting block (32) is provided with an inner tooth hole, the inner eccentric bushing (33) and the outer eccentric bushing (34) are both in a structure that the outer wall is not concentric with the axis of the inner hole, the inner eccentric bushing (33) is rotated through the inner shifting block (31), and the outer eccentric bushing (34) is rotated through the outer shifting block (32), so that the axes of rotating shafts in the inner eccentric bushing (33) and the outer eccentric bushing (34) are adjusted.