CN111336253A

CN111336253A - Movable hinged sealing structure for aircraft landing gear

Info

Publication number: CN111336253A
Application number: CN202010168520.9A
Authority: CN
Inventors: 李志愿; 钟声; 宁晓东; 孙继勇; 金军; 路红伟; 张成亮; 邢钟; 李璐; 李忠钰
Original assignee: AVIC Landing Gear Advanced Manufacturing Corp
Current assignee: AVIC Landing Gear Advanced Manufacturing Corp
Priority date: 2020-03-12
Filing date: 2020-03-12
Publication date: 2020-06-26
Anticipated expiration: 2040-03-12
Also published as: CN111336253B

Abstract

The invention provides a movable hinged sealing structure for an aircraft landing gear. Seal structure is used for urceolus and prevents the articulated position of activity of turning round the arm, it includes: the bearing shaft is an annular shaft and is sleeved in an inner hole of the movable hinge part; the lubricating shaft is sleeved in the bearing shaft; one part of the bush is sleeved in an inner hole of the outer cylinder, the other part of the bush is sleeved in an inner hole of the anti-torsion arm, and the bush is in contact with the bearing shaft; the shallow lubricating channel is used for lubricating between the bearing shaft and the anti-torsion arm; the deep lubrication channel is used for lubricating between the bearing shaft and the outer cylinder. Compared with the prior art, the sealing structure provided by the invention can realize lubrication and water prevention of the movable part, is simple and feasible in later maintenance and reliable in service performance, and meets the waterproof and anticorrosion use requirements of the typical hinged part of the amphibious aircraft.

Description

Movable hinged sealing structure for aircraft landing gear

Technical Field

The invention relates to the technical field of aircraft landing gear structures, in particular to a movable hinged sealing structure for an aircraft landing gear.

Background

With the need of the national rescue equipment strategy, the development of amphibious fire-fighting rescue aircraft is very important. Compared with a land-based aircraft, the amphibious aircraft has the advantages that high requirements are put forward on overall performance parameters, material characteristics and technological capacity of the aircraft, and the requirements on landing gears are higher.

The landing gear not only has various performance characteristics of a roadbed aircraft landing gear, but also puts high requirements on water resistance and corrosion resistance, particularly in a marine high-salt environment. The amphibious aircraft has water takeoff and landing capabilities, the aircraft lands and slides on water, and the landing gear of the aircraft is wholly soaked in seawater, so that the landing gear is required to have good waterproof, drainage and corrosion resistance, and the same service life of the landing gear and the aircraft body can be ensured.

The aircraft landing gear system is a very complicated electromechanical liquid composite system, the complexity of the system causes various structural forms and connection forms, and higher requirements on water resistance and corrosion resistance are also provided. Various connecting forms are also corresponding to various water-proof and corrosion-proof measures. The sealing ring is easy to be damaged and difficult to find in the assembly process of the existing waterproof measure for the movable hinged part of the landing gear of the amphibious aircraft, the assembly relation of parts is complex, the covering of the waterproof and anticorrosive part is incomplete, the construction space of the waterproof coating process is limited, and the later maintainability is difficult to achieve; however, in order to fix the corresponding hinge bolt, the outer cylinder body is provided with a stop hole, and particularly, the high-strength steel opening is easy to concentrate stress and is a fatigue source of cracks.

Disclosure of Invention

The invention aims to provide a movable hinged sealing structure for an aircraft landing gear, which has excellent waterproof performance.

The technical scheme of the invention is as follows: a kind of aircraft landing gear uses the activity hinge joint hermetically-sealed construction to be used in the outer cylinder and activity hinge joint position of the anti-twist arm, including:

the bearing shaft is an annular shaft and is sleeved in an inner hole of the movable hinge part;

the lubricating shaft is sleeved in the bearing shaft;

one part of the bush is sleeved in an inner hole of the outer cylinder, the other part of the bush is sleeved in an inner hole of the torsion-proof arm, and the bush is in contact with the bearing shaft;

the shallow lubricating channel extends from the outer end surface of the lubricating shaft to the inside of the lubricating shaft and sequentially communicates the bearing shaft and the bushing to the torsion-proof arm;

and the deep lubricating channel extends from the outer end surface of the lubricating shaft to the inside of the lubricating shaft, and sequentially communicates the bearing shaft and the bushing to the outer barrel, and the extension length of the deep lubricating channel is longer than that of the shallow lubricating channel.

In the scheme, lubricating grease is injected into the shallow lubricating channel and the deep lubricating channel, oil film sealing between the bearing shaft and the torsion-proof arm is realized through the lubricating grease injected into the shallow lubricating channel, oil film sealing between the bearing shaft and the outer cylinder is realized through the lubricating grease injected into the deep lubricating channel, and the formed oil film not only has a lubricating effect on the movable hinge joint, but also can effectively prevent water from entering.

Preferably, the shallow lubricating channel comprises a shallow lubricating groove, a first annular groove and a first through hole, and the first annular groove is annularly arranged at the end of the lubricating shaft; the first through hole radially penetrates through the bearing shaft, and the first annular groove and the first through hole are arranged close to the torsion-proof arm;

the deep lubricating channel comprises a deep lubricating groove, a second annular groove and a second through hole, and the second annular groove is annularly arranged at the end head of the lubricating shaft; the second through hole radially penetrates through the bearing shaft, and the second annular groove and the second through hole are both arranged close to the outer cylinder;

the shallow lubricating groove extends from the end surface of the lubricating shaft to the inside of the lubricating shaft, and is communicated with the first radial hole, the first annular groove and the lubricating hole which is radially communicated with the bushing to the torsion-proof arm;

the deep lubricating groove extends from the end surface of the lubricating shaft to the inside of the lubricating shaft, and is communicated with the second radial hole, the first annular groove and the lubricating hole which is radially communicated on the bushing to the outer cylinder.

For the follow-up maintainability can reach, will the bush design is split type structure, promptly, the bush includes first bush and second bush, first bush suit is in preventing the torque arm, the suit of second bush is in the urceolus, realizes that the bush is installed and is easily dismantled the back on urceolus and preventing the torque arm.

Preferably, the first bushing comprises an inner annular groove annularly arranged on the inner side wall of the first bushing, and an outer annular groove annularly arranged on the outer side wall and corresponding to the inner annular groove, wherein the number of the lubricating holes is multiple, and the lubricating holes radially penetrate between the inner annular groove and the outer annular groove and are uniformly distributed in the circumferential direction;

the second bushing and the first bushing are identical in structure and are symmetrically installed.

Preferably, an axial groove is further formed in the inner side wall of the first bushing, one end of the axial groove penetrates through the end face of one side of the first bushing, and the other end of the axial groove extends towards the inner annular groove; the second bush is arranged opposite to the penetrating end face of the axial groove of the first bush.

Preferably, the shallow lubrication channel, the deep lubrication channel and the bushing are symmetrically arranged at two ends of the lubrication shaft and the bearing shaft.

Preferably, the lubricating device further comprises a lubricating nozzle and a lubricating nozzle seat, each of the shallow lubricating channel and the deep lubricating channel is connected with one lubricating nozzle through one lubricating nozzle seat, and the lubricating nozzles are mounted on the outer end face of the lubricating shaft. The oil nozzle seat is added to realize interchangeability and maintainability, and is convenient and reliable.

Preferably, an barb matched with the shallow lubrication channel or the deep lubrication channel is arranged on the outer diameter of one end of the oil nozzle seat, an internal thread matched with the oil nozzle is arranged on the inner diameter of the other end of the oil nozzle seat, and an oil filling hole penetrating from the oil nozzle to the shallow lubrication channel or the deep lubrication channel is formed in the oil nozzle seat.

Preferably, the lubricating shaft and the bearing shaft are fixed at the middle part through fastening bolts; the sealing structure further comprises a fillet seal and a toe cap seal, the fillet seal is arranged between the bushing and the torsion-proof arm and between the bushing and the outer barrel, and the toe cap seal is arranged at two ends of the fastening bolt.

Preferably, the lubricating device further comprises a sealing ring arranged between the lubricating shaft and the bearing shaft. The end face sealing is realized with the bearing shaft inner diameter by the sealing ring, so that the lubricating grease can be prevented from overflowing, and the waterproof effect can be realized.

Compared with the related technology, the invention has the beneficial effects that: the lubrication of the movable part can be realized, the waterproof effect can be realized, the later maintenance is simple and easy, the service performance is reliable, and the waterproof and anticorrosion use requirements of the typical hinged part of the amphibious aircraft are met.

Drawings

FIG. 1 is a schematic structural view of a living hinge seal structure for an aircraft landing gear according to the present invention;

FIG. 2 is a cross-sectional view taken along line B-B of FIG. 1;

FIG. 3 is a perspective view of the first bushing of FIG. 2;

FIG. 4 is a cross-sectional view of the lubricated shaft of FIG. 2;

fig. 5 is a cross-sectional view of the bearing shaft of fig. 2;

FIG. 6 is a cross-sectional view of the nozzle base of FIG. 2;

FIG. 7 is a schematic diagram of a gluing construction of a movable hinge sealing structure for an aircraft landing gear provided by the invention;

fig. 8 is a schematic flow diagram of grease injection of the articulated seal structure for an aircraft landing gear provided by the invention.

In the attached drawing, 1 outer cylinder, 2 torsion-proof arm, 3 sensor induction sheet, 4 fastening bolt, 5 gasket, 6 nut, 7 split pin, 8 first bush, 9 second bush, 10 lubricating shaft, 11 bearing shaft, 12 oil nozzle seat, 13 oil nozzle, 14 sealing ring, 15 fillet sealing, 16 toe cap sealing, 8-1 axial groove, 8-2 internal annular groove, 8-3 lubricating hole, 8-4 external annular groove, 10-1 third annular groove, 10-2 shallow lubricating groove, 10-3 first annular groove, 10-4 first radial hole, 10-5 deep lubricating groove, 10-6 second radial hole, 10-7 second annular groove, 10-8 first mounting hole, 10-9 lightening groove, 11-1 first through hole, 11-2 second through hole, 11-3 second mounting hole, 12-1 internal thread, 12-2 barbs and 12-3 oil holes.

Detailed Description

The present invention will be described in detail below with reference to the embodiments with reference to the attached drawings. It should be noted that the embodiments and features of the embodiments may be combined with each other without conflict. For convenience of description, the words "upper", "lower", "left" and "right" in the following description are used only to indicate the correspondence between the upper, lower, left and right directions of the drawings themselves, and do not limit the structure.

As shown in fig. 1 and 2, the hinge seal structure for the landing gear of the aircraft provided by the embodiment is used at a hinge position between an outer cylinder 1 and a torsion-proof arm 2, the torsion-proof arm 2 is of a fork-shaped structure, and two ends of the torsion-proof arm are inserted and hinged at the outer side of the outer cylinder 1. The hinge is a living hinge. And sensor induction sheets 3 are arranged between the two ends of the outer cylinder 1 and the anti-torsion arm 2. In the present embodiment, two sensor sheets 3 are provided, 3/1 and 3/2.

The sealing structure comprises a fastening bolt 4, a gasket 5, a nut 6, a split pin 7, a first bushing 8, a second bushing 9, a lubricating shaft 10, a force bearing shaft 11, a shallow lubricating channel, a deep lubricating channel, a fuel nozzle seat 12, a fuel nozzle 13, a sealing ring 14, a fillet seal 15 and a ferrule seal 16.

The bearing shaft 11 is an annular shaft, and the anti-torsion arm 2 and the outer barrel 1 penetrate through the movable hinge joint part. The hollow inner cavity of the bearing shaft 11 is sleeved with the lubricating shaft 10, and the excircles at two ends of the bearing shaft 11 are sleeved with a first bushing 8 and a second bushing 9. The first bush 8 is contacted with the hinge inner hole of the torsion-proof arm 2, and the second bush 9 is contacted with the hinge inner hole of the outer cylinder 1.

As shown in fig. 2 and 3, the first bushing 8 is a flange-type annular cylinder structure with a shoulder 8-5 on one side. An inner annular groove 8-2 is annularly arranged on the inner side wall of the annular cylinder, an outer annular groove 8-4 corresponding to the inner annular groove 8-2 is annularly arranged on the outer side wall of the annular cylinder, a plurality of lubricating holes 8-3 are radially communicated between the inner annular groove 8-2 and the outer annular groove 8-4, and the plurality of lubricating holes 8-3 are circumferentially and uniformly distributed. In this embodiment, the number of the lubricating holes 8-3 is four, and the lubricating holes are uniformly distributed along the circumference of the inner side wall of the first bushing 8 at 90 degrees.

An axial groove 8-1 is further formed in the inner side wall of the first bushing 8, one end of the axial groove 8-1 penetrates through the end face, provided with the convex shoulder 8-5, of the first bushing 8, and the other end of the axial groove 8-1 extends towards the inner annular groove 8-2 and exceeds the inner annular groove 8-2. The number of the axial grooves 8-1 is four in the embodiment, and the included angles of 90 degrees are uniformly distributed along the circumference of the inner side wall of the first bushing 8.

The axial grooves 8-1 are staggered with the lubricating holes 8-3, and the axial grooves 8-1 can be positioned in the middle of the two lubricating holes 8-3.

The second bush 9 and the first bush 8 have the same structure, when the sensor.

And the external annular groove 8-4 of the first bushing 8 is filled annularly after the lubricating grease entering through the shallow lubricating channel overflows from the lubricating hole 8-3, and a lubricating oil film is formed between the first bushing 8 and the torsion-proof arm 2. Similarly, the outer annular groove of the second bush 9 is filled with grease that enters through the deep lubrication passage and that overflows from the lubrication hole, and a lubricating oil film is formed between the second bush 9 and the outer cylinder 1. The arrangement of the four axial grooves 8-1 can realize the uniformity of lubrication, the axial grooves 8-1 can realize end surface lubrication with the sensor induction sheet at the through part at one side of the convex shoulder, and the structure that the other ends of the axial grooves 8-1 are not through can prevent lubricating grease from overflowing.

As shown in fig. 2, 4 and 5, the shallow lubricating channel comprises a shallow lubricating groove 10-2, a first annular groove 10-3 and a first through hole 11-1, and the first annular groove 10-3 is annularly arranged at the end of the lubricating shaft 10; the first through hole 11-1 radially penetrates through the bearing shaft 11, and the first annular groove 10-3 and the first through hole 11-1 are both arranged close to the torsion-proof arm 2;

the deep lubricating channel comprises a deep lubricating groove 10-5, a second annular groove 10-7 and a second through hole 11-2, and the second annular groove 10-7 is annularly arranged at the end of the lubricating shaft 10; the second through hole 11-2 radially penetrates through the bearing shaft 11, and the second annular groove 10-7 and the second through hole 11-2 are both arranged close to the outer cylinder 1;

the shallow lubricating groove 10-2 extends from the end face of the lubricating shaft 10 to the inside of the lubricating shaft, and is communicated with the first radial hole 10-4, the first annular groove 10-3, and the lubricating hole 8-3 which is radially communicated with the first bushing 8 to the torsion preventing arm 2.

The deep lubricating groove 10-5 extends from the end face of the lubricating shaft 10 to the inside of the lubricating shaft, and is communicated with the second radial hole 10-6, the first annular groove 10-3 and a lubricating hole which is radially communicated on the second bushing 9 to the outer cylinder 1. The deep lubrication channel extends longer than the shallow lubrication channel.

The shallow lubrication channel realizes the lubrication function between the bearing shaft 11 and the anti-torsion arm 2. The deep lubrication channel realizes the function of lubrication between the bearing shaft 11 and the outer cylinder 1.

Each of the shallow lubrication passage and the deep lubrication passage is connected with an oil nozzle 13 through one of the oil nozzle seats 12, and the oil nozzle 13 is installed on the outer end surface of the lubrication shaft 10.

Third annular grooves 10-1 are formed in two ends of the lubricating shaft 10, the third annular grooves 10-1 are located on the outer side of the first annular grooves 10-3, sealing rings 14 are installed in the third annular grooves 10-1, and the sealing rings 14 are abutted between the lubricating shaft 10 and the force bearing shaft 11. The third annular groove 10-1, the sealing ring 14 and the inner diameter of the bearing shaft 11 realize end face sealing, so that lubricating grease can be prevented from overflowing, and a waterproof effect is achieved.

The middle part of the lubricating shaft 10 is provided with a sunken lightening groove 10-9.

As shown in fig. 2, 3, 4 and 5, the inner annular groove 8-2 and the outer annular groove 8-4 have the same axial size according to the axial positions of the first radial hole 10-4 and the second radial hole 10-6 on the lubricating shaft 10 and the first through hole 11-1 and the second through hole 11-2 on the bearing shaft 11. The number of the first radial holes 10-4, the number of the second radial holes 10-6, the number of the first through holes 11-1 and the number of the second through holes 11-2 are four in the embodiment, the first through holes and the second through holes are evenly distributed in the circumference with an included angle of 90 degrees, and the first through holes and the second through holes are aligned one by one during installation.

As shown in fig. 2 and 6, an agnail 12-2 matched with the shallow lubrication groove 10-2 or the deep lubrication groove 10-5 is arranged on the outer diameter of one end of the oil nozzle base 12, an internal thread 12-1 matched with the oil nozzle 13 is arranged on the inner diameter of the other end of the oil nozzle base 12, and an oil filling hole 12-3 penetrating from the oil nozzle 13 to the shallow lubrication groove 10-2 or the deep lubrication groove 10-5 is arranged in the oil nozzle base 12.

As shown in fig. 2, the shallow lubrication passage, the deep lubrication passage, and the first bushing 8 and the second bushing 9 are symmetrically disposed at both ends of the lubrication shaft 10 and the bearing shaft 11. That is, 8/1, 8/2, 9/1, 9/2 are used in common for the first bush 8 and the second bush 9. The oil nozzle seats 12 are used for four, 12/1, 12/2, 12/3 and 12/4 respectively as shown in the figure, and the oil nozzle seats 13 are also used for four, 13/1, 13/2, 13/3 and 13/4 respectively as shown in the figure. Two sealing rings 14 are used, 14/1 and 14/2 as shown in the figure.

As shown in fig. 2, 4 and 5, a first mounting hole 10-8 is formed in the middle of the lubricating shaft 10, a second mounting hole 11-3 is formed in the middle of the bearing shaft 11, a fastening bolt 4 penetrates through the first mounting hole 10-8 and the second mounting hole 11-3, and a washer 5, a nut 6 and a cotter pin 7 are used for achieving axial fixation.

When the entire seal is installed, it is necessary to apply a sealant to the end of the annular barrel and the end of the shoulder of the first bushing 8 to form the fillet seal 15 with the torsion beam 2, as shown in fig. 7. And (3) applying a sealant to the tail end of the annular barrel and the tail end of the shoulder of the second lining 9 to form the fillet seal 15 with the outer barrel 1. The head and the tail of the bolt 4 after installation are respectively sealed by the ferrule 16.

As shown in fig. 8, the arrows represent the flow direction of grease injection through the grease nipple 13. In the figure, A, B, a small amount of grease will overflow to lubricate the end faces of the first and second bushings and the sensor plate, and a small amount of grease will overflow at C to detect whether the bushing is fully filled. The small gap on the end surface is filled with lubricating grease, and the oil film formed by filling prevents water from entering. The sealing of the ferrule at both ends of the fastening bolt also prevents water from entering.

The result of a long-term waterproof test shows that the movable hinge sealing structure has a good waterproof effect and can meet the sealing performance of the movable connection part of the landing gear of the amphibious aircraft.

The above description is only an embodiment of the present invention, and not intended to limit the scope of the present invention, and all modifications of equivalent structures and equivalent processes, which are made by using the contents of the present specification and the accompanying drawings, or directly or indirectly applied to other related technical fields, are included in the scope of the present invention.

Claims

1. The utility model provides an aircraft is activity hinge joint seal structure for undercarriage for the activity hinge joint position of urceolus (1) and anti-torque arm (2), its characterized in that includes:

the bearing shaft (11) is an annular shaft and is sleeved in an inner hole of the movable hinge part;

the lubricating shaft (10) is sleeved in the bearing shaft (11);

one part of the bush is sleeved in an inner hole of the outer cylinder (1), the other part of the bush is sleeved in an inner hole of the torsion-proof arm (2), and the bush is in contact with the bearing shaft (11);

the shallow lubricating channel extends from the outer end face of the lubricating shaft (10) to the inside of the lubricating shaft and sequentially communicates the bearing shaft (11) and the bushing to the torsion-proof arm (2);

the deep lubricating channel extends from the outer end face of the lubricating shaft (10) to the inside of the lubricating shaft and sequentially communicates the bearing shaft (11) and the bushing to the outer cylinder (1); the deep lubrication channel extends longer than the shallow lubrication channel.

2. The articulated seal structure for aircraft landing gear according to claim 1, wherein the shallow lubrication channel comprises a shallow lubrication groove (10-2), a first annular groove (10-3) and a first through hole (11-1), the first annular groove (10-3) is annularly arranged at the head of the lubrication shaft (10); the first through hole (11-1) penetrates through the bearing shaft (11) in the radial direction, and the first annular groove (10-3) and the first through hole (11-1) are arranged close to the torsion-proof arm (2);

the deep lubricating channel comprises a deep lubricating groove (10-5), a second annular groove (10-7) and a second through hole (11-2), and the second annular groove (10-7) is annularly arranged at the end of the lubricating shaft (10); the second through hole (11-2) radially penetrates through the bearing shaft (11), and the second annular groove (10-7) and the second through hole (11-2) are arranged close to the outer cylinder (1);

the shallow lubricating groove (10-2) extends from the end face of the lubricating shaft (10) to the inside of the lubricating shaft, and is communicated with the first radial hole (10-4), the first annular groove (10-3) and a lubricating hole which is radially communicated with the bushing to the torsion preventing arm (2);

the deep lubricating groove (10-5) extends from the end face of the lubricating shaft (10) to the inside of the lubricating shaft, and is communicated with the second radial hole (10-6), the first annular groove (10-3) and the lubricating hole which is radially communicated with the bushing to the outer cylinder (1).

3. The articulated seal structure for aircraft landing gear according to claim 1, characterized in that the bushing comprises a first bushing (8) and a second bushing (9), the first bushing (8) being housed in the torsion arm (2) and the second bushing (9) being housed in the outer cylinder (1).

4. The articulated seal structure for aircraft landing gear according to claim 3, wherein the first bushing (8) comprises an inner annular groove (8-2) arranged annularly on its inner side wall, an outer annular groove (8-4) arranged annularly on its outer side wall and corresponding to the inner annular groove (8-2), and lubrication holes (8-3) radially penetrating between the inner annular groove (8-2) and the outer annular groove (8-4), the lubrication holes (8-3) being plural and arranged circumferentially and uniformly;

the second bushing (9) and the first bushing (8) are identical in structure and are symmetrically installed.

5. The articulated seal structure for aircraft landing gear according to claim 3, wherein the inner side wall of the first bushing (8) is further provided with an axial groove (8-1), one end of the axial groove (8-1) penetrates through one side end face of the first bushing (8), and the other end of the axial groove (8-1) extends to the inner annular groove (8-2); the second bush (9) is arranged opposite to the through end face of the axial groove (8-1) of the first bush (8).

6. The articulated seal structure for aircraft landing gear according to claim 1, wherein the shallow lubrication channel, the deep lubrication channel and the bushing are symmetrically arranged at both ends of the lubrication shaft (10) and the bearing shaft (11).

7. The articulated seal structure for aircraft landing gear according to claim 1, further comprising a nozzle (13) and a nozzle base (12), wherein each of the shallow lubrication passage and the deep lubrication passage is connected to one nozzle (13) through one nozzle base (12), and the nozzle (13) is mounted on the outer end surface of the lubrication shaft (10).

8. The movable hinge sealing structure for the aircraft landing gear according to claim 7, wherein an agnail (12-2) matched with the shallow lubrication channel or the deep lubrication channel is arranged on the outer diameter of one end of the oil nozzle seat (12), an internal thread (12-1) matched with the oil nozzle (13) is arranged on the inner diameter of the other end of the oil nozzle seat (12), and an oil filling hole (12-3) penetrating from the oil nozzle (13) to the shallow lubrication channel or the deep lubrication channel is formed in the oil nozzle seat (12).

9. The articulated seal structure for aircraft landing gear according to claim 1, wherein the lubricating shaft (10) and the bearing shaft (11) are fixed at their middle portions by fastening bolts (4); the sealing structure further comprises a fillet seal and a toe cap seal, the fillet seal is arranged between the bushing and the torsion-proof arm (2) and between the bushing and the outer barrel (1), and the toe cap seal is arranged at two ends of the fastening bolt (4).

10. The articulated seal structure for aircraft landing gear according to claim 1, further comprising a seal ring (14) provided between the lubricating shaft (10) and the bearing shaft (11).