A needle roller bearing for an aircraft landing gear

Abstract

The utility model discloses a kind of needle roller bearings for aircraft landing gear, it is related to the technical field of aircraft landing gear, including outer ring and lubricating assembly, the inside of outer ring is provided with retainer, and the inside rotation of retainer is connected with needle body, the outside of outer ring is placed with outer sleeve, the inside of outer sleeve is set to lubricating assembly, and lubricating assembly includes oil inlet pipe, shunt cavity, oil injection hole, elastic strip and oil limiting groove.The needle roller bearings for aircraft landing gear are set through the setting of lubricating assembly, since oil inlet pipe is connected with the oil supply equipment outside, thus when needle body needs to be lubricated, it is not necessary to disassemble needle roller bearings as a whole, only need to inject oil into shunt cavity, with internal oil pressure increasing can extrude elastic strip and flow into oil injection hole from oil limiting groove, to spray to the outside of needle body, automatically lubricate operation, simultaneously, oil injection hole is inclined, so that the oil ejected covers the side of needle body, and when needle body rotates, it can be fully lubricated.

Description

Technical Field

[0001] This utility model relates to the field of aircraft landing gear technology, specifically to a needle roller bearing for aircraft landing gear. Background Technology

[0002] Landing gear is the core component of aircraft ground safety, and needle roller bearings, through their high load-bearing capacity, impact resistance, and compact design, become its durable joints. They ensure the smooth landing of the hundreds-ton aircraft and support precise control during high-speed taxiing. The synergistic effect of the two directly affects the safety of takeoff and landing and operational efficiency.

[0003] Existing needle roller bearings are not convenient for automatic lubrication of the needle rollers during use. If they are not disassembled and lubricated in time, the wear of the needle roller bearings will be accelerated, leading to equipment damage. Utility Model Content

[0004] The purpose of this invention is to provide a needle roller bearing for aircraft landing gear to solve the problems mentioned in the background art.

[0005] To achieve the above objectives, this utility model provides the following technical solution: a needle roller bearing for aircraft landing gear, comprising an outer ring and a lubrication assembly. A cage is provided inside the outer ring, and a needle body is rotatably connected inside the cage. An outer sleeve is disposed on the outer side of the outer ring. The lubrication assembly is disposed inside the outer sleeve and includes an oil inlet pipe, a flow distribution chamber, an oil injection hole, an elastic strip, and an oil limiting groove. An oil inlet pipe is disposed inside one end of the outer sleeve. A flow distribution chamber is opened on the outer side of the outer ring, and an oil injection hole is opened in the middle of the outer ring. An elastic strip is disposed inside the flow distribution chamber, and an oil limiting groove is opened inside the elastic strip.

[0006] Furthermore, the oil limiting groove is cross-shaped, and the oil limiting groove corresponds one-to-one with the oil injection hole.

[0007] Furthermore, the injection holes are inclined and are equidistantly distributed along the outer periphery of the outer ring.

[0008] Furthermore, a first groove is provided on one side of the outer ring, and a first sealing ring is placed inside the first groove.

[0009] Furthermore, a first protruding ring is provided on one side of the first sealing ring, and the first protruding ring is fixedly connected to the outer sleeve.

[0010] Furthermore, a second groove is provided on the other side of the outer ring, and a second sealing ring is placed inside the second groove.

[0011] Furthermore, a second protruding ring is provided on one side of the second sealing ring, and the second protruding ring is fixedly connected to the outer sleeve.

[0012] Furthermore, the outer peripheral surface of the outer sleeve is provided with bolts, and the outer peripheral surface of the outer ring is provided with threaded holes, and the bolts are threadedly connected to the outer ring through the threaded holes.

[0013] This utility model provides a needle roller bearing for aircraft landing gear, which has the following advantages:

[0014] 1. This utility model, through the setting of the lubrication component, since the oil inlet pipe is connected to the external oil supply equipment, does not require the complete disassembly of the needle roller bearing when the needle body needs to be lubricated. It only needs to inject oil into the distribution chamber. As the internal oil pressure increases, it can squeeze the elastic strip and flow from the oil limiting groove into the oil spray hole, thereby spraying it to the outside of the needle body for automatic lubrication. At the same time, the oil spray hole is inclined so that the sprayed oil covers the side of the needle body. When the needle body rotates, it can be fully lubricated. When the oil supply stops, the oil limiting groove of the elastic strip can be reset to block the oil and prevent all the oil in the distribution chamber from flowing out through the oil spray hole, thereby preventing excessive waste.

[0015] 2. This utility model, through the design of the outer sleeve, allows for easy maintenance and cleaning of the flow distribution cavity after disassembly, since the outer sleeve and outer ring are designed separately. At the same time, during installation, the first and second convex rings can be inserted into the first and second grooves respectively, pressing the first and second sealing rings together. Then, bolts and threaded holes are used to lock the outer ring and the outer sleeve, thereby improving the sealing performance between the outer ring and the outer sleeve and preventing oil leakage. Attached Figure Description

[0016] Figure 1 This is a schematic diagram of the overall three-dimensional structure of a needle roller bearing for aircraft landing gear according to the present invention.

[0017] Figure 2 This is a three-dimensional structural diagram of the outer ring of a needle roller bearing for aircraft landing gear according to the present invention.

[0018] Figure 3 This is a three-dimensional structural diagram of the outer sleeve of a needle roller bearing for aircraft landing gear according to the present invention.

[0019] In the diagram: 1. Outer ring; 2. Cage; 3. Needle body; 4. Outer sleeve; 5. Lubrication assembly; 501. Oil inlet pipe; 502. Diverter chamber; 503. Oil injection hole; 504. Elastic strip; 505. Oil limiting groove; 6. First groove; 7. First sealing ring; 8. First convex ring; 9. Second groove; 10. Second sealing ring; 11. Second convex ring; 12. Bolt; 13. Threaded hole. Detailed Implementation

[0020] The embodiments of this utility model will be described in further detail below with reference to the accompanying drawings and examples. The following examples are for illustrative purposes only and should not be construed as limiting the scope of this utility model.

[0021] like Figure 1 and Figure 2 As shown, a needle roller bearing for aircraft landing gear includes an outer ring 1 and a lubrication assembly 5. A cage 2 is disposed inside the outer ring 1, and needle bodies 3 are rotatably connected inside the cage 2. The cage 2 provides isolation and limiting between multiple needle bodies 3. An outer sleeve 4 is disposed on the outer side of the outer ring 1. The lubrication assembly 5 is disposed inside the outer sleeve 4 and includes an oil inlet pipe 501, a distribution cavity 502, an oil injection hole 503, an elastic strip 504, and an oil limiting groove 505. An oil inlet pipe 501 is disposed inside one end of the outer sleeve 4. The distribution cavity 502 is opened on the outer side of the outer ring 1, and an oil injection hole 503 is opened in the middle of the outer ring 1. An external oil supply device injects oil into the distribution cavity 502 through the oil inlet pipe 501, and then distributes it to each oil injection hole 503. The oil is sprayed onto the outside of the needle body 3. The oil spray holes 503 are inclined and are equidistantly distributed around the outer periphery of the outer ring 1. Since the inclined oil spray holes 503 are a certain distance from the side of the needle body 3, the sprayed oil has a certain diffusion distance, covering the side of the needle body 3. An elastic strip 504 is installed inside the diversion cavity 502, and a limiting oil groove 505 is opened inside the elastic strip 504. The limiting oil groove 505 is cross-shaped and corresponds one-to-one with the oil spray hole 503. When the oil supply stops, the limiting oil groove 505 of the elastic strip 504 can be reset to block the oil and prevent all the oil inside the diversion cavity 502 from flowing out through the oil spray hole 503, thereby preventing excessive waste.

[0022] like Figures 1 to 3 As shown, a first groove 6 is provided on one side of the outer ring 1, and a first sealing ring 7 is placed inside the first groove 6. A first convex ring 8 is provided on one side of the first sealing ring 7, and the first convex ring 8 is fixedly connected to the outer sleeve 4. The first convex ring 8 will press the first sealing ring 7 in the first groove 6. A second groove 9 is provided on the other side of the outer ring 1, and a second sealing ring 10 is placed inside the second groove 9. A second convex ring 11 is provided on one side of the second sealing ring 10, and the second convex ring 11 is fixedly connected to the outer sleeve 4. The second convex ring 11 will press the second sealing ring 10 in the second groove 9, which can improve the sealing performance. A bolt 12 is provided on the outer circumferential surface of the outer sleeve 4, and a threaded hole 13 is provided on the outer circumferential surface of the outer ring 1. The bolt 12 is threadedly connected to the outer ring 1 through the threaded hole 13. The bolt 12 and the threaded hole 13 are used to lock the outer ring 1 and the outer sleeve 4.

[0023] In summary, the landing gear of this aircraft uses needle roller bearings. When using them, firstly, according to... Figure 1 , Figure 2 and Figure 3 The structure shown first connects the oil inlet pipe 501 to an external oil supply device. After a period of use, the oil supply device is activated to inject lubricating oil into the distribution chamber 502. Then, as the oil pressure inside the distribution chamber 502 increases, it squeezes the elastic strip 504 and flows from the oil limiting groove 505 into the spray hole 503, spraying it towards the outside of the needle body 3. Therefore, when the needle body 3 rotates, it is fully lubricated. When the oil supply is stopped, the oil limiting groove 505 of the elastic strip 504 returns to its original position to block the oil and prevent further leakage. All the oil inside the flow divider 502 flows out through the oil injection hole 503. Finally, when maintenance and cleaning of the flow divider 502 are required, the outer ring 1 and the outer sleeve 4 can be disassembled simply by loosening the bolt 12. At the same time, during installation, the first convex ring 8 and the second convex ring 11 can be inserted into the first groove 6 and the second groove 9 respectively, pressing the first sealing ring 7 and the second sealing ring 10. Then, the bolt 12 and the threaded hole 13 are used to lock the outer ring 1 and the outer sleeve 4, thereby improving the sealing performance between the outer ring 1 and the outer sleeve 4.

[0024] The embodiments of this utility model are given for illustrative and descriptive purposes only, and are not intended to be exhaustive or to limit the utility model to the forms disclosed. Many modifications and variations will be apparent to those skilled in the art. The embodiments were chosen and described in order to better illustrate the principles and practical applications of this utility model, and to enable those skilled in the art to understand this utility model and design various embodiments with various modifications suitable for a particular purpose.

Claims

1. A needle roller bearing for aircraft landing gear, comprising an outer ring (1) and a lubrication assembly (5), characterized in that, The outer ring (1) is provided with a retainer (2) inside, and a needle body (3) is rotatably connected inside the retainer (2). The outer ring (1) is provided with an outer sleeve (4) on the outside. The lubrication component (5) is provided inside the outer sleeve (4). The lubrication component (5) includes an oil inlet pipe (501), a flow divider (502), an oil injection hole (503), an elastic strip (504), and an oil limiting groove (505). The oil inlet pipe (501) is provided inside one end of the outer sleeve (4). The flow divider (502) is provided on the outside of the outer ring (1). The oil injection hole (503) is provided in the middle of the outer ring (1). The elastic strip (504) is provided inside the flow divider (502). The oil limiting groove (505) is provided inside the elastic strip (504).

2. The needle roller bearing for aircraft landing gear according to claim 1, characterized in that, The oil limiting groove (505) is cross-shaped, and the oil limiting groove (505) corresponds one-to-one with the oil injection hole (503).

3. The needle roller bearing for aircraft landing gear according to claim 1, characterized in that, The oil injection holes (503) are inclined and are equidistantly distributed along the outer periphery of the outer ring (1).

4. A needle roller bearing for aircraft landing gear according to claim 1, characterized in that, A first groove (6) is provided on one side of the outer ring (1), and a first sealing ring (7) is placed inside the first groove (6).

5. A needle roller bearing for aircraft landing gear according to claim 4, characterized in that, A first protruding ring (8) is provided on one side of the first sealing ring (7), and the first protruding ring (8) is fixedly connected to the outer sleeve (4).

6. A needle roller bearing for aircraft landing gear according to claim 5, characterized in that, A second groove (9) is provided on the other side of the outer ring (1), and a second sealing ring (10) is placed inside the second groove (9).

7. A needle roller bearing for aircraft landing gear according to claim 6, characterized in that, A second protruding ring (11) is provided on one side of the second sealing ring (10), and the second protruding ring (11) is fixedly connected to the outer sleeve (4).

8. A needle roller bearing for aircraft landing gear according to claim 7, characterized in that, The outer circumferential surface of the outer jacket (4) is provided with bolts (12), and the outer circumferential surface of the outer ring (1) is provided with threaded holes (13), and the bolts (12) are threadedly connected to the outer ring (1) through the threaded holes (13).

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