Bearing for aircraft suspension system

Abstract

The utility model provides a bearing for airplane suspension system, including outer ring, inner race and a plurality of cylindrical rollers, the outer ring and the inner race between form at least two columns for cylindrical roller and accommodate the raceway, the both sides of raceway are provided with the sealing assembly that forms the cover to raceway, the outer ring corresponding raceway's middle part place is in the circumference arrangement a plurality of oil groove and corresponding oil groove setting control oil piece, the control oil piece on form a plurality of oil channel that links oil groove and raceway. In view of prior art's insufficient, the utility model provides a kind of bearing for airplane suspension system of maintenance-free, long service life, strong carrying capacity.

Description

Technical Field

[0001] This utility model relates to the field of bearings, and in particular to a bearing for an aircraft suspension system. Background Technology

[0002] Bearings are crucial components used for rotating supports in mechanical bodies, and they are widely used in various industries. Among them, aircraft suspension systems are core systems that ensure flight safety and operational reliability. Their operational stability is directly related to the overall aircraft condition, and bearings are key transmission components that must withstand suspension loads, vibration and shocks, and long-term service under complex conditions. Therefore, stringent requirements are placed on bearing performance. For example, maintenance-free operation is required due to the special installation space and the difficulty of maintenance operations; service life is required to match the overall service life of the aircraft of more than 30 years to avoid system failure due to bearing failure; and high load-bearing capacity is required to adapt to the weight load of suspension components and the dynamic impact loads during flight. Utility Model Content

[0003] To address the shortcomings of existing technologies, this invention provides a maintenance-free bearing for aircraft suspension systems that has a long service life and high load-bearing capacity.

[0004] To achieve the above objectives, this utility model provides a bearing for an aircraft suspension system, comprising an outer ring, an inner ring, and a plurality of cylindrical rollers. At least two rows of raceways are formed between the outer ring and the inner ring to accommodate the cylindrical rollers. Sealing components covering the raceways are provided on both sides of the raceways. A plurality of oil grooves and corresponding oil control elements are arranged circumferentially at the middle of the raceways on the outer ring. A plurality of oil passages connecting the oil grooves and the raceways are formed on the oil control elements.

[0005] The advantages of the above technical solution are as follows: By setting sealing components on both sides of the raceway, a seal can be formed inside the bearing, ensuring a stable environment inside the bearing. In the middle of the outer raceway, oil grooves and oil control components with oil channels are arranged circumferentially. The oil grooves can store sufficient lubricating medium in advance, and the oil control components connect the oil grooves and the raceway through their own oil channels. The lubricating medium can be continuously and stably introduced into the raceway through the oil control components to lubricate the contact area between the cylindrical rollers and the raceway. No additional grease replenishment maintenance is required to meet the needs of long-term use. Finally, through multiple rows of cylindrical rollers, while ensuring high sealing performance and long-term lubrication, the bearing's high load-bearing capacity is also taken into account, so as to achieve the purpose of maintenance-free operation and long service life.

[0006] The present invention can be further configured such that: the oil control component is made of porous polyimide material, and the oil channel is formed by the porous structure of the oil control component.

[0007] Through further design, porous polyimide material is selected to manufacture the oil control components, and the oil channels are naturally formed by its own porous structure. On the one hand, polyimide itself has excellent high temperature resistance, aging resistance, wear resistance and impact resistance. It can maintain structural stability under harsh environments such as long-term vibration and temperature difference, and is not easy to deform or fail, thus providing reliable support for the service life of bearings. On the other hand, the natural oil channels formed by the porous structure are evenly distributed and have fine pore size. They can not only achieve the slow and continuous release of lubricating medium through capillary permeation, but also regulate the oil supply rate and avoid excessive loss or insufficient supply of lubricating medium, thereby ensuring the long-term effectiveness of bearings.

[0008] This utility model can be further configured such that: the oil control component is provided with an external thread that forms a screw connection with the oil groove.

[0009] By further refining the design, an external thread adapted to the oil groove is incorporated into the oil control component to achieve a screw connection. This facilitates installation, ensures a stable connection structure, and guarantees connection strength and durability.

[0010] The present invention can be further configured such that: the sealing component includes a sealing ring and a retaining ring respectively fitted and positioned on the outer ring and on the inner ring, the sealing ring being made of an elastic material and the retaining ring being made of a rigid material.

[0011] By further designing the sealing assembly, an elastic sealing ring and a rigid retaining ring are used, which are respectively fitted and positioned on the outer and inner rings. The rigid retaining ring, fitted on the inner ring, can withstand the vibration and impact during the operation of the aircraft suspension system with its own structural strength, maintaining the precise positioning of the seal and preventing the sealing assembly from deforming or shifting due to long-term stress. The elastic sealing ring, fitted on the outer ring fixed to the external equipment, can ensure its reset through its own elasticity, avoiding long-term friction with the retaining ring under vibration and impact, and ensuring product stability.

[0012] The present invention can be further configured such that: the retaining ring is sleeved on the position opposite to the inner ring and the sealing ring, and forms a stepped portion with an outer diameter larger than the outer diameter of the inner ring, and the retaining ring and the sealing ring are fitted with a clearance.

[0013] With further design, the retaining ring is fitted onto the inner ring and the sealing ring at their relative positions, forming a stepped portion with an outer diameter larger than that of the inner ring. At the same time, the two are designed to form a clearance fit. On the one hand, the retaining ring replaces the flange that would normally be required on the inner ring to provide a limit, facilitating installation and ensuring the stability of the bearing. On the other hand, the clearance fit design between the retaining ring and the sealing ring ensures a good sealing effect while avoiding direct contact friction when the two rotate relative to each other. In conjunction with the oil groove and oil control components, the stability of the internal lubricating medium is ensured.

[0014] The present invention can be further configured such that: the retaining ring and the sealing ring are respectively provided with a first hook and a second hook, the ends of the first hook and the second hook are arranged opposite to each other, and form a clearance fit between the retaining ring and the sealing ring.

[0015] By further configuring the retaining ring and the sealing ring, respectively, a first hook and a second hook are arranged opposite to each other, and the ends of the two hooks form a clearance fit between the retaining ring and the sealing ring. This clearance fit can extend the length of the labyrinth seal, making the path for external impurities to enter the raceway longer, resulting in better interception and a more reliable internal environment. In addition, the hook structure can also provide bidirectional axial restraint for the retaining ring and the sealing ring, preventing axial displacement and separation of the two under extreme conditions, and significantly enhancing the structural stability and durability of the sealing assembly. Attached Figure Description

[0016] Figure 1 This is a schematic diagram of the structure of an embodiment of the present utility model; Figure 2 This is an embodiment of the present utility model. Figure 1 Enlarged view of part a; Figure 3 This is an embodiment of the present utility model. Figure 1 Enlarged view of part b Wherein: outer ring 1; oil groove 11; oil control component 12; inner ring 2; cylindrical roller 3; raceway 4; sealing assembly 5; sealing ring 51; second hook 511; retaining ring 52; step 521; first hook 522. Detailed Implementation

[0017] An embodiment of this utility model of a bearing for an aircraft suspension system is shown below. Figure 1-3 As shown: It includes an outer ring 1, an inner ring 2, and several cylindrical rollers 3. At least two rows of raceways 4 are formed between the outer ring 1 and the inner ring 2 to accommodate the cylindrical rollers 3. Sealing components 5 covering the raceways are provided on both sides of the raceways 4. Several oil grooves 11 and corresponding oil control elements 12 are arranged circumferentially at the center of the raceways on the outer ring 1. The oil control elements 12 are made of porous polyimide material, which can be customized with graded pores as needed: pore size distribution from micropores (<2nm) to mesopores (2-50nm). The macroscopic pores (>50nm) have a porosity of 30%-90%, and the aromatic or aliphatic polymer chains form a continuous phase to support the pore structure. In this embodiment, by customizing the gaps in the oil control component, the lubricating medium in the oil tank 11 is allowed to flow out at a rate of about 0.25mg / 24 hours, ensuring that the oil control component 12 has a number of oil channels connecting the oil tank 11 and the raceway 4, and the oil channels are formed by the porous structure of the oil control component 12.

[0018] The oil control component 12 is provided with an external thread that forms a screw connection with the oil groove 11.

[0019] The sealing assembly 5 includes a sealing ring 51 that is respectively fitted and positioned on the outer ring 1 and a retaining ring 52 on the inner ring 2. The sealing ring 51 is made of an elastic material, and the retaining ring 52 is made of a rigid material.

[0020] The retaining ring 52 is sleeved on the inner ring 2 at a radially opposite position to the sealing ring 51, and has a stepped portion 521 with an outer diameter larger than the outer diameter of the inner ring 2. The retaining ring 52 and the sealing ring 51 are fitted with a clearance.

[0021] The retaining ring 52 and the sealing ring 51 are respectively provided with a first hook portion 522 and a second hook portion 511. The ends of the first hook portion 522 and the second hook portion 511 are axially opposite to each other and form a clearance fit between the retaining ring 52 and the sealing ring 51.

[0022] The above examples are merely one preferred embodiment of this utility model. Ordinary variations and substitutions made by those skilled in the art within the scope of this utility model's technical solution are all included within the protection scope of this utility model.

Claims

1. A bearing for an aircraft suspension system, comprising an outer ring, an inner ring, and a plurality of cylindrical rollers, wherein at least two rows of raceways for accommodating the cylindrical rollers are formed between the outer ring and the inner ring, characterized in that: The raceway is provided with sealing components on both sides to cover the raceway. The outer ring is provided with a number of oil grooves and oil control components arranged circumferentially at the middle of the raceway. The oil control components are provided with a number of oil channels that connect the oil grooves and the raceway.

2. The bearing for an aircraft suspension system according to claim 1, characterized in that: The oil control component is made of porous polyimide material, and the oil passage is formed by the porous structure of the oil control component.

3. The bearing for an aircraft suspension system according to claim 1 or 2, characterized in that: The oil control component is provided with an external thread that forms a screw connection with the oil groove.

4. The bearing for an aircraft suspension system according to claim 1 or 2, characterized in that: The sealing assembly includes a sealing ring fitted and positioned on the outer ring and a retaining ring on the inner ring, wherein the sealing ring is made of an elastic material and the retaining ring is made of a rigid material.

5. The bearing for an aircraft suspension system according to claim 4, characterized in that: The retaining ring is fitted onto the inner ring at the position opposite to the sealing ring, and forms a stepped portion with an outer diameter larger than the outer diameter of the inner ring, with a clearance fit between the retaining ring and the sealing ring.

6. The bearing for an aircraft suspension system according to claim 5, characterized in that: The retaining ring and the sealing ring are respectively provided with a first hook and a second hook, the ends of the first hook and the second hook are arranged opposite to each other, and form a clearance fit between the retaining ring and the sealing ring.

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