A bearing bushing for an aircraft and a machining apparatus therefor

Abstract

The application discloses an aero bearing bush and a processing equipment thereof, which comprises a whole cylindrical bush body, both ends of the bush body are connected with lead-in sections, the end faces of the lead-in sections extend radially outward to form annular flanges, the outer surface of the bush body is circumferentially provided with a plurality of axial expansion grooves, support ribs are formed between adjacent expansion grooves, and the inner surface of the bush body is provided with a three-stage oil storage lubrication network, which comprises a variable-pitch spiral main oil groove, a herringbone-shaped auxiliary oil groove and a micro oil storage pit array. The aero bearing bush can release thermal expansion stress and resist fatigue load through the deep and shallow alternating expansion grooves on the outer circle of the bush, and can guarantee stable lubrication and anti-lock under severe aero working conditions through the three-stage oil storage lubrication network in the inner hole. The processing equipment can switch the inner and outer surface processing modes, reduce clamping errors, and improve the precision and use reliability of the bush finished product.

Description

Technical Field

[0001] This invention relates to the field of bearing bushing technology, specifically to an aerospace bearing bushing and its processing equipment. Background Technology

[0002] Aviation bearing bushings operate under harsh conditions of alternating loads, severe temperature fluctuations, and frequent start-stop cycles, placing extremely high demands on their load-bearing capacity, thermal deformation adaptability, lubrication reliability, and machining accuracy.

[0003] Existing aerospace bearing bushings have the following shortcomings: 1. When the bushing is subjected to thermal expansion or impact load, the shaft is prone to seizure; the lubrication structure of the bushing inner hole is simple, mostly a single oil groove, with insufficient lubricating oil delivery and storage capacity. It is difficult to establish a hydrodynamic oil film during shaft start-up and shutdown and low-speed operation, which easily leads to dry friction; the oil film coverage is limited, the oil supply is unstable, and the risk of abrasive wear is high. 2. Traditional processing equipment mostly adopts a single positioning and clamping structure, which can only realize a single processing mode of external clamping or internal support positioning of bushings. It cannot adapt to the integrated continuous processing of the inner and outer surfaces of bushings. It often requires separate equipment and separate processes to complete the cutting of the inner hole and outer circle. Multiple clamping is very easy to produce positioning deviation, causing the bushing coaxiality and roundness to exceed the tolerance, which greatly reduces the product processing accuracy and pass rate. Summary of the Invention

[0004] The purpose of this invention is to provide an aerospace bearing bushing and its processing equipment to solve the problems mentioned in the background art.

[0005] To achieve the above objectives, the present invention provides the following technical solution: an aerospace bearing bushing, comprising an integral cylindrical bushing body, wherein both ends of the bushing body are connected to an inlet section, and the end face of the inlet section extends radially outward to form an annular flange; the outer surface of the bushing body is provided with a plurality of axially extending expansion and contraction grooves in the circumferential direction, and supporting ribs are formed between adjacent expansion and contraction grooves; the inner surface of the bushing body is provided with a three-stage oil storage and lubrication network, wherein the three-stage oil storage and lubrication network includes a variable pitch spiral main oil groove, a herringbone auxiliary oil groove, and a micro oil storage pit array.

[0006] Furthermore, the depths of the expansion and contraction grooves are arranged alternately in the circumferential direction, with the depth of the deep grooves being 55% to 65% of the bushing wall thickness and the depth of the shallow grooves being 35% to 45% of the bushing wall thickness; and the bottom of the expansion and contraction grooves is a rounded transition; the two ends of the expansion and contraction grooves do not extend to the end face of the bushing.

[0007] Furthermore, the variable pitch spiral main oil groove is a single or double spiral groove that extends continuously along the inner hole axially. Its pitch gradually decreases from both ends of the bushing to the middle, and the pitch at both ends is 1.5 to 2.0 times the pitch at the middle. The spiral direction matches the rotation direction of the shaft.

[0008] Furthermore, the herringbone-shaped auxiliary oil groove is arranged in the area between the spiral main oil grooves, and is composed of multiple sets of V-shaped micro-grooves, with the V-shaped opening facing the rotation direction of the shaft and the V-shaped tip pointing to the axial midpoint of the bushing body.

[0009] The present invention also discloses a processing equipment for aerospace bearing bushings. A fixed cylinder is mounted on the base, and a support cylinder is coaxially arranged inside the fixed cylinder. Several supports are arranged inside the fixed cylinder. The support cylinder is slidably mounted in the middle of the supports. An inner support assembly is provided at the front end of the support for supporting the inner surface of the bearing bushing. A clamping assembly is provided at the front end of the fixed cylinder for clamping the outer surface of the bearing bushing. A first driving member is provided at the rear end of the base, and the first driving member is connected to the support cylinder in a transmission manner. The inner support assembly includes a drive rod and an adjusting cylinder. The adjusting cylinder is fixedly connected to the front end of the support cylinder. The drive rod is slidably assembled in the middle of the support cylinder and is coaxially arranged with the adjusting cylinder. A second drive member is provided at the rear end of the support cylinder to drive the drive rod to move horizontally. A plurality of through holes are evenly spaced on the outer surface of the adjusting cylinder. A slider is slidably arranged in each through hole. The bottom end of the slider extends to be connected to the drive rod. An elastic sheet is connected between the slider and the inner wall of the front end of the through hole. The elastic sheet is in the shape of an outwardly convex arc. When the slider moves forward, it drives the elastic sheet to convex outward further. The clamping assembly includes several clamping blocks and a drive ring. The drive ring is slidably sleeved on the outside of the fixed cylinder. The clamping blocks are evenly arranged along the front end circumference of the fixed cylinder and are slidably embedded in the inner wall of the fixed cylinder. When the drive ring rotates axially, it squeezes the clamping blocks to retract radially, thereby clamping the outer circle of the bearing bushing. The elastic sheet and the clamping blocks can work selectively or simultaneously.

[0010] Furthermore, the front end of the adjusting cylinder is provided with several sliding holes, each of which is slidably connected to a limit block, and a return spring is connected between the limit block and the inner wall of the sliding hole; the bottom rear end of the limit block is a sloping structure; the front end of the driving rod is provided with a cone head adapted to the sloping structure.

[0011] Furthermore, the fixed cylinder has several through openings corresponding to the clamping blocks. The clamping blocks are slidably assembled in the through openings. A flexible sheet is connected to the bottom of the through opening. The bottom end of the clamping block is connected to the upper end of the flexible sheet. A wedge is provided at the upper end of the clamping block. Several roller frames are circumferentially arranged on the outer surface of the fixed cylinder. The drive ring is rotatably sleeved on each roller frame. A wedge-shaped boss that matches the wedge is provided on the inner surface of the drive ring. A toothed ring is sleeved on the outer surface of the drive ring. A motor that is drivenly connected to the toothed ring is provided at the upper end of the base.

[0012] Furthermore, the elastic sheet is made of metal, and several flexible strips are provided on the outer end face of the elastic sheet.

[0013] Furthermore, the first driving component is a first telescopic cylinder, which is fixed to the rear end of the base. The rear end of the support cylinder is provided with a guide frame, on which a plurality of guide rods are provided. The guide rods are slidably connected to the rear end of the fixed cylinder. The piston end of the first telescopic cylinder is connected to the guide frame. The second driving component is a second telescopic cylinder, which is fixed to the guide frame. Its piston end passes through the guide frame and extends to connect with the driving rod.

[0014] Compared with the prior art, the beneficial effects of the present invention are: 1. This invention features alternating deep and shallow expansion and contraction grooves on the outer circumference of the bushing body, forming a differentiated flexible structure. The deep groove area exhibits high flexibility, preferentially opening elastically to release expansion stress when heated or impacted, preventing the shaft from seizing. The shallow groove area retains sufficient rigidity to bear radial loads. A three-stage oil storage and lubrication network is set in the inner hole: the variable pitch spiral main oil groove enables directional pumping of lubricating oil, establishing a stable oil film in the central load-bearing area; the herringbone-shaped auxiliary oil groove collects oil, forming a local dynamic pressure effect and expanding the oil film coverage; the micro-oil storage pits provide boundary lubrication during low-speed start-stop conditions, accommodating wear debris and adapting to aerospace alternating and frequent start-stop conditions. 2. This equipment can switch between internal surface processing mode and external surface processing mode. It can perform internal hole oil groove structure processing with external clamping and positioning; and internal support provides full-range support. After releasing the external clamp, it can process the expansion and contraction groove of the bushing outer circle, eliminating the need for multiple tooling changes and reducing clamping errors. 3. This equipment adopts a telescopic limiting block structure to achieve axial limiting and thin-walled port reinforcement support. The limiting block extends radially under the drive of the cone head to bear the axial component of the cutting force and prevent the bushing from slipping and moving. It can also provide local rigid support for the inner side of the thin-walled port of the bushing to suppress port collapse, warping and cracking, while suppressing cutting vibration and improving processing quality. Attached Figure Description

[0015] Figure 1 A schematic diagram of the structure of an aerospace bearing bushing; Figure 2 A front view schematic diagram of a machining equipment for aerospace bearing bushings; Figure 3 This is a rear view schematic diagram of a bearing bushing processing equipment for aircraft. Figure 4 A cross-sectional view of a machining equipment for aerospace bearing bushings; Figure 5 for Figure 4 Enlarged view of a portion of point A in the middle; Figure 6 This is a schematic diagram of the clamping component structure of the present invention; Figure 7 This is a schematic diagram of the internal support component structure of the present invention.

[0016] In the figure, the components are: bushing body-1, inlet section-2, expansion groove-3, variable pitch spiral main oil groove-4, herringbone auxiliary oil groove-5, micro oil storage pit array-6, base-7, fixed cylinder-8, support cylinder-9, support-10, inner support assembly-11, clamping assembly-12, drive rod-13, adjusting cylinder-14, through bar hole-15, slider-16, elastic sheet-17, clamping block-18, drive ring-19, sliding hole-20, limiting block-21, return spring-22, cone head-23, through port-24, flexible sheet-25, wedge block-26, roller frame-27, wedge-shaped boss-28, gear ring-29, motor-30, flexible strip-31, first drive component-32, guide frame-33, guide rod-34, and second drive component-35. Detailed Implementation

[0017] The technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of the present invention, and not all embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of the present invention.

[0018] like Figure 1 As shown, an aerospace bearing bushing includes an integral cylindrical bushing body 1. Both ends of the bushing body 1 are connected to an inlet section 2, and the end face of the inlet section 2 extends radially outward to form an annular flange. The outer surface of the bushing body 1 is provided with a plurality of axially extending expansion and contraction grooves 3 in the circumferential direction, and supporting ribs are formed between adjacent expansion and contraction grooves 3. The inner surface of the bushing body 1 is provided with a three-stage oil storage and lubrication network, which includes a variable pitch spiral main oil groove 4, a herringbone auxiliary oil groove 5, and a micro oil storage pit array 6.

[0019] The inlet section 2 serves as a guide chamfer during assembly, facilitating the insertion of the shaft into the bushing's inner hole and preventing scratches on the inner hole's oil groove and working surface during assembly. The annular flange acts as an axial limiting stop, locking onto the bearing housing end face after assembly to restrict the bushing's axial movement, withstand axial loads under aerospace conditions, and prevent external dust and contaminants from entering the friction pair gap. In this embodiment, the depths of each expansion and contraction groove 3 are arranged alternately in the circumferential direction, wherein the depth of the deep groove is 55% to 65% of the bushing wall thickness, and the depth of the shallow groove is 35% to 45% of the bushing wall thickness; and the bottom of the expansion and contraction groove 3 is a rounded transition.

[0020] Due to temperature changes and alternating radial loads in aviation operations, the bushing undergoes thermal expansion and contraction, as well as elastic deformation. The alternating deep and shallow expansion and contraction grooves 3 form a differentiated flexible structure. The deep grooves are more flexible and can generate greater radial elastic deformation, while the shallow grooves are more rigid and serve as the main load-bearing support ribs. When the bushing expands due to heat or is impacted and squeezed by the shaft, the deep grooves elastically open first to release the expansion stress and prevent the bushing from seizing the shaft. After the load decreases and the temperature drops, the ribs elastically retract. The rounded bottom of the grooves eliminates the stress source at sharp corners and prevents fatigue cracks from forming at the bottom of the grooves under alternating loads. The support ribs bear the radial load between the bushing and the bearing housing, ensuring the load-bearing capacity of the bushing foundation. The expansion and contraction grooves 3 can also serve as heat dissipation channels on the outer circle, improving heat dissipation efficiency.

[0021] In this embodiment, the variable pitch spiral main oil groove 4 is a single or double spiral groove that extends continuously along the inner hole axially. Its pitch gradually decreases from both ends of the bushing to the middle, and the pitch at both ends is 1.5 to 2.0 times the pitch at the middle. The spiral direction matches the rotation direction of the shaft.

[0022] When the shaft rotates, the pumping effect of the spiral grooves drives the flow of lubricating oil. The large pitch at both ends is due to the large pitch in the oil inlet areas at both ends, which provides strong axial transport capacity and quickly pumps the lubricating oil from both ends of the bushing into the friction area in the middle of the bushing. The small pitch in the middle is due to the spiral grooves becoming denser as the lubricating oil reaches the bearing area in the middle of the bushing, reducing the axial flow velocity of the lubricating oil, prolonging the residence time of the lubricating oil in the main bearing area, and establishing a stable oil film. When the shaft rotates, the spiral grooves form a positive pumping suction, continuously transporting the lubricating oil to the high-pressure bearing area in the middle of the bushing, preventing dry friction due to lack of oil in the middle area. The variable pitch spiral main oil groove 4 acts as a primary network, responsible for macroscopic lubricating oil transport and overall oil circulation.

[0023] In this embodiment, the herringbone-shaped auxiliary oil groove 5 is arranged in the area between the variable pitch spiral main oil groove 4, and is composed of multiple sets of V-shaped micro-grooves, with the V-shaped opening facing the rotation direction of the shaft and the V-shaped tip pointing to the axial midpoint of the bushing body 1.

[0024] The V-shaped opening faces the direction of rotation, and the lubricating oil is captured by the V-shaped groove, converging towards the tip of the V-shape and gathering at the midpoint of the bushing's axial direction, continuously supplying oil to the highest pressure friction pair in the middle of the bushing; the herringbone auxiliary oil groove 5 can create a local dynamic pressure effect to help lift the shaft; when the main oil groove supply fluctuates, the herringbone auxiliary oil groove 5 can temporarily store oil to compensate for local insufficient oil supply; at the same time, it diverts and diffuses the oil from the variable pitch spiral main oil groove 4 to the flat working surface between the spiral grooves, expanding the oil film coverage area.

[0025] The function of the micro-oil storage pit array 6 is that the tiny pits act as miniature oil pools to statically store lubricating oil. When the shaft starts and stops, or experiences low speed or instantaneous load impact (common start-stop conditions in aviation), and the hydrodynamic oil film is difficult to establish, a small amount of lubricating oil is squeezed out from the pits to form a boundary lubrication film, preventing direct metal-to-metal scraping during the start-stop phase. At the same time, the pits can accommodate a small amount of wear debris, reducing abrasive wear.

[0026] Please see Figures 2 to 7 As shown, this embodiment also provides a processing equipment for aerospace bearing bushings, including a base 7, a fixed cylinder 8 mounted on the base 7, a support cylinder 9 coaxially arranged inside the fixed cylinder 8, a plurality of supports 10 arranged inside the fixed cylinder 8, the support cylinder 9 slidably mounted in the middle of the supports 10, an inner support assembly 11 arranged at the front end of the supports 10 for supporting the inner surface of the bearing bushing, a clamping assembly 12 arranged at the front end of the fixed cylinder 8 for clamping the outer surface of the bearing bushing, and a first driving member 32 arranged at the rear end of the base 7, the first driving member 32 being connected to the support cylinder 9 in a transmission manner; The inner support assembly 11 includes a drive rod 13 and an adjusting cylinder 14. The adjusting cylinder 14 is fixedly connected to the front end of the support cylinder 9. The drive rod 13 is slidably assembled in the middle of the support cylinder 9 and is coaxially arranged with the adjusting cylinder 14. A second drive member 35 is provided at the rear end of the support cylinder 9 to drive the drive rod 13 to move horizontally. Several through holes 15 are evenly spaced on the outer surface of the adjusting cylinder 14. A slider 16 is slidably arranged in each through hole 15. The bottom end of the slider 16 extends to connect with the drive rod 13. An elastic piece 17 is connected between the slider 16 and the inner wall of the front end of the through hole 15. The elastic piece 17 is in the shape of an outwardly convex arc. When the slider 16 moves forward, it drives the elastic piece 17 to convex outward further. The second driving member 35 drives the driving rod 13 to move forward axially. The driving rod 13 pulls the slider 16 forward, thereby causing the slider 16 to pull the elastic plate 17 forward. The elastic plate 17 further arches outward and expands. The outer surface of the elastic plate 17 presses against the inner wall of the bushing to achieve internal support positioning. When it is necessary to remove the workpiece, the second driving member 35 simply drives the driving rod 13 to retract backward, the slider 16 moves backward, the elastic plate 17 retracts, the diameter decreases, and the workpiece is released.

[0027] The clamping assembly 12 includes several clamping blocks 18 and a drive ring 19. The drive ring 19 is slidably sleeved on the outside of the fixed cylinder 8. The clamping blocks 18 are evenly arranged along the front end circumference of the fixed cylinder 8 and are slidably embedded in the inner wall of the fixed cylinder 8. When the drive ring 19 rotates axially, it squeezes the clamping blocks 18 to retract radially, thereby clamping the outer circle of the bearing bushing. The elastic sheet 17 and the clamping blocks 18 can work selectively or simultaneously.

[0028] In this embodiment, the front end of the adjusting cylinder 14 is provided with a plurality of sliding holes 20, and each sliding hole 20 is slidably connected to a limiting block 21, and a return spring 22 is connected between the limiting block 21 and the inner wall of the sliding hole 20; the bottom rear end of the limiting block 21 is inclined; the front end of the driving rod 13 is provided with a cone head 23 adapted to the inclined structure.

[0029] When the second driving member 35 pushes the driving rod 13 forward, the cone head 23 presses forward against the inclined surface of the limiting block 21. The inclined surface converts the axial thrust into a radial component force, pushing the limiting block 21 to extend radially outward along the sliding hole 20. After extending, the end face of the limiting block 21 abuts against the front end face of the bushing, restricting the bushing from moving forward axially relative to the inner support assembly 11, bearing the axial cutting force generated during outer circle cutting, and preventing the bushing from slipping or moving.

[0030] When the drive rod 13 retracts backward, the cone 23 separates from the inclined surface of the limiting block 21, and the reset spring 22 pulls the limiting block 21 radially inward to leave the front end face of the bushing, releasing the axial limit and facilitating the subsequent overall exit of the inner support assembly 11 from the inner cavity of the bushing.

[0031] In addition, when performing end face machining on the outer surface of the bushing (such as port chamfering), the operator can align the limiting block 21 to the inner surface of the front edge of the bushing according to the machining requirements, provide local rigid support for the thin-walled port of the bushing, constrain the deformation of the thin wall of the port from the inside, and completely avoid the bushing port from collapsing, warping, and cracking during the outer circle cutting process.

[0032] The specific working steps are as follows: when it is necessary to process the end face of the front end of the outer surface of the bushing, the clamping assembly 12 clamps and fixes the rear half of the bushing, and then the adjusting cylinder 14 drives the limiting block 21 to move to the inner side position corresponding to the front end face of the bushing. Then the driving rod 13 drives the limiting block 21 to move out to abut against the inner surface of the front edge of the bushing to form support.

[0033] When machining the inner surface of the bushing, the bushing is clamped and fixed by the clamping assembly 12. The operator can operate the adjusting cylinder 14 to move the limiting block 21 to the area of ​​the rear edge of the bushing that does not need to be machined, without interfering with the cutting of the inner circle tool. Then the driving rod 13 drives the limiting block 21 to move out and abut against the rear end of the bushing to provide local reinforcement support for the rear edge of the bushing. At the same time, the internal support of the limiting block 21 can suppress the vibration generated during the machining of the bushing.

[0034] In this embodiment, the fixed cylinder 8 has several through holes 24 corresponding to the clamping blocks 18. The clamping blocks 18 are slidably assembled in the through holes 24. A flexible sheet 25 is connected to the bottom of the through holes 24. The bottom end of the clamping blocks 18 is connected to the upper end of the flexible sheet 25. A wedge block 26 is provided at the upper end of the clamping blocks 18. Several roller frames 27 are circumferentially arranged on the outer surface of the fixed cylinder 8. The drive ring 19 is rotatably sleeved on each roller frame 27. A wedge-shaped boss 28 that matches the wedge block 26 is provided on the inner surface of the drive ring 19. A toothed ring 29 is sleeved on the outer surface of the drive ring 19. A motor 30 that is connected to the toothed ring 29 is provided at the upper end of the base 7.

[0035] Motor 30 drives gear ring 29 and drive ring 19 to rotate. The wedge-shaped boss 28 on the inner side of drive ring 19 rotates circumferentially, squeezing the upper wedge block 26 of clamping block 18. The wedge block 26 is subjected to axial force, which is converted into radial force, pushing clamping block 18 to retract inward along through opening 24, so that the inner surface of clamping block 18 presses against the outer circle of bushing, realizing outer circle clamping. After processing, motor 30 drives drive ring 19 to rotate in the opposite direction, wedge-shaped boss 28 disengages from wedge block 26. Flexible sheet 25 has a certain elasticity. After losing the squeezing force of wedge-shaped boss 28, it can elastically reset, thereby pulling clamping block 18 radially outward to reset and release the workpiece.

[0036] In this embodiment, the elastic sheet 17 is made of metal, and a plurality of flexible strips 31 are provided on the outer end face of the elastic sheet 17.

[0037] The elastic sheet 17 is made of metal to ensure its elasticity and structural strength during repeated expansion and contraction, and can stably provide radial support force. Several flexible strips 31 are provided on the outer end face of the elastic sheet 17. The flexible strips 31 are in contact with the inner surface of the bushing, which can disperse the tensioning contact stress and prevent the metal elastic sheet 17 from damaging the inner wall of the bushing. At the same time, it increases the frictional resistance of the contact surface, prevents the bushing from slipping circumferentially during the cutting process, and can also adapt to the small contour error of the inner hole of the bushing, absorb cutting vibration, reduce machining marks, and improve the machining accuracy of the outer surface of the bushing.

[0038] In this embodiment, the first driving component 32 is a first telescopic cylinder, which is fixed to the rear end of the base 7. The rear end of the support cylinder 9 is provided with a guide frame 33, which is provided with a plurality of guide rods 34. The guide rods 34 are slidably connected to the rear end of the fixed cylinder 8. The piston end of the first telescopic cylinder is connected to the guide frame 33. The second driving component 35 is a second telescopic cylinder, which is fixed to the guide frame 33. Its piston end passes through the guide frame 33 and extends to connect with the driving rod 13.

[0039] The second drive component 35 independently drives the drive rod 13 to move axially and independently controls the expansion, loosening, and extension and retraction of the inner support assembly 11 and the limit block 21. It is independent of the first drive component 32. The overall movement of the support cylinder 9 (station feed) and the expansion and tightening of the inner support are decoupled and can be controlled separately.

[0040] The working principle of this embodiment is as follows: This device achieves switching between two processing modes through the first driving component 32 controlling the overall axial movement of the inner support assembly 11, the second driving component 35 independently controlling the expansion / retraction of the inner support, and the wedge clamping mechanism of the clamping assembly 12: Inner surface processing mode: The inner support assembly 11 retracts and moves into the non-processing area of ​​the fixed cylinder 8; the motor 30 drives the drive ring 19 to rotate through the gear ring 29, the wedge-shaped boss 28 on the inner side of the drive ring 19 squeezes the upper wedge block 26 of the clamping block 18, and pushes the clamping block 18 to radially retract inward along the through opening 24 of the fixed cylinder 8, and evenly clamps the bushing from the outer circumference of the bushing to achieve radial positioning of the bushing. The inner hole tool extends into the inner hole of the bushing and sequentially processes the variable pitch spiral main oil groove 4, the herringbone secondary oil groove 5 and the micro oil storage pit array 6. Outer surface machining mode: The clamping assembly 12 first holds the bearing bushing in place. The second driving member 35 drives the driving rod 13 to move forward. The forward movement of the driving rod 13 pulls the slider 16 forward, causing the outwardly convex arc-shaped elastic plate 17 to arch further outward. The elastic plate 17 fits against the inner wall of the bushing's inner hole, forming uniform support across the entire middle section of the bushing. After the bushing is positioned and supported, the clamping assembly 12 releases its grip. The first driving member 32 drives the support cylinder 9, which in turn drives the inner support assembly 11, along with the bushing, to move forward axially. This causes the bushing to move out of the front end of the fixed cylinder 8, exposing the entire outer surface of the bushing. The external tool can then perform cutting machining on the outer circle of the bushing and the alternating deep and shallow expansion and contraction grooves 3. After machining is completed, the first driving member 32 drives the support cylinder 9 and the bushing to retract. The second driving member 35 drives the driving rod 13 to move backward. The elastic plate 17 retracts inward, and the limiting block 21 retracts under the action of the return spring 22, releasing the support for the bushing.

[0041] Although the present invention has been described in detail with reference to the foregoing embodiments, those skilled in the art can still modify the technical solutions described in the foregoing embodiments or make equivalent substitutions for some of the technical features. Any modifications, equivalent substitutions, improvements, etc., made within the spirit and principles of the present invention should be included within the protection scope of the present invention.

Claims

1. An aerospace bearing bushing, comprising an integral cylindrical bushing body, characterized in that: Both ends of the bushing body are connected to inlet sections, and the end faces of the inlet sections extend radially outward to form an annular flange; the outer surface of the bushing body is provided with several axially extending expansion and contraction grooves in the circumferential direction, and supporting ribs are formed between adjacent expansion and contraction grooves; the inner surface of the bushing body is provided with a three-stage oil storage and lubrication network, which includes a variable pitch spiral main oil groove, a herringbone auxiliary oil groove, and a micro oil storage pit array.

2. The aerospace bearing bushing according to claim 1, characterized in that: The depths of the expansion and contraction grooves are arranged alternately in the circumferential direction, with the depth of the deep grooves being 55% to 65% of the bushing wall thickness and the depth of the shallow grooves being 35% to 45% of the bushing wall thickness; and the bottom of the expansion and contraction grooves is a rounded transition.

3. The aerospace bearing bushing according to claim 1, characterized in that: The variable pitch spiral main oil groove is a single or double spiral groove that extends continuously along the inner hole axially. Its pitch gradually decreases from both ends of the bushing to the middle, and the pitch at both ends is 1.5 to 2.0 times the pitch at the middle. The spiral direction matches the rotation direction of the shaft.

4. The aerospace bearing bushing according to claim 1, characterized in that: The herringbone-shaped auxiliary oil groove is arranged in the area between the spiral main oil grooves. It is composed of multiple sets of V-shaped micro-grooves, with the V-shaped opening facing the rotation direction of the shaft and the V-shaped tip pointing to the axial midpoint of the bushing body.

5. A processing equipment for aerospace bearing bushings, characterized in that: The device includes a base, on which a fixed cylinder is mounted, and a support cylinder is coaxially arranged inside the fixed cylinder. Several supports are arranged inside the fixed cylinder, and the support cylinder is slidably mounted in the middle of the supports. An inner support assembly is provided at the front end of the support for supporting the inner surface of the bearing bushing. A clamping assembly is provided at the front end of the fixed cylinder for clamping the outer surface of the bearing bushing. A first driving member is provided at the rear end of the base, and the first driving member is pulsatorically connected to the support cylinder. The inner support assembly includes a drive rod and an adjusting cylinder. The adjusting cylinder is fixedly connected to the front end of the support cylinder. The drive rod is slidably assembled in the middle of the support cylinder and is coaxially arranged with the adjusting cylinder. A second drive member is provided at the rear end of the support cylinder to drive the drive rod to move horizontally. A plurality of through holes are evenly spaced on the outer surface of the adjusting cylinder. A slider is slidably arranged in each through hole. The bottom end of the slider extends to be connected to the drive rod. An elastic sheet is connected between the slider and the inner wall of the front end of the through hole. The elastic sheet is in the shape of an outwardly convex arc. When the slider moves forward, it drives the elastic sheet to convex outward further. The clamping assembly includes several clamping blocks and a drive ring. The drive ring is slidably sleeved on the outside of the fixed cylinder. The clamping blocks are evenly arranged along the front end circumference of the fixed cylinder and are slidably embedded in the inner wall of the fixed cylinder. When the drive ring rotates axially, it squeezes the clamping blocks to retract radially, thereby clamping the outer circle of the bearing bushing.

6. The processing equipment for aerospace bearing bushings according to claim 5, characterized in that: The front end of the adjusting cylinder has several sliding holes circumferentially opened, and each sliding hole is slidably connected to a limit block, and a return spring is connected between the limit block and the inner wall of the sliding hole; the bottom rear end of the limit block has an inclined structure; the front end of the driving rod is provided with a cone head adapted to the inclined structure.

7. The processing equipment for aerospace bearing bushings according to claim 5, characterized in that: The fixed cylinder has several through openings corresponding to the clamping blocks. The clamping blocks are slidably assembled in the through openings. A flexible sheet is connected to the bottom of the through opening. The bottom end of the clamping block is connected to the upper end of the flexible sheet. A wedge is provided at the upper end of the clamping block. Several roller frames are circumferentially arranged on the outer surface of the fixed cylinder. The drive ring is rotatably sleeved on each roller frame. A wedge-shaped boss that matches the wedge is provided on the inner surface of the drive ring. A toothed ring is sleeved on the outer surface of the drive ring. A motor that is drivenly connected to the toothed ring is provided at the upper end of the base.

8. The processing equipment for aerospace bearing bushings according to claim 5, characterized in that: The elastic sheet is made of metal, and several flexible strips are provided on the outer end face of the elastic sheet.

9. The processing equipment for aerospace bearing bushings according to claim 5, characterized in that: The first driving component is a first telescopic cylinder, which is fixed to the rear end of the base. The rear end of the support cylinder is provided with a guide frame, which is provided with a plurality of guide rods. The guide rods are slidably connected to the rear end of the fixed cylinder. The piston end of the first telescopic cylinder is connected to the guide frame. The second driving component is a second telescopic cylinder, which is fixed to the guide frame. Its piston end passes through the guide frame and extends to connect with the driving rod.

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