A thin-wall aircraft workpiece inner cavity polishing device

Abstract

This application relates to a grinding device for the inner cavity of thin-walled aerospace workpieces, belonging to the field of aerospace workpiece grinding. It includes a grinding execution part and a workpiece mounting part. The workpiece mounting part includes a mounting assembly, a negative pressure generator, and a negative pressure adsorption component. The mounting assembly is connected to the negative pressure adsorption component, and the negative pressure generator is connected to the negative pressure adsorption component to create a negative pressure environment around the negative pressure adsorption component. The negative pressure adsorption component can adsorb and fix the aerospace workpiece placed in the negative pressure environment. The grinding execution part can grind the inner cavity wall surface of the aerospace workpiece. This application uses negative pressure adsorption to fix the aerospace workpiece, effectively avoiding deformation of the thin-walled aerospace workpiece during clamping while ensuring stable clamping and precise positioning during the inner cavity grinding process.

Description

Technical Field

[0001] This application relates to the field of aerospace workpiece grinding, and in particular to a grinding device for the inner cavity of thin-walled aerospace workpieces. Background Technology

[0002] Aerospace internal cavity workpieces, especially long cylindrical and thin-walled rotating aerospace workpieces, usually require grinding, refining or polishing of their internal cavity surfaces during the manufacturing process to remove internal surface defects, improve surface roughness, or meet the internal surface quality requirements of subsequent assembly, bonding, coating and other processes.

[0003] In existing technologies, the grinding of the inner walls of pipes, cylinders, or other rotating aerospace workpieces typically involves inserting a grinding mechanism into the inner cavity of the workpiece and coordinating with the rotation of the workpiece or the axial movement of the grinding mechanism to achieve continuous machining of the inner surface. For some highly automated equipment, CNC drive structures are used to control the rotation of the workpiece and the feed of the grinding head, thereby improving processing efficiency and consistency.

[0004] However, in practical applications, when processing thin-walled aerospace workpieces with internal cavities, the thin-walled aerospace workpieces have small wall thickness and weak overall rigidity. During clamping, on the one hand, if a traditional rigid clamping method is used, the clamping force is easily concentrated on a local area, which can lead to problems such as local pressure damage, radial deformation, increased ellipticity, or overall shape instability of the aerospace workpiece. On the other hand, if the clamping force is reduced to avoid significant deformation of the thin-walled aerospace workpiece during clamping, the aerospace workpiece is prone to loosening, displacement, or jumping during rotary grinding, resulting in unstable grinding trajectory, uneven local processing, and poor surface consistency. In severe cases, it may also affect the stability of equipment operation and processing safety.

[0005] Therefore, how to effectively avoid deformation of thin-walled aerospace workpieces during clamping while ensuring stable clamping and precise positioning during internal cavity grinding has become a technical problem that urgently needs to be solved in this field. Summary of the Invention

[0006] In order to effectively avoid deformation of thin-walled aerospace workpieces during clamping while ensuring stable clamping and precise positioning during the internal cavity grinding process, this application provides a grinding device for the internal cavity of thin-walled aerospace workpieces.

[0007] The technical solution of the thin-walled aerospace workpiece internal cavity grinding device provided in this application is as follows: A grinding device for the inner cavity of a thin-walled aerospace workpiece includes a grinding execution part and a workpiece mounting part. The workpiece mounting part includes a mounting assembly, a negative pressure generator, and a negative pressure adsorption component. The mounting assembly is connected to the negative pressure adsorption component, and the negative pressure generator is connected to the negative pressure adsorption component to form a negative pressure environment around the negative pressure adsorption component. The negative pressure adsorption component can adsorb and fix the aerospace workpiece placed in the negative pressure environment. The grinding execution part can grind the inner cavity wall surface of the aerospace workpiece.

[0008] By adopting the above technical solution and using negative pressure adsorption to fix the aerospace workpiece, the risk of crushing, radial deformation, increased ellipticity and overall instability caused by applying large clamping force locally to thin-walled aerospace workpieces by traditional rigid clamping methods can be reduced. At the same time, the installation stability of the aerospace workpiece during the grinding process can be guaranteed, thereby improving the grinding stability of the inner cavity wall surface of the aerospace workpiece.

[0009] Preferably, the negative pressure adsorption component includes an adsorption hood with one end open. The aerospace workpiece can be inserted into the adsorption hood and abut against the adsorption hood, forming an adsorption space between the workpiece and the adsorption hood. The negative pressure generating component acts on the adsorption space to generate negative pressure, so that the aerospace workpiece can be abutted and fixed against the adsorption hood under the action of pressure difference.

[0010] By adopting the above technical solution, the pressure difference formed inside and outside the adsorption space can be used to stably adsorb the aerospace workpiece onto the adsorption cover, thereby improving the reliability of the aerospace workpiece installation. Compared with the mechanical gripper clamping method, it is more conducive to reducing local stress concentration on thin-walled aerospace workpieces and improving the uniformity of force during the aerospace workpiece clamping process.

[0011] Preferably, the connection between the inner wall of the adsorption hood and the aerospace workpiece forms a closed contact line or contact surface.

[0012] By adopting the above technical solution, the sealing performance between the aerospace workpiece and the adsorption hood can be improved, and the damage to the negative pressure state of the adsorption space caused by external air leakage can be reduced, which is conducive to maintaining a stable adsorption and fixation effect and further improving the clamping stability of the aerospace workpiece during the rotary grinding process.

[0013] Preferably, the mounting assembly includes a first mounting base, a snap-fit ​​structure, and a rotary drive mechanism. The first mounting base is disposed on a slide rail frame. The snap-fit ​​structure is rotatably connected to the first mounting base and can fix the adsorption cover. The rotary drive mechanism is connected to the snap-fit ​​structure to drive the aerospace workpiece to rotate.

[0014] By adopting the above technical solution, it is possible to drive the aerospace workpiece to rotate around its own axis on the basis of stable installation, thereby facilitating the continuous circumferential grinding of the inner cavity wall surface of the aerospace workpiece in conjunction with the grinding execution part, and improving the continuity and processing efficiency of grinding.

[0015] Preferably, the closed end of the adsorption hood is provided with a connecting seat, the rotation axis of the connecting seat is collinear with the rotation axis of the adsorption hood, the connecting seat is provided with a gas through hole communicating with the inner cavity of the adsorption hood, and the negative pressure generating element is connected to the connecting seat through a rotary joint so as to form a gas channel communicating with the gas through hole.

[0016] By adopting the above technical solution, the negative pressure generator can continuously provide a negative pressure path to the adsorption space during the rotation of the aerospace workpiece, thereby avoiding the problem of air path interruption caused by the rotation of the aerospace workpiece, and thus ensuring that the aerospace workpiece can maintain a stable adsorption and fixation effect while rotating.

[0017] Preferably, the adsorption hood is provided with a base tube that communicates with the external environment, and a sealing tube is connected to the base tube. The sealing tube is slidably and sealed to the base tube, and the inner cavity of the base tube and the inner cavity of the sealing tube form a communication channel. The sealing tube is arranged opposite to the through hole on the aerospace workpiece, and the port of the sealing tube can cover the area of ​​the aerospace workpiece located around the through hole, so that the communication channel is isolated from the adsorption space.

[0018] By adopting the above technical solution, the through-hole area on the aerospace workpiece can be locally isolated, reducing the possibility of outside air entering the adsorption space through the through-hole of the aerospace workpiece. This helps to maintain the stability of the negative pressure in the adsorption space and improves the adaptability of the device of this application to aerospace workpieces with holes.

[0019] Preferably, the sealing tube is inserted into the base tube, and the base tube is provided with an elastic element. The elastic element is connected to the sealing tube so as to drive the end of the sealing tube to abut against the aerospace workpiece.

[0020] By adopting the above technical solution, the sealing tube can be automatically attached to the surface of the aerospace workpiece by using the elastic element, thereby compensating for the installation error, dimensional tolerance or positional deviation of the aerospace workpiece, improving the fit between the sealing tube and the aerospace workpiece, and thus improving the sealing stability and sealing reliability of the through hole area.

[0021] Preferably, the mounting assembly further includes a second mounting base, a rotating base, and a clamping and fixing structure. The second mounting base is disposed on the portion of the aerospace workpiece that is suspended above the first mounting base. The rotating base is rotatably disposed on the second mounting base. The clamping and fixing structure is disposed on the rotating base and can clamp and fix the aerospace workpiece so that the aerospace workpiece can drive the rotating base to rotate.

[0022] By adopting the above technical solutions, auxiliary support and limiting can be provided for the suspended part of the aerospace workpiece, reducing the vibration, sway, deflection or jumping of long cylindrical or thin-walled aerospace workpieces during rotary grinding, thereby improving the operational stability and grinding accuracy of aerospace workpieces during processing.

[0023] Preferably, the grinding execution part includes a spatial execution frame, a drive shaft, a power element, and a grinding wheel. The power element is connected to the spatial execution frame, the drive shaft is connected to the power element, and the grinding wheel is connected to the drive shaft. The spatial execution frame can drive the grinding wheel to change its spatial position, and the power element can drive the grinding wheel to rotate.

[0024] By adopting the above technical solution, the grinding wheel is driven to rotate under the power element, and the position of the grinding wheel is adjusted by the space execution frame, thereby realizing the grinding and processing of the inner wall surface of different positions of the aerospace workpiece, and improving the adaptability of the device to different lengths, different inner diameters or different processing areas.

[0025] Preferably, the spatial execution frame is provided with a dust suction channel that changes synchronously with the spatial position of the grinding wheel. One end of the dust suction channel is connected to the dust suction mechanism, and the other end extends to the vicinity of the grinding wheel, so as to form a negative pressure area around the grinding wheel.

[0026] By adopting the above technical solution, the dust suction channel can move synchronously with the grinding wheel, thereby timely suctioning and cleaning of dust and grinding debris generated during the grinding process, reducing the adverse effects of dust accumulation and grinding debris residue on the surface quality of the processed surface and the operating environment of the equipment.

[0027] In summary, this application includes at least one of the following beneficial technical effects: 1. This application uses negative pressure generating components and negative pressure adsorption components to install and fix aerospace workpieces by negative pressure adsorption. Compared with the traditional rigid clamping method, it can reduce the risk of crushing, radial deformation, increased ellipticity and overall instability of thin-walled aerospace workpieces caused by excessive local force during clamping, thereby helping to ensure the shape accuracy and clamping stability of aerospace workpieces. 2. This application, by setting a connecting seat, gas passage and rotary joint, enables the negative pressure passage to remain connected while the aerospace workpiece is rotating, thereby taking into account both the aerospace workpiece's rotation requirements and negative pressure adsorption requirements, avoiding air path interruption caused by rotation, and further ensuring the clamping stability of the aerospace workpiece during the grinding process. 3. By setting a second mounting base, a rotating base, and a clamping and fixing structure on the suspended part of the aerospace workpiece, this application can provide auxiliary support and limit the end or middle of the aerospace workpiece away from the adsorption cover, reduce the deflection, swaying and vibration of the long cylindrical aerospace workpiece during the rotary grinding process, and further improve the grinding accuracy and equipment operation stability. Attached Figure Description

[0028] Figure 1 This is a schematic diagram of the structure of a thin-walled aerospace workpiece inner cavity grinding device according to Embodiment 1 of this application.

[0029] Figure 2 This is a schematic diagram used to illustrate the structure of the drive shaft.

[0030] Figure 3 It is a display Figure 2 The top view in the image.

[0031] Figure 4 It is along Figure 3 A cross-sectional view along line AA in the middle.

[0032] Figure 5 yes Figure 4 Enlarged view of section B in the middle.

[0033] Figure 6 It is a structural diagram used to show the installation components.

[0034] Figure 7 This is a structural diagram used to illustrate the snap-fit ​​structure and the rotary drive mechanism.

[0035] Figure 8 yes Figure 7 Enlarged view of section C.

[0036] Figure 9 yes Figure 6 Enlarged view of section D in the middle.

[0037] Figure 10 This is a schematic diagram used to demonstrate the contact between an aerospace workpiece and the adsorption cover line.

[0038] Figure 11 This is a schematic diagram of the structure in which the aerospace workpiece contacts the adsorption cover in Example 2.

[0039] Figure 12 This is a schematic diagram of the structure of the aircraft workpiece and the adsorption cover in Example 3.

[0040] Figure 13 It is a structural diagram used to demonstrate the fit between the base tube, the sealing tube, and the aerospace workpiece with through holes.

[0041] Explanation of reference numerals in the attached drawings: 1. Slide rail frame; 2. Grinding execution part; 21. Spatial execution frame; 211. X-axis moving mechanism; 212. Z-axis moving mechanism; 213. Column; 214. Motor base; 22. Drive shaft; 221. Bushing; 222. Threaded mounting seat; 23. Power element; 231. Rotary motor; 24. Grinding wheel; 25. Dust suction hood; 26. Dust suction pipe; 261. Dust suction channel; 27. Dust suction mechanism; 271. Rotary connecting joint; 2711. First annular box; 2712. Second annular box; 272. Negative pressure fan; 273. Filter box; 3. Workpiece mounting part; 31. Mounting assembly; 311. First mounting seat; 312. Snap-fit ​​structure; 3121. Four-jaw chuck; 3122. Clamping drive mechanism; 3123. First motor; 313. Rotary drive mechanism; 3131. Second motor; 3132. Conductive slip ring assembly; 3133. Stationary brush; 3134. Rotating conductive ring; 314. Second mounting base; 315. Rotary base; 316. Clamping fixing structure; 3161. Clamping block; 3162. Clamping bolt; 32. Negative pressure generating element; 33. Negative pressure adsorption element; 331. Adsorption cover; 332. Connecting base; 333. Gas through hole; 334. Rotary joint; 4. Adsorption space; 51. Base tube; 52. Sealing tube; 53. Connecting channel; 54. Elastic element; 541. Telescopic spring; 6. Aerospace workpiece. Detailed Implementation

[0042] The following is in conjunction with the appendix Figure 1-13 This application will be described in further detail.

[0043] This application discloses a grinding device for the inner cavity of a thin-walled aerospace workpiece. Example 1

[0044] Reference Figure 1 , Figure 2A grinding device for the inner cavity of a thin-walled aerospace workpiece includes a grinding execution part 2 and a workpiece mounting part 3 mounted on a slide rail frame 1. The grinding execution part 2 includes a spatial execution frame 21, a drive shaft 22, a power element 23, and a grinding wheel 24. In this embodiment, the spatial execution frame 21 includes an X-axis moving mechanism 211 and a Z-axis moving mechanism 212. The slide rail frame 1 is provided with a guide rail arranged along the X-direction. The guide rail adopts a steel strip sealing form, and is equipped with a protective strip plate to seal the mounting holes of the guide rail, so that the top surface of the guide rail is smooth and flat, and foreign objects cannot accumulate. This not only improves the sealing effect, but also makes it aesthetically pleasing and practical. A column 213 is provided on the guide rail. The column 213 is slidably connected to the guide rail by a slider. The column 213 adopts a box-in-box structure. The column 213 is driven to move along the X direction by the X-axis moving mechanism 211. In this embodiment, both the X-axis moving mechanism 211 and the Z-axis moving mechanism 212 are driven by linear moving mechanisms composed of servo motors and lead screw and nut mechanisms. Therefore, the nut in the X-axis moving mechanism 211 is connected to the column 213, driving the column 213 to move along the X direction.

[0045] The Z-axis moving mechanism 212 is mounted on the column 213, with the lead screw centrally located to minimize deformation caused by ambient temperature, resulting in high rigidity, stable operation, and high sensitivity. Linear rails along the Z-axis are mounted on both sides of the column 213. A motor base 214, which engages with the linear rails via a slider, is also mounted on the column 213. The nut in the Z-axis moving mechanism 212 connects to the motor base 214, thereby driving the motor base 214 to move along the Z-axis.

[0046] Reference Figure 3 , Figure 4 In this embodiment, the power element 23 is a rotary motor 231, which is fixedly mounted on a motor base 214. The output shaft of the rotary motor 231 is connected to the drive shaft 22 via a bearing seat rotatably mounted on the motor base 214. In this embodiment, the drive shaft 22 consists of one or more bushings 221. The number of bushings 221 can be determined by the depth of the inner cavity of the aerospace workpiece 6. In this embodiment, two bushings 221 are used as an example. The two bushings 221 are coaxially fixedly connected by bolts to increase the length of the drive shaft 22. The grinding wheel 24 is connected to the bushing 221 in the drive shaft 22 via a threaded mounting seat 222. Specifically, the grinding wheel 24 is fixedly coaxially connected to the threaded mounting seat 222 via a shaft. The threaded mounting seat 222 is inserted into the bushing 221 of the drive shaft 22 and threadedly connected to the bushing 221 to achieve a fixed connection between the grinding wheel 24 and the drive shaft 22.

[0047] A dust suction hood 25 is provided on the end of the drive shaft 22 near the grinding wheel 24. The outer diameter of the dust suction hood 25 is larger than the diameter of the grinding wheel 24, which makes the effective range of the dust suction hood 25 larger and the dust suction effect better. The dust suction hood 25 is made of flexible material, so that when the dust suction hood 25 comes into contact with the inner wall of the aerospace workpiece 6, it will deform under pressure and will not cause impact to the aerospace workpiece 6. Two dust suction pipes 26 are fixedly provided on the drive shaft 22. Each dust suction pipe 26 has a dust suction channel 261 inside. The two dust suction pipes 26 are arranged opposite each other along the circumference of the drive shaft 22. Part of the dust suction pipe 26 protrudes outside the smaller diameter bushing 221, and part is embedded in the larger diameter bushing 221. One end of each dust suction pipe 26 is connected to the dust suction hood 25, and the other end is connected to the dust suction mechanism 27.

[0048] Reference Figure 4 , Figure 5 The vacuuming mechanism 27 includes a rotatable connector 271, a negative pressure fan 272, and a filter box 273. The rotatable connector 271 includes a first annular housing 2711 fixed to the motor base 214 and a second annular housing 2712 fixed to the drive shaft 22. The second annular housing 2712 is inserted into the first annular housing 2711, and the first annular housing 2711 and the second annular housing 2712 are rotatably connected, and a sliding seal is achieved between them through a sealing strip. The first annular housing 2711 and the second annular housing 2712 form a sealed vacuuming chamber. The second annular housing 2712 is connected to the end of the vacuuming pipe 26, allowing the vacuuming channel 261 to communicate with the vacuuming chamber.

[0049] The suction inlet of the negative pressure fan 272 is connected to the first annular housing 2711 via a pipe, allowing the negative pressure fan 272 to communicate with the dust collection chamber. This creates a negative pressure environment around the grinding wheel 24 via the dust collection hood 25, enabling the adsorption of dust and debris around the grinding wheel 24. A filter box 273 is connected in series in the pipe between the negative pressure fan 272 and the first annular housing 2711. This allows the air containing dust and debris drawn in by the negative pressure fan 272 to be filtered by the filter box 273 before entering the negative pressure fan 272, achieving the filtration and collection of dust and debris in the air. By creating a localized negative pressure area around the grinding wheel 24, dust, grinding debris, and particulate matter generated during the grinding process can be promptly removed, preventing them from accumulating in the inner cavity of the aerospace workpiece 6 or re-adhering to the machined surface, thereby improving the quality of the machined surface and the working environment of the equipment.

[0050] Reference Figure 1 , Figure 6In this embodiment, the workpiece mounting portion 3 includes a mounting assembly 31, a negative pressure generating element 32, and a negative pressure adsorption element 33. The aerospace workpiece 6 in this embodiment is a hollow, thin-walled shell that is a rotating body with one end closed and the other open. The mounting assembly 31 in this embodiment includes a first mounting base 311, a snap-fit ​​structure 312, a rotary drive mechanism 313, a second mounting base 314, a rotating base 315, and a clamping and fixing structure 316. Both the first mounting base 311 and the second mounting base 314 are fixedly mounted on the slide rail frame 1.

[0051] Reference Figure 6 , Figure 7 and Figure 8 In this embodiment, the negative pressure adsorption component 33 includes an adsorption cover 331. One end of the adsorption cover 331 is open, and the other end is closed. The adsorption cover 331 is a conical structure of rotation, with the open end being the larger end. A connecting seat 332 is fixedly and coaxially mounted on the closed end of the adsorption cover 331. The connecting seat 332 has a gas passage 333 communicating with the inner cavity of the adsorption cover 331. A rotary joint 334 is sleeved on the connecting seat 332, and the rotary joint 334 is rotatably connected to the connecting seat 332. The gas passage 333 is connected to one end of the rotary joint 334, so that the gas passage 333 remains in communication with the rotary joint 334 during the rotation of the connecting seat 332. The other end of the rotary joint 334 is connected to the negative pressure generator 32, so that the negative pressure generator 32 communicates with the gas passage 333 through the rotary joint 334. In this embodiment, the negative pressure generator 32 is one of a vacuum pump or a negative pressure fan.

[0052] The snap-fit ​​structure 312 is disposed on the first mounting base 311. In this embodiment, the snap-fit ​​structure 312 is a four-jaw chuck 3121. The four-jaw chuck 3121 is disposed on the first mounting base 311. Specifically, the four-jaw chuck 3121 includes a chuck body and four jaws disposed on the chuck body. The four jaws are distributed circumferentially along the chuck body. Each jaw can move radially relative to the chuck body to clamp or release the connecting seat 332.

[0053] Furthermore, the four-jaw chuck 3121 is equipped with a clamping drive mechanism 3122, wherein the clamping drive mechanism 3122 is used to drive the four jaws to produce a clamping action, and the rotation drive mechanism 313 is used to drive the four-jaw chuck 3121 to rotate around its own axis.

[0054] In this embodiment, the clamping drive mechanism 3122 includes a first motor 3123 mounted on the chuck body. The first motor 3123 is connected to the clamping transmission structure of the four-jaw chuck 3121 to drive the four jaws to synchronously approach or move away from the central axis of the four-jaw chuck 3121, thereby clamping or releasing the adsorption cover 331. The clamping transmission structure can be a lead screw drive structure, a gear and rack drive structure, a worm gear drive structure, a wedge linkage structure, or other transmission structures that can convert the output motion of the first motor 3123 into the radial synchronous displacement of the four jaws. By driving the clamping action of the four-jaw chuck 3121 with the first motor 3123, automatic clamping of the adsorption cover 331 can be achieved, improving clamping efficiency and enhancing the consistency and stability of the clamping action.

[0055] The rotary drive mechanism 313 includes a second motor 3131, which is connected to the chuck body of the four-jaw chuck 3121 to drive the four-jaw chuck 3121 to rotate around its own axis, thereby driving the adsorption cover 331 and the aerospace workpiece 6 adsorbed and fixed on the adsorption cover 331 to rotate synchronously. The second motor 3131 can be directly connected to the four-jaw chuck 3121, or it can be connected to the four-jaw chuck 3121 through synchronous belt drive, gear drive, chain drive, or reduction mechanism. By driving the four-jaw chuck 3121 to rotate through the second motor 3131, the aerospace workpiece 6 can achieve stable rotation while maintaining its fixed installation state, so as to cooperate with the grinding execution part 2 to continuously grind the inner wall surface of the aerospace workpiece 6.

[0056] To accommodate the rotation of the first motor 3123, a conductive slip ring assembly 3132 is provided on the first mounting base 311. The conductive slip ring assembly 3132 includes a stationary brush 3133 and a rotating conductive ring 3134 that rotates synchronously with the chuck body. The stationary brush 3133 is connected to an external power supply, and the rotating conductive ring 3134 is connected to the first motor 3123. When the equipment is in operation, the second motor 3131 drives the chuck body to rotate continuously. Since the first motor 3123 is mounted on the chuck body or rotates synchronously with the chuck body, the first motor 3123 is rotating relative to the equipment frame. At this time, the external power supply is input through the stationary brush 3133 located at the stationary end. The stationary brush 3133 and the rotating conductive ring 3134 always maintain sliding conductive contact, so that electrical energy can be continuously transferred from the stationary structure to the rotating structure and then delivered to the first motor 3123.

[0057] Reference Figure 6 , Figure 9The second mounting base 314 is disposed between the first mounting base 311 and the column 213. The rotating base 315 is rotatably connected to the second mounting base 314. The rotating base 315 has a through hole in the middle for inserting the end of the aerospace workpiece 6. The rotation axis of the rotating base 315 is collinear with the rotation axis of the adsorption cover 331. The clamping and fixing structure 316 is disposed on the rotating base 315. There are four sets of clamping and fixing structures 316, which are arranged at 90-degree intervals along the circumference of the rotating base 315. Each set of clamping and fixing structures 316 includes a clamping block 3161 and a clamping bolt 3162. The clamping bolt 3162 is arranged along the radial direction of the rotating base 315 and is threadedly connected to the rotating base 315. The clamping block 3161 is located at the end of the clamping bolt 3162 facing the center of the rotating base 315. The clamping bolt 3162 is inserted into the clamping block 3161 and is rotatably connected to the clamping block 3161. In this embodiment, the clamping block 3161 is a rubber block, and the side of the clamping block 3161 facing the center of the rotating base 315 forms an arc-shaped surface that is adapted to the surface of the aerospace workpiece 6.

[0058] Since the main positioning and fixation of the aerospace workpiece 6 are still achieved by the aforementioned negative pressure adsorption structure, the clamping and fixing structure 316 at the second mounting base 314 plays more of an auxiliary support, guiding and vibration damping role, rather than undertaking the main clamping task. This can reduce the runout of the aerospace workpiece 6 during rotation and avoid deformation of the aerospace workpiece 6 caused by excessive auxiliary clamping force.

[0059] Reference Figure 10 Because the shape of the inner cavity of the adsorption cover 331 in this application adopts a contour-following design that matches the surface shape of the aerospace workpiece 6, when the aerospace workpiece 6 is inserted into the adsorption cover 331, a closed contact line is formed at the connection between the outer surface of the aerospace workpiece 6 and the inner cavity wall of the adsorption cover 331. That is, the aerospace workpiece 6 and the adsorption cover 331 are connected by line contact. At this time, an adsorption space 4 is formed between the aerospace workpiece 6 and the adsorption cover 331. The negative pressure generator 32 acts on the adsorption space 4 to generate negative pressure, which causes a force to be generated between the aerospace workpiece 6 and the adsorption cover 331, thereby causing the adsorption cover 331 to drive the aerospace workpiece 6 to rotate. The aerospace workpiece 6 is fixed by using negative pressure adsorption, which can reduce the risk of crushing, radial deformation, increased ellipticity and overall instability caused by the traditional rigid clamping method of applying a large clamping force locally to thin-walled aerospace workpieces 6. At the same time, it can ensure the installation stability of the aerospace workpiece 6 during the grinding process, thereby improving the grinding stability of the inner cavity wall of the aerospace workpiece 6.

[0060] The implementation principle of Example 1 is as follows: First, the adsorption cover 331 is installed on the snap-fit ​​structure 312, and then one end of the aerospace workpiece 6 is inserted into the adsorption cover 331, so that the aerospace workpiece 6 and the adsorption cover 331 form an adsorption space 4. Then, the two outer ends of the aerospace workpiece 6 are placed on the rotating seat 315, and the aerospace workpiece 6 is clamped and fixed by the clamping block 3161 and the clamping bolt 3162. The aerospace workpiece 6 is stacked by adjusting the clamping bolt 3162.

[0061] Subsequently, the negative pressure generator 32 is activated, and air is drawn from the adsorption space 4 through the rotary joint 334, connecting seat 332, and gas passage 333, creating a negative pressure within the adsorption space 4. Under the pressure difference, the aerospace workpiece 6 is pressed against and fixed to the adsorption cover 331. After the aerospace workpiece 6 is installed and fixed, the second motor 3131 is activated, causing the aerospace workpiece 6 to rotate around its axis. Simultaneously, the space actuator 21 drives the grinding wheel 24 to enter the predetermined position inside the aerospace workpiece 6, and the rotary motor 231 drives the grinding wheel 24 to rotate. Through the coordination of the rotation of the aerospace workpiece 6 and the change in the position of the grinding wheel 24, continuous grinding of the inner wall of the aerospace workpiece 6 is achieved.

[0062] During the polishing process, the dust extraction mechanism 27 works simultaneously, creating a localized negative pressure area in the dust extraction channel 261 near the polishing wheel 24, which promptly removes polishing dust and shavings. After processing, the second motor 3131 and the rotary motor 231 are turned off to release the negative pressure in the adsorption space 4, and then the aerospace workpiece 6 is removed, completing one processing cycle.

[0063] Using negative pressure adsorption to fix the aerospace workpiece 6 can reduce the risk of crushing, radial deformation, increased ellipticity and overall instability caused by applying large clamping force locally to thin-walled aerospace workpiece 6 using traditional rigid clamping methods. At the same time, it can ensure the installation stability of aerospace workpiece 6 during the grinding process, thereby improving the grinding stability of the inner cavity wall surface of aerospace workpiece 6. Example 2

[0064] Reference Figure 11 The difference between this embodiment and Embodiment 1 is that the adsorption cover 331 has a higher compatibility with the aerospace workpiece 6 in this embodiment. When the aerospace workpiece 6 is inserted into the adsorption cover 331, a closed contact surface is formed at the connection between the inner wall of the adsorption cover 331 and the outer surface of the aerospace workpiece 6. That is, the adsorption cover 331 and the aerospace workpiece 6 are connected in a surface contact manner. This surface contact method improves the sealing of the connection between the adsorption cover 331 and the aerospace workpiece 6, further contributing to the generation of negative pressure within the adsorption space 4, resulting in a stronger connection between the adsorption cover 331 and the aerospace workpiece 6. Furthermore, it ensures more uniform force distribution between the aerospace workpiece 6 and the adsorption cover 331, making the shape of the aerospace workpiece 6 more stable. Example 3

[0065] Reference Figure 12 , Figure 13 The difference between this embodiment and Embodiment 1 is that the grinding device in this embodiment can grind not only aerospace workpieces 6 that are closed at one end and open at the other, but also aerospace workpieces 6 that are open at both ends. Specifically, the adsorption hood 331 is provided with a base tube 51 arranged radially. The base tube 51 passes through the inner and outer sides of the adsorption hood 331. The end of the base tube 51 located on the inner side of the adsorption hood 331 extends toward the opening of the adsorption hood 331, so that the base tube 51 is L-shaped. A sealing tube 52 is inserted into the end of the base tube 51 facing the opening of the adsorption hood 331. The sealing tube 52 and the base tube 51 are slidably and sealingly connected. The inner cavity of the base tube 51 and the inner cavity of the sealing tube 52 form a communicating channel 53.

[0066] An elastic element 54 is embedded in the base tube 51. In this embodiment, the elastic element 54 is a telescopic spring 541. One end of the telescopic spring 541 is connected to the base tube 51, and the other end is connected to the sealing tube 52. The telescopic spring 541 applies the elastic force of the sealing tube 52 extending out of the base tube 51. The inner diameter of the sealing tube 52 is larger than the diameter of the through hole on the aerospace workpiece 6, so that the sealing tube 52 can cover the area of ​​the aerospace workpiece 6 located around the through hole, thereby forming a connecting channel 53 that is isolated from the adsorption space 4.

[0067] The implementation principle of Embodiment 3 is as follows: When an aerospace workpiece 6 with a hole at the end is inserted into the adsorption cover 331, the aerospace workpiece 6 abuts against the adsorption cover 331, and the telescopic spring 541 pushes the sealing tube 52 to abut against the aerospace workpiece 6, isolating the through hole on the aerospace workpiece 6 from the adsorption space 4. When a negative pressure is generated in the adsorption space 4, the aerospace workpiece 6 can be adsorbed and fixed on the adsorption cover 331, forming an adsorption and fixation of the aerospace workpiece 6 with a hole at the end, improving the adaptability of the device of this application to aerospace workpieces 6 with holes. At the same time, relying on the connection of the sealing tube 52 to the outside atmosphere through the base tube 51, the sealing tube 52 is not easily affected by the negative pressure in the adsorption space 4 and will not detach from the aerospace workpiece 6, improving the stability of the contact between the sealing tube 52 and the aerospace workpiece 6. This allows the telescopic spring 541 to isolate the through hole on the aerospace workpiece 6 from the adsorption space 4 without applying excessive elastic force, reducing the force exerted by the telescopic spring 541 on the aerospace workpiece 6 that is opposite to the adsorption force, thereby improving the reliability of the connection between the aerospace workpiece 6 and the adsorption cover 331.

[0068] The above are all preferred embodiments of this application, and are not intended to limit the scope of protection of this application. Therefore, all equivalent changes made in accordance with the structure, shape and principle of this application should be covered within the scope of protection of this application.

Claims

1. A grinding device for the inner cavity of a thin-walled aerospace workpiece, characterized in that, It includes a grinding execution part (2) and a workpiece mounting part (3); The workpiece mounting part (3) includes a mounting assembly (31), a negative pressure generator (32), and a negative pressure adsorption component (33). The mounting assembly (31) is connected to the negative pressure adsorption component (33), and the negative pressure generator (32) is connected to the negative pressure adsorption component (33) so as to form a negative pressure environment around the negative pressure adsorption component (33). The negative pressure adsorption component (33) can adsorb and fix the aerospace workpiece (6) placed in the negative pressure environment. The grinding execution part (2) can grind the inner wall surface of the aerospace workpiece (6).

2. The thin-walled aerospace workpiece internal cavity grinding device according to claim 1, characterized in that: The negative pressure adsorption component (33) includes an adsorption cover (331), one end of which is open. The aerospace workpiece (6) can be inserted into the adsorption cover (331) and abut against the adsorption cover (331), forming an adsorption space (4) between the workpiece and the adsorption cover (331). The negative pressure generator (32) acts on the adsorption space (4) to generate negative pressure, so that the aerospace workpiece (6) can be abutted and fixed on the adsorption cover (331) under the action of pressure difference.

3. The thin-walled aerospace workpiece internal cavity grinding device according to claim 2, characterized in that: The connection between the inner wall of the adsorption cover (331) and the aerospace workpiece (6) forms a closed contact line or contact surface.

4. The thin-walled aerospace workpiece internal cavity grinding device according to claim 2, characterized in that: The mounting assembly (31) includes a first mounting base (311), a snap-fit ​​structure (312), and a rotary drive mechanism (313). The first mounting base (311) is mounted on the slide rail (1). The snap-fit ​​structure (312) is rotatably connected to the first mounting base (311) and can fix the adsorption cover (331). The rotary drive mechanism (313) is connected to the snap-fit ​​structure (312) to drive the aerospace workpiece (6) to rotate.

5. The thin-walled aerospace workpiece internal cavity grinding device according to claim 4, characterized in that: The closed end of the adsorption hood (331) is provided with a connecting seat (332). The rotation axis of the connecting seat (332) is collinear with the rotation axis of the adsorption hood (331). The connecting seat (332) is provided with a gas passage hole (333) communicating with the inner cavity of the adsorption hood (331). The negative pressure generating element (32) is connected to the connecting seat (332) through a rotary joint (334) to form a gas channel communicating with the gas passage hole (333).

6. The thin-walled aerospace workpiece internal cavity grinding device according to claim 5, characterized in that: The adsorption hood (331) is provided with a base tube (51) that communicates with the external environment. A sealing tube (52) is connected to the base tube (51). The sealing tube (52) is slidably sealed to the base tube (51). The inner cavity of the base tube (51) and the inner cavity of the sealing tube (52) form a communication channel (53). The sealing tube (52) is arranged opposite to the through hole on the aerospace workpiece (6). The port of the sealing tube (52) can cover the area of ​​the aerospace workpiece (6) around the through hole, so that the communication channel (53) is isolated from the adsorption space (4).

7. The thin-walled aerospace workpiece internal cavity grinding device according to claim 6, characterized in that: The sealing tube (52) is inserted into the base tube (51), and the base tube (51) is provided with an elastic element (54). The elastic element (54) is connected to the sealing tube (52) so as to drive the end of the sealing tube (52) to abut against the aerospace workpiece (6).

8. The thin-walled aerospace workpiece internal cavity grinding device according to claim 4, characterized in that: The mounting assembly (31) further includes a second mounting base (314), a rotating base (315), and a clamping and fixing structure (316). The second mounting base (314) is disposed on the part of the aerospace workpiece (6) that is suspended above the first mounting base (311). The rotating base (315) is rotatably disposed on the second mounting base (314). The clamping and fixing structure (316) is disposed on the rotating base (315) and can clamp and fix the aerospace workpiece (6) so that the aerospace workpiece (6) can drive the rotating base (315) to rotate.

9. The thin-walled aerospace workpiece internal cavity grinding device according to claim 1, characterized in that: The grinding execution part (2) includes a spatial execution frame (21), a drive shaft (22), a power element (23), and a grinding wheel (24). The power element (23) is connected to the spatial execution frame (21), the drive shaft (22) is connected to the power element (23), and the grinding wheel (24) is connected to the drive shaft (22). The spatial execution frame (21) can drive the grinding wheel (24) to change its spatial position, and the power element (23) can drive the grinding wheel (24) to rotate.

10. The thin-walled aerospace workpiece internal cavity grinding device according to claim 9, characterized in that: The space execution frame (21) is provided with a dust suction channel (261) that changes synchronously with the spatial position of the grinding wheel (24). One end of the dust suction channel (261) is connected to the dust suction mechanism (27), and the other end extends to the vicinity of the grinding wheel (24) so ​​as to form a negative pressure area around the grinding wheel (24).

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