Aerospace forge piece manufacturing device with defect detection function and technology of aerospace forge piece manufacturing device

Abstract

The invention provides an aerospace forge piece manufacturing device with a defect detection function and a process of the aerospace forge piece manufacturing device, and relates to the technical field of aerospace forge piece manufacturing. A fixing groove is formed in the front end of the workbench top end, and two threaded holes are formed in the two sides of the fixing groove correspondingly. The detection ring and the detection sensor are moved up and down through the electric cylinder, the detection ring is sleeved on the spaceflight forge piece, the detection sensor moves up and down to automatically detect the spaceflight forge piece, the detection sensor detects defects on the spaceflight forge piece at the moment, and the detection sensor can provide high-precision measurement data. Tiny defects and irregularities can be detected, and it is ensured that the quality of the forge piece meets the strict spaceflight standard; the problems that spaceflight forgings need to be detected automatically, and if the spaceflight forgings are detected manually, errors can occur, and the detection quality can be affected are solved.

Description

Technical Field

[0001] The invention relates to the technical field of aerospace forging manufacturing, and in particular to an aerospace forging manufacturing device with defect detection and a process thereof. Background Art

[0002] The aerospace field is at the forefront of modern science and technology, involving national security, economic development, scientific research progress and other aspects. In this field, forgings, as an important basic material, are widely used in the manufacture of aircraft, spacecraft, engines and their key components. Due to their excellent mechanical properties, toughness and durability, forgings can withstand extreme working environments and high-load operations, so they play an indispensable role in the aerospace industry. The quality of forgings directly affects the safety and reliability of aerospace products. During flight, aircraft are subjected to huge aerodynamic loads and temperature changes, so the structure and performance requirements of forgings are extremely high. High-strength, low-density, and high-temperature resistant forging materials can effectively improve the performance of aerospace products and extend their service life, thereby gaining an advantage in competition. Although the existing forging manufacturing technology has met the needs of the aerospace field to a certain extent, there are still some key limitations. Traditional forging methods mostly use hot forging or cold forging processes. During the hot forging process, the material is plastically deformed at high temperature. This high-temperature operation may cause coarse grains inside the material, generate defects such as inclusions and pores, and these defects are easy to cause the forging to break under high load. In addition, the traditional forging process has certain limitations for the manufacture of forgings with complex shapes. The process parameters are difficult to control and have high requirements on workers' skills. It is easily affected by human operation, thus affecting the overall quality of the forgings.

[0003] During the use of the forging manufacturing device, since the temperature of the aerospace forgings is high when forging is completed, the aerospace forgings need to be automatically pushed to the inspection site, otherwise the heat emitted by the aerospace forgings will scald the workers. In addition, the aerospace forgings also need to be inspected automatically. If the aerospace forgings are inspected manually, not only will errors occur but also the inspection quality will be affected. Summary of the invention

[0004] The disclosed embodiments relate to an aerospace forging manufacturing device with defect detection and a process thereof. When the forging of the aerospace forging is completed, the push plate will automatically push the aerospace forging to the detection position, and the limit plate will block and position the aerospace forging at this position. At this time, the detection ring and the detection sensor are moved up and down by an electric cylinder. The detection ring is mounted on the aerospace forging. The detection sensor moves up and down to automatically detect the aerospace forging. At this time, the detection sensor detects defects on the aerospace forging. The detection sensor can provide high-precision measurement data and can detect tiny defects and irregularities to ensure that the quality of the forging meets strict aerospace standards. Timely detection of aerospace forgings can timely discover quality problems and prevent unqualified products from flowing into downstream processing or assembly links, thereby reducing rework costs and time.

[0005] In a first aspect of the present disclosure, an aerospace forging manufacturing device with defect detection and a process thereof are provided, which specifically include: a workbench; a fixing groove is provided at the front end of the top of the workbench, and two threaded holes are provided on both sides of the fixing groove; two rectangular grooves are provided at the rear end of the top of the workbench, and two threaded grooves are provided at the outer ends of the rectangular grooves; grooves are provided at both ends of the workbench; mutually symmetrical frame grooves are provided at the top of the workbench, and two threaded grooves are provided at the outer ends of the frame grooves; an arc-shaped limiting plate is fixedly installed at the rear end of the workbench; A fixing seat is fixedly installed at the fixing groove at the front end of the workbench, and a groove is provided at the upper end of the fixing seat; a fixing frame is fixedly installed at the frame groove of the workbench, and a through slot hole is provided in the middle of the upper end of the fixing frame; symmetrical anti-drop holes are provided at the lower ends of both ends of the fixing frame; a through round hole is provided at the lower end of the fixing frame; bases are fixedly installed at the grooves at both ends of the workbench, and a groove is provided at the upper end of the base; The top of the workbench is fixedly installed with symmetrical fixed vertical plates, and the upper ends of the fixed vertical plates are provided with through shaft holes; through rotating shafts are rotatably inserted in the shaft holes of the two fixed vertical plates, and a baffle plate is sleeved in the middle of the rotating shaft, and positioning plates are fixedly installed at the lower ends of the inner side walls of the two fixed vertical plates respectively, and fixed frames are fixedly installed at the two rectangular grooves at the rear end of the workbench, and a groove is provided in the middle of the top of the fixed frame; the upper end of the fixed frame is provided with symmetrical limiting holes; Side plates are fixedly installed at the lower ends of both ends of the fixing frame, and through bolts are rotatably inserted at both ends of the side plates; an electric cylinder is fixedly installed in the groove in the middle of the fixing frame, and a connecting plate is fixedly installed on the upper end of the electric cylinder; symmetrical limiting rods are fixedly installed at the bottom of the connecting plate, and detection circles are fixedly installed at the lower ends of the two limiting rods; detection sensors are evenly installed on the inner wall of the detection circle.

[0006] In at least some embodiments, a stabilizing block is fixedly mounted on the rear end of the upper end of the fixing seat, and four penetrating screws are rotatably inserted on the stabilizing block, and penetrating guide plate holes are respectively opened at both ends of the stabilizing block.

[0007] In at least some embodiments, an electric push rod is fixedly mounted in the groove of the fixing seat, an arc-shaped push plate is fixedly mounted at the rear end of the electric push rod, and mutually parallel guide strips are fixedly mounted on the push plate.

[0008] In at least some embodiments, four corners of the upper end of the fixed frame are respectively provided with penetrating guide holes, the lower ends of the two side walls of the fixed frame are respectively fixedly installed with stabilizing plates, and two ends of the stabilizing plates are respectively rotatably inserted with two penetrating bolts, and the two ends of the inner side walls of the fixed frame are respectively provided with mutually parallel sliding grooves.

[0009] In at least some embodiments, a hydraulic cylinder is fixedly installed at the slot hole at the upper end of the fixed frame, a supporting plate is fixedly installed at the lower end of the hydraulic cylinder, and three through-column holes are opened on the supporting plate, and vertically upward guide rods are fixedly installed at the four corners of the supporting plate.

[0010] In at least some embodiments, sliding blocks symmetrical to each other are fixedly mounted on both side walls of the bearing plate, a hammer block is fixedly mounted on the lower end of the hydraulic cylinder, and three connecting columns are fixedly mounted on the hammer block.

[0011] In at least some embodiments, electric rods are fixedly installed in the grooves of the two bases, and clamping blocks are fixedly installed at opposite ends of the two electric rods, and symmetrical anti-drop rods are fixedly installed at the back ends of the two clamping blocks.

[0012] In at least some embodiments, mutually symmetrical slots are provided on the left side wall of the clamping block at the right end, and mutually symmetrical inserting blocks are fixedly mounted on the right side wall of the clamping block at the left end.

[0013] The invention discloses a production process of reinforced rosin glue based on an impregnation matrix, comprising the following steps: firstly, an electric push rod is used to move a push plate backward, and an aerospace forging is pushed backward by an inner concave surface of the push plate, and the aerospace forging is pushed to the position directly below a fixed frame; then two electric rods are used to push two clamping blocks in opposite directions, and two clamping blocks are used to temporarily fix and clamp the two ends of the aerospace forging; then a hydraulic cylinder is used to frequently move a hammering block up and down, and the hammering block is used to frequently hammer the aerospace forging below for forging; then, an electric push rod is used to move the push plate backward again, and the forged aerospace forging is pushed further backward, and the aerospace forging is pushed to the inner concave surface of a limit plate; finally, an electric cylinder is used to pull a connecting plate downward, and a detection circle will also move downward at this time, and a detection sensor is used to detect defects on the aerospace forging.

[0014] The present invention provides an aerospace forging manufacturing device with defect detection and a process thereof, which has the following beneficial effects: When the forging of aerospace forgings is completed, the push plate will automatically push the aerospace forgings to the inspection position, and the limit plate will block and position the aerospace forgings at this position. At this time, the electric cylinder is used to move the inspection ring and the inspection sensor up and down. The inspection ring is put on the aerospace forging, and the inspection sensor moves up and down to automatically inspect the aerospace forgings. At this time, the inspection sensor detects defects on the aerospace forgings. The inspection sensor can provide high-precision measurement data and can detect tiny defects and irregularities to ensure that the quality of the forgings meets strict aerospace standards. Timely inspection of aerospace forgings can timely discover quality problems and prevent unqualified products from flowing into downstream processing or assembly links, thereby reducing rework costs and time.

[0015] First, place the aerospace forging on the workbench, use the electric push rod to move the push plate backward, use the concave surface of the push plate to push the aerospace forging backward, push the aerospace forging to the bottom of the fixed frame, and then pull the push plate forward from the fixed frame to move it out. By using the electric push rod to move the aerospace forging, the operational errors that may be caused during manual handling can be reduced. The concave surface design of the push plate can better cover the forging, ensuring that the aerospace forging will not slip or shift during the movement, thereby improving the positioning accuracy.

[0016] Use a hydraulic cylinder to push the hammer block downward, use the hammer block to hammer and forge the aerospace forging below, and then use the hydraulic cylinder to move the hammer block upward. In this way, frequent up and down movements of the hammer block can forge the aerospace forging below. Frequent hammering can transfer more energy to the forging in a short time, thereby speeding up the forging process and improving production efficiency. Hammering can cause metal materials to recrystallize during plastic deformation, reduce defects in the material, and thus improve the density of the forging.

[0017] Use two electric rods to push the two clamping blocks in opposite directions, and use the opposite ends of the two clamping blocks to temporarily fix and clamp the two ends of the aerospace forging, so that the aerospace forging will not move when being hammered and forged. By clamping the two ends of the aerospace forging, the movement of the forging due to external force during the forging process can be effectively avoided, thereby ensuring the accuracy and consistency of the forging. BRIEF DESCRIPTION OF THE DRAWINGS

[0018] In order to more clearly illustrate the technical solution of the embodiment of the present invention, the drawings of the embodiment are briefly introduced below.

[0019] The drawings described below are only related to some embodiments of the present invention, but are not intended to limit the present invention.

[0020] In the attached picture: Figure 1The schematic diagram of the upper left front axial structure of the present application is shown; Figure 2 The schematic diagram of the upper left rear axial view of the present application is shown; Figure 3 A schematic diagram of the structure of the workbench and the fixed seat of the present application is shown; Figure 4 A schematic diagram of the disassembled structure of a fixed seat of the present application is shown; Figure 5 A schematic diagram of the structure of the fixing frame and the base portion of the present application is shown; Figure 6 A schematic diagram of the disassembled structure of the fixing frame and the base part of the present application is shown; Figure 7 A schematic diagram of the partially disassembled structure of the hydraulic cylinder and the electric rod of the present application is shown; Figure 8 A schematic diagram of the disassembled structure of the fixed vertical plate of the present application is shown; Fig. 9 A schematic diagram of a partially disassembled structure of a fixing frame of the present application is shown; Fig.10 A schematic diagram of the explosion structure of the present application is shown.

[0021] Reference numerals list Workbench; 101, limit plate; 2, fixed seat; 201, stabilizing block; 202, guide plate hole; 203, electric push rod; 204, push plate; 205, guide strip plate; 3, fixed frame; 301, guide hole; 302, stabilizing plate; 303, slide groove; 304, hydraulic cylinder; 305, load-bearing plate; 306, guide rod; 307, slider; 308, hammer block; 309, connecting column; 4, base; 401, electric rod; 402, clamping block; 403, anti-slip rod; 404, slot; 405, plug-in block; 5, fixed vertical plate; 501, rotating shaft; 502, baffle plate; 503, positioning plate; 6, fixed frame; 601, limit hole; 602, side plate; 603, electric cylinder; 604, connecting plate; 605, limit rod; 606, detection circle; 607, detection sensor. DETAILED DESCRIPTION

[0022] In order to make the purpose, technical solution and advantages of the embodiment of the present invention clearer, the technical solution of the embodiment of the present invention will be clearly and completely described below in conjunction with the accompanying drawings of the embodiment of the present invention. Obviously, the described embodiment is a part of the embodiment of the present invention, not all of the embodiments. Based on the described embodiment of the present invention, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the present invention.

[0023] Example 1: Please refer to Figures 1 to 10： The present invention proposes an aerospace forging manufacturing device with defect detection and a process thereof, comprising: a workbench 1; a fixing groove is provided at the front end of the top of the workbench 1, and two threaded holes are provided on both sides of the fixing groove; two rectangular grooves are provided at the rear end of the top of the workbench 1, and two threaded grooves are provided at the outer ends of the rectangular grooves; grooves are provided at both ends of the workbench 1; mutually symmetrical frame grooves are provided at the top of the workbench 1, and two screw grooves are provided at the outer ends of the frame grooves; an arc-shaped limiting plate 101 is fixedly installed at the rear end of the workbench 1; an electric push rod 203 is used to move the pushing plate 204 backwards, and the forged aerospace forging is continued to be pushed backwards, and the aerospace forging is pushed to the inner concave surface of the limiting plate 101, at which time the aerospace forging The workpiece will stop moving when it is blocked by the limit plate 101, so that the detection ring 606 can be moved up and down to be put on the aerospace forging for detection. A fixed seat 2 is fixedly installed at the fixed groove at the front end of the workbench 1, and a groove is provided at the upper end of the fixed seat 2; a fixed frame 3 is fixedly installed at the frame groove of the workbench 1, and a through slot is provided in the middle of the upper end of the fixed frame 3; symmetrical anti-drop holes are provided at the lower ends of both ends of the fixed frame 3; a through circular hole is provided at the lower end of the fixed frame 3; a base 4 is fixedly installed at the grooves at both ends of the workbench 1, and a groove is provided at the upper end of the base 4; symmetrical fixed vertical plates 5 are fixedly installed at the top of the workbench 1, and a through axial hole is provided at the upper end of the fixed vertical plates 5; two at the rear end of the workbench 1 A fixing frame 6 is fixedly installed at the rectangular groove, and a groove is provided in the middle of the top of the fixing frame 6; symmetrical limiting holes 601 are provided at the upper end of the fixing frame 6; side panels 602 are fixedly installed at the lower ends of both ends of the fixing frame 6, and through bolts are rotatably inserted at both ends of the side panels 602; the bolts on the side panels 602 are rotatably inserted into the threaded grooves of the workbench 1 to fix and limit the side panels 602 and the fixing frame 6, so that the fixing frame 6 will not move or tilt when touched, so that the fixing frame 6 can stably carry the electric cylinder 603, and the electric cylinder 603 is fixedly installed at the groove in the middle of the fixing frame 6, and the upper end of the electric cylinder 603 is fixedly installed with a connecting plate 604; the connecting plate 604 is pulled downward by the electric cylinder 603 The connecting plate 604 is connected. At this time, the limiting rods 605 at both ends of the connecting plate 604 will pull the detection ring 606 downward, and the detection ring 606 is sleeved on the aerospace forging and moved up and down. The detection sensor 607 on the inner wall of the detection ring 606 is used to detect the defects on the aerospace forging. The bottom of the connecting plate 604 is fixedly installed with mutually symmetrical limiting rods 605, and the limiting rods 605 slide through the limiting hole 601. When the detection ring 606 slides up and down, the limiting rods 605 are restricted by the limiting hole 601, and the detection ring 606 can only slide up and down to prevent the detection ring 606 from tilting when sliding up and down. The detection sensor 607 cannot stably detect the aerospace forging, and the lower ends of the two limiting rods 605 are fixedly installed with the detection ring 606;During the forging process of aerospace forgings, impurities will be scattered everywhere. The baffle plate 502 will block the aerospace forgings to prevent the impurities on the aerospace forgings from falling on the detection circle 606. The inner wall of the detection circle 606 is evenly installed with detection sensors 607. The detection sensors 607 can provide high-precision measurement data and can detect tiny defects and irregularities. ;

[0024] Among them, a stabilizing block 201 is fixedly installed at the rear end of the upper end of the fixing seat 2, and four penetrating screws are rotatably inserted on the stabilizing block 201. The screws on the stabilizing block 201 are rotatably inserted into the threaded holes of the workbench 1 to restrict the stabilizing block 201 and the fixing seat 2. When the stabilizing block 201 or the fixing seat 2 is touched, it will not move. In this way, the fixing seat 2 can stably carry the electric push rod 203. Penetrating guide plate holes 202 are respectively opened at both ends of the stabilizing block 201. The electric push rod 203 is fixedly installed in the groove of the fixing seat 2. First, place the aerospace forging on the workbench 1, and use the electric push rod 203 to move the push plate 204 backward. The concave surface of the push plate 204 is used to push the aerospace forging backward to the position directly below the fixed frame 3, and then the push plate 204 is pulled forward and moved out from the fixed frame 3. An arc-shaped push plate 204 is fixedly installed at the rear end of the electric push rod 203, and mutually parallel guide strips 205 are fixedly installed on the push plate 204. The guide strips 205 slide through the guide plate holes 202. When the push plate 204 slides back and forth, the guide strips 205 are restricted by the guide plate holes 202, and the push plate 204 can only slide back and forth to prevent the detection circle 606 from tilting when sliding back and forth, and the push plate 204 cannot smoothly push the aerospace forging.

[0025] The four corners of the upper end of the fixed frame 3 are respectively provided with penetrating guide holes 301, and the lower ends of the two side walls of the fixed frame 3 are respectively fixedly installed with stabilizing plates 302, and two through bolts are respectively inserted and rotated at both ends of the stabilizing plates 302. The bolts on the stabilizing plates 302 are inserted and rotated in the screw grooves of the workbench 1 to restrict the stabilizing plates 302 and the fixed frame 3. When the fixed frame 3 is touched, it will not move or tilt, so that the fixed frame 3 can stably carry the hydraulic cylinder 304, and the hydraulic cylinder 304 is used to push the hammer block downward. 308, the hammer block 308 is used to hammer and forge the aerospace forging below, and then the hammer block 308 is moved upward by the hydraulic cylinder 304. In this way, the hammer block 308 can be frequently moved up and down to forge the aerospace forging below. The two ends of the inner wall of the fixed frame 3 are respectively provided with mutually parallel slide grooves 303, and the slot hole at the upper end of the fixed frame 3 is fixedly installed with a penetrating hydraulic cylinder 304, and the lower end of the hydraulic cylinder 304 is fixedly installed with a bearing plate 305, and the bearing plate 305 is provided with three penetrating column holes, and the bearing plate 305 is provided with a plurality of penetrating column holes. 5 are respectively fixedly installed with vertically upward guide rods 306, and the guide rods 306 slide through the guide holes 301. When the bearing plate 305 slides up and down, the guide rods 306 are restricted by the guide holes 301, and the bearing plate 305 can only slide up and down, so as to prevent the bearing plate 305 from tilting when sliding up and down, and the hammering block 308 will also tilt, and the hammering block 308 will not be able to fall smoothly on the aerospace forging. The two side walls of the bearing plate 305 are respectively fixedly installed with mutually symmetrical sliders 307. 7 is slidably installed in the slide groove 303. When the bearing plate 305 slides up and down, the slider 307 is restricted by the slide groove 303, and the bearing plate 305 does not tilt when sliding up and down. A hammer block 308 is fixedly installed at the lower end of the hydraulic cylinder 304, and three connecting columns 309 are fixedly installed on the hammer block 308. The three connecting columns 309 are respectively inserted into the three column holes of the bearing plate 305, and then the upper ends of the connecting columns 309 are fixedly welded to the bearing plate 305, so that the hammer block 308 is fixedly connected to the bearing plate 305.

[0026] Among them, electric rods 401 are fixedly installed at the grooves of the two bases 4, and the electric rods 401 penetrate the circular holes at the lower end of the fixed frame 3, and the opposite ends of the two electric rods 401 are fixedly installed with clamping blocks 402, and the two electric rods 401 are used to push the two clamping blocks 402 in opposite directions, and the two ends of the aerospace forgings are temporarily fixed and clamped by the opposite ends of the two clamping blocks 402, so that the aerospace forgings will not move when being hammered and forged, and the two ends of the two clamping blocks 402 facing away from each other are fixedly installed with mutually symmetrical anti-slip rods 403, and the anti-slip rods 403 slides through the anti-drop hole of the fixed frame 3. When the clamping block 402 slides left and right, the anti-drop rod 403 is restricted by the anti-drop hole of the fixed frame 3, and the clamping block 402 can only slide left and right to prevent the clamping block 402 from tilting when sliding left and right. The two clamping blocks 402 cannot stably clamp the aerospace forgings. Mutually symmetrical slots 404 are provided on the left side wall of the right-end clamping block 402, and mutually symmetrical plug-in blocks 405 are fixedly installed on the right side wall of the left-end clamping block 402. When the two clamping blocks 402 are docked, the plug-in block 405 will be inserted into the slot 404.

[0027] Among them, a rotating shaft 501 is rotatably inserted in the axial holes of the two fixed vertical plates 5, and a baffle plate 502 is mounted in the middle of the rotating shaft 501. When the aerospace forging moves backward, it touches the baffle plate 502. At this time, the aerospace forging will push the baffle plate 502 backward to make the baffle plate 502 flip backward, and then pull the push plate 204 forward to reset it. The lower ends of the inner walls of the two fixed vertical plates 5 are respectively fixed with positioning plates 503. The baffle plate 502 is attached to the side walls of the two positioning plates 503. There is a gap between the bottom of the baffle plate 502 and the top of the workbench 1, and the push plate 204 can move back and forth from the bottom of the baffle plate 502.

[0028] Embodiment 2, based on embodiment 1, as Figure 1 and Fig.10 As shown, the lower ends of the two side walls of the fixed frame 3 are respectively fixedly installed with stabilizing plates 302, and two ends of the stabilizing plates 302 are respectively rotatably inserted with two penetrating bolts. The stabilizing plates 302 and the bolts are removed, and then the fixed frame 3 is fixedly welded on the workbench 1 to stabilize the fixed frame 3. In this way, the fixed frame 3 will not move when touched, which avoids the bolts from loosening and failing to stabilize the fixed frame 3 due to long-term use, and also saves the cost of parts.

[0029] The working principle of this embodiment is as follows: first, place the aerospace forging on the workbench 1, use the electric push rod 203 to move the push plate 204 backward, use the inner concave surface of the push plate 204 to push the aerospace forging backward, push the aerospace forging to the position directly below the fixed frame 3, and then pull the push plate 204 forward from the fixed frame 3 to move it out, and then use two electric rods 401 to push the two clamping blocks 402 in opposite directions, and use the opposite ends of the two clamping blocks 402 to temporarily fix and clamp the two ends of the aerospace forging, so that the aerospace forging will not move when it is hammered and forged, and then use the hydraulic cylinder 304 to push the hammering block 308 downward, use the hammering block 308 to hammer and forge the aerospace forging below, and then use the hydraulic cylinder 304 to move the hammering block 308 upward, so that the hammering block 308 can be frequently moved up and down to forge the aerospace forging below. When the forging of the aerospace forging is completed, the two clamping blocks 402 are moved back to back to release the clamped aerospace forging, and then the electric push rod 203 is used to move the push plate 204 backward. The push plate 204 continues to push the forged aerospace forging backward. At this time, the aerospace forging will push the baffle plate 502 backward to flip the baffle plate 502 backward. Then the push plate 204 is pulled forward to reset and the aerospace forging is pushed to the inner concave surface of the limit plate 101. At this time, the aerospace forging is blocked by the limit plate 101 and stops moving. Then the electric cylinder 603 is used to pull the connecting plate 604 downward. At this time, the limiting rods 605 at both ends of the connecting plate 604 will pull the detection ring 606 downward, and the detection ring 606 is put on the aerospace forging and moves up and down. The detection sensor 607 on the inner wall of the detection ring 606 is used to detect defects on the aerospace forging.

[0030] In this article, there are a few points to note: 1. The drawings of the embodiments of the present disclosure only involve structures related to the embodiments of the present disclosure, and other structures may refer to general designs.

[0031] 2. In the absence of conflict, the embodiments of the present disclosure and the features therein may be combined with each other to obtain new embodiments.

[0032] The above are only specific embodiments of the present disclosure, but the protection scope of the present disclosure is not limited thereto. Any technician familiar with the technical field can easily think of changes or substitutions within the technical scope disclosed in the present disclosure, which should be included in the protection scope of the present disclosure. Therefore, the protection scope of the present disclosure should be based on the protection scope of the claims.

Claims

1. An aerospace forging manufacturing device with defect detection, comprising: A workbench (1); a fixing groove is provided at the front end of the top of the workbench (1), and two threaded holes are provided on both sides of the fixing groove; two rectangular grooves are provided at the rear end of the top of the workbench (1), and two threaded grooves are provided at the outer ends of the rectangular grooves; grooves are provided at both ends of the workbench (1); a mutually symmetrical frame groove is provided at the top of the workbench (1), and two screw grooves are provided at the outer ends of the frame groove; an arc-shaped limiting plate (101) is fixedly installed at the rear end of the workbench (1); a fixing seat (2) is fixedly installed at the fixing groove at the front end of the workbench (1), and a groove is provided at the upper end of the fixing seat (2); a fixing frame (3) is fixedly installed at the frame groove of the workbench (1), and a through slot hole is provided in the middle of the upper end of the fixing frame (3); symmetrical anti-drop holes are provided at the lower ends of the two ends of the fixing frame (3); a through circular hole is provided at the lower end of the fixing frame (3); a base (4) is fixedly installed at the grooves at both ends of the workbench (1), and the base (4) A groove is provided at the upper end; the top of the workbench (1) is fixedly mounted with mutually symmetrical fixed vertical plates (5), and the upper end of the fixed vertical plates (5) is provided with a through axial hole; it is characterized in that a fixing frame (6) is fixedly mounted at two rectangular grooves at the rear end of the workbench (1), and a groove is provided at the middle of the top of the fixing frame (6); the upper end of the fixing frame (6) is provided with mutually symmetrical limiting holes (601); the lower ends of the two ends of the fixing frame (6) are respectively fixedly mounted with side plates (602), and the side plates (603) are respectively fixedly mounted with side plates (604). Bolts are rotatably inserted through the two ends of the side plate (602); an electric cylinder (603) is fixedly installed in the groove in the middle of the fixing frame (6), and a connecting plate (604) is fixedly installed on the upper end of the electric cylinder (603); symmetrical limiting rods (605) are fixedly installed on the bottom of the connecting plate (604), and detection rings (606) are fixedly installed on the lower ends of the two limiting rods (605); detection sensors (607) are evenly installed on the inner side wall of the detection ring (606).

2. The aerospace forging manufacturing device with defect detection according to claim 1, characterized in that: A stabilizing block (201) is fixedly mounted at the rear end of the upper end of the fixing seat (2), and four through-going screw rods are rotatably inserted into the stabilizing block (201), and through-going guide plate holes (202) are respectively provided at both ends of the stabilizing block (201).

3. The aerospace forging manufacturing device with defect detection according to claim 1, characterized in that: An electric push rod (203) is fixedly mounted in the groove of the fixing seat (2), an arc-shaped push plate (204) is fixedly mounted at the rear end of the electric push rod (203), and mutually parallel guide strips (205) are fixedly mounted on the push plate (204).

4. The aerospace forging manufacturing device with defect detection according to claim 1, characterized in that: The four corners of the upper end of the fixing frame (3) are respectively provided with penetrating guide holes (301); the lower ends of the two side walls of the fixing frame (3) are respectively fixedly mounted with stabilizing plates (302); two ends of the stabilizing plates (302) are respectively rotatably inserted with two penetrating bolts; and the two ends of the inner side wall of the fixing frame (3) are respectively provided with mutually parallel sliding grooves (303).

5. The aerospace forging manufacturing device with defect detection according to claim 1, characterized in that: A hydraulic cylinder (304) is fixedly mounted on the slot at the upper end of the fixed frame (3), a bearing plate (305) is fixedly mounted on the lower end of the hydraulic cylinder (304), and three through-holes are formed on the bearing plate (305), and vertically upward guide rods (306) are fixedly mounted on the four corners of the bearing plate (305).

6. The aerospace forging manufacturing device with defect detection according to claim 5, characterized in that: Mutually symmetrical sliding blocks (307) are fixedly mounted on both side walls of the bearing plate (305), a hammering block (308) is fixedly mounted on the lower end of the hydraulic cylinder (304), and three connecting columns (309) are fixedly mounted on the hammering block (308).

7. The aerospace forging manufacturing device with defect detection according to claim 1, characterized in that: An electric rod (401) is fixedly mounted at the grooves of the two bases (4), and a clamping block (402) is fixedly mounted at the opposite ends of the two electric rods (401), and mutually symmetrical anti-dropping rods (403) are fixedly mounted at the opposite ends of the two clamping blocks (402).

8. The aerospace forging manufacturing device with defect detection according to claim 7, characterized in that: The left side wall of the clamping block (402) at the right end is provided with mutually symmetrical slots (404), and the right side wall of the clamping block (402) at the left end is fixedly provided with mutually symmetrical inserting blocks (405).

9. The aerospace forging manufacturing device with defect detection according to claim 1, characterized in that: A rotating shaft (501) is rotatably inserted into the shaft holes of the two fixed vertical plates (5), and a blocking plate (502) is sleeved in the middle of the rotating shaft (501). Positioning plates (503) are respectively fixedly mounted on the lower ends of the inner side walls of the two fixed vertical plates (5).

10. A process for manufacturing aerospace forgings with defect detection according to claim 5, characterized in that: The following steps are involved: 1) First, use the electric push rod (203) to move the push plate (204) backward, and use the inner concave surface of the push plate (204) to push the aerospace forging backward, and push the aerospace forging to the position directly below the fixed frame (3); 2) Then, two electric rods (401) are used to push two clamping blocks (402) in opposite directions, and two clamping blocks (402) are used to temporarily fix and clamp the two ends of the aerospace forging; 3) Then, the hydraulic cylinder (304) is used to frequently move the hammer block (308) up and down, and the hammer block (308) is used to frequently hammer the aerospace forging below for forging; 4) Then, the push plate (204) is moved backward by the electric push rod (203) to continue to push the forged aerospace forging backward to the inner concave surface of the limit plate (101); 5) Finally, the connecting plate (604) is pulled downward by the electric cylinder (603), and the detection circle (606) is also moved downward, and the defects on the aerospace forging are detected by the detection sensor (607).

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