Fixing device for aircraft wall panel maintenance and processing

Abstract

The present invention relates to the technical field of fixing tooling, and specifically to a fixing device for aircraft wall panel maintenance and processing, comprising a supporting component, a movable component provided for internal rotation of the supporting component, a longitudinal positioning component provided for internal rotation of the movable component, and a driving component provided at the right end of the supporting component. The aircraft wall panel is longitudinally positioned by the longitudinal positioning component to suppress longitudinal movement of the aircraft wall panel, and the front and rear sliding supporting wheels and pressure wheels can adjust the distance between the front and rear pressure wheels and the front and rear supporting wheels to cope with aircraft wall panels of different widths, and the longitudinal positioning component can act on the aircraft wall panel to move left or right, so that while the aircraft wall panel is longitudinally positioned, the left and right position of the aircraft wall panel can be adjusted, which facilitates adjustment of the position of the maintenance area on the aircraft wall panel and has high flexibility.

Description

Technical Field

[0001] The invention relates to the technical field of fixing tooling, in particular to a fixing device for repairing and processing aircraft wall panels. Background Art

[0002] Aircraft wall panels refer to composite wall panels composed of skins, long stringers and wing spar caps. The skins are usually connected to the long stringers and wing spar caps by riveting. According to their appearance, the skins can be divided into single-curvature skins, double-curvature skins and complex-shaped skins. Single-curvature skins have curvature in only one direction and are mostly used in the fuselage and wings of aircraft.

[0003] According to a Chinese patent application with publication number CN117415650A, a fixture for processing aircraft wall panels is disclosed. The fixture can locally support the drilled area of ​​the skin when drilling in the open middle part of the skin, thereby reducing the problem of impact deformation caused by the drilled area being suspended in the air. However, the above-mentioned fixture still has the technical problem of low flexibility, and it is not convenient to adjust the processing position of the aircraft wall panel. Therefore, we propose a fixture for aircraft wall panel maintenance and processing to solve the above-mentioned technical problems. Summary of the Invention

[0004] The present invention provides the following technical solutions: a fixing device for aircraft panel repair and processing, comprising a supporting component;

[0005] A movable component is provided inside the support component for rotating and is used for adjusting the angle of the aircraft wall panel;

[0006] A longitudinal positioning component is provided inside the movable component for rotation, and the longitudinal positioning component is used for lateral adjustment of the aircraft wall panel;

[0007] A driving component is provided at the right end of the supporting component, and the driving component is used for inputting power to the movable component;

[0008] A transverse positioning component is provided inside the movable component, and the transverse positioning component is used for supporting the aircraft wall panel.

[0009] As a preferred solution of the present invention, the supporting component includes a machine tripod, and three positioning pins are fixedly installed on the adjacent side surfaces of the machine tripod, and the outer walls of the positioning pins are rotatably mounted with an I-shaped wheel.

[0010] As a preferred solution of the present invention, the movable component includes two end plates distributed on the left and right, four square tubes are fixedly installed between the two end plates, the four square tubes are divided into two layers, and each layer has two front and back layers. Two sliding sleeves distributed on the left and right are slidably installed on the outer walls of the square tubes, wherein a connecting plate is fixedly installed between the upper and lower sliding sleeves, and the front and right parts of the left and right end plates are fixedly installed with force pile seats, the force pile seats in the left and right directions are staggered up and down, and the side surfaces of the left and right force pile seats that are close to each other are fixedly installed with servo cylinders through brackets, and the output rod ends of the left and right servo cylinders are respectively connected to the left and right sliding sleeves through brackets.

[0011] As a preferred solution of the present invention, a clearance opening is opened between the two end plates, and guide rings are fixedly installed on the side surfaces of the left and right end plates that are away from each other. The guide rings are located outside the clearance opening and are movably stuck inside the three work-shaped wheels.

[0012] The cam is secured to the chassis and has two camshafts that are connected to the chassis to release the brake, and the cam is secured to the chassis by a spring that is secured to the chassis.

[0013] As a preferred solution of the present invention, a motor fixing seat is fixedly installed on the lower part of the side surface close to the two connecting plates located at the front, a servo motor is fixedly installed on the front of the motor fixing seat, a driving pulley is fixedly installed on the output shaft of the servo motor, a driven pulley is fixedly installed on the front part of the central axis of the roller, and a power belt is commonly connected between the driven pulley and the driving pulley.

[0014] As a preferred solution of the present invention, a first torque limiting groove is provided on the outer wall of the roller, and a first positioning hoop is fixedly installed on a side surface away from the front and rear rollers, and a first fastening bolt is threadedly connected to the outer wall of the first positioning hoop, and an end of the first fastening bolt abuts against the bottom wall of the first torque limiting groove. A second torque limiting groove is provided on the outer wall of the pressure roller, and a second positioning hoop is fixedly installed on a side surface away from the front and rear rollers, and a second fastening bolt is threadedly connected to the outer wall of the second positioning hoop, and an end of the second fastening bolt abuts against the bottom wall of the second torque limiting groove.

[0015] As a preferred solution of the present invention, the driving component includes an AC motor fixedly mounted on the lower right end of the machine tripod, a driving gear is fixedly mounted on the output shaft of the AC motor, and a driven gear ring is fixedly mounted on the right side of one of the guide rings located on the right, the driven gear ring is located on the top of the driving gear, and the driven gear ring and the driving gear are engaged with each other.

[0016] As a preferred solution of the present invention, the transverse positioning component includes two linear guide rails fixedly installed on the opposite surfaces of the left and right end plates, and two linear sliders distributed front and back are slidably installed on the outer walls of the left and right linear guide rails, wherein a transverse positioning plate is fixedly installed between the two linear sliders in the left and right directions, and the number of the transverse positioning plates is two, and the side surfaces of the two transverse positioning plates that are close to each other are penetrated by multiple mounting grooves distributed equidistantly on the left and right, and top wheels are rotatably installed inside the transverse positioning plates.

[0017] As a preferred solution of the present invention, a follower sleeve is fixedly installed on the side of the first positioning ring hoop away from the supporting roller. The follower sleeve is slidably located on the periphery of the supporting roller, and an annular groove is provided on the outer wall of the follower sleeve. The bottom of the horizontal positioning plate is movably clamped in the inside of the annular groove.

[0018] Compared with the prior art, the present invention has the following beneficial effects:

[0019] 1. In the present invention, the aircraft panel is longitudinally positioned by a longitudinal positioning component to suppress the longitudinal movement of the aircraft panel, and the distance between the front and rear pressure rollers and the front and rear pressure rollers can be adjusted by sliding the supporting rollers and the pressure rollers forward and backward to cope with the use of aircraft panels of different widths. By controlling the output rods of the left and right servo cylinders to extend and retract in opposite directions, the distance between the left and right connecting plates is adjusted. The left and right connecting plates are further used to adjust the distance between the supporting rollers and the pressure rollers in the left and right directions, that is, the distance between the left and right supporting rollers and the pressure rollers is adjusted, so as to facilitate the vertical positioning of aircraft panels of different lengths. The output shaft of the servo motor drives the active pulley to rotate, and further drives the driven pulley and the supporting roller to rotate under the connection of the power belt. The rotation of the supporting roller further drives the supporting roller to rotate. The torque of the supporting roller rotation directly causes the aircraft panel to move left or right, so that while the aircraft panel is longitudinally positioned, the left and right position of the aircraft panel can be adjusted, which facilitates the adjustment of the position of the maintenance area on the aircraft panel and has strong flexibility.

[0020] 2. In the present invention, the first positioning ring hoop drives the follower sleeve to move together with the annular groove. Due to the clamping effect of the annular groove and the bottom of the transverse positioning plate, the annular groove drives the transverse positioning plate to move during the axial movement along the roller. The transverse positioning plate can further ensure the stability of the movement of the transverse positioning plate through the guiding effect of the two linear sliders and two linear guide rails at both ends. The movement of the transverse positioning plate drives the multiple top wheels to move together through the multiple mounting grooves until the outer walls of the multiple top wheels on the front and rear transverse positioning plates respectively abut the front and rear inner walls of the aircraft wall panel, thereby providing a transverse positioning effect for the aircraft wall panel and preventing the aircraft wall panel from moving laterally. At the same time, since the positions of the front and rear transverse positioning plates can be adjusted front and back in this device, it can be used to perform front and back positioning on aircraft wall panels of different widths, and has a wide range of uses.

[0021] 3. In the present invention, the output shaft of the AC motor drives the driving gear to rotate, and the rotation of the driving gear further drives the guide ring to rotate through the driven gear ring meshing with it, so that the movable part and the longitudinal positioning part rotate as a whole, thereby adjusting the angle of the aircraft wall panel to facilitate maintenance and processing of the side of the aircraft wall panel. BRIEF DESCRIPTION OF THE DRAWINGS

[0022] Figure 1 It is a schematic diagram of the structure of the present invention;

[0023] Figure 2 Schematic diagram of the structure of the supporting component in the present invention;

[0024] Figure 3 It is a structural schematic diagram of the movable parts in the present invention;

[0025] Figure 4 Schematic diagram of the planar structure of the movable parts in the present invention;

[0026] Figure 5 For the present invention Figure 3 Schematic diagram of the local structure;

[0027] Figure 6 For the present invention Figure 5 Schematic diagram of the local structure;

[0028] Figure 7 For the present invention Figure 6 A schematic diagram of the enlarged structure of part A;

[0029] Figure 8 It is a structural schematic diagram of the longitudinal positioning component in the present invention;

[0030] Figure 9 For the present invention Figure 8 Schematic diagram of the enlarged structure of part B;

[0031] Figure 10 It is a schematic diagram of the local structure of the roller in the present invention.

[0032] In the figure: 100, supporting component; 101, machine foot frame; 102, positioning shaft pin; 103, work wheel; 200, movable component; 201, end plate; 202, square tube; 203, sliding sleeve; 204, connecting plate; 205, load-bearing pile seat; 206, servo cylinder; 207, clearance port; 208, guide ring; 300, longitudinal positioning component; 301, roller; 302, supporting roller; 303, slide groove; 304, pressure roller; 305, pressure roller; 306, spring bracket; 307, insertion rod; 308, sliding seat; 309, tensioning spring; 3010, motor fixing seat; 3011, servo motor ; 3012, driving pulley; 3013, driven pulley; 3014, power belt; 3001, first torque limiting groove; 3002, first positioning hoop; 30021, first fastening bolt; 3004, second torque limiting groove; 3005, second positioning hoop; 30051, second fastening bolt; 400, driving component; 401, AC motor; 402, driving gear; 403, driven gear ring; 500, horizontal positioning component; 501, linear guide rail; 502, linear slider; 503, horizontal positioning plate; 504, placement groove; 505, top wheel; 506, follower sleeve; 507, ring groove. DETAILED DESCRIPTION

[0033] The following will clearly and completely describe the technical solutions in the embodiments of the present invention in conjunction with the accompanying drawings. Obviously, the described embodiments are only part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without making creative efforts are within the scope of protection of the present invention.

[0034] See also Figures 1-10 The technical solution provided by the present invention specifically includes the following embodiments:

[0035] Embodiment 1: A fixing device for aircraft panel repair and processing, comprising a support component 100, a movable component 200 being provided for rotation inside the support component 100, a longitudinal positioning component 300 being provided for rotation inside the movable component 200, and a driving component 400 being provided at the right end of the support component 100;

[0036] The supporting component 100 includes a machine stand 101. Three positioning pins 102 are fixedly installed on the adjacent side surfaces of the machine stand 101. The outer walls of the positioning pins 102 are rotatably mounted with a work wheel 103.

[0037] The movable component 200 includes two end plates 201 distributed on the left and right, and four square tubes 202 are fixedly installed between the two end plates 201. The four square tubes 202 are divided into two layers, one upper layer and the other lower layer, and each layer has two front and rear layers. Two sliding sleeves 203 distributed on the left and right are slidably installed on the outer walls of the square tubes 202, wherein a connecting plate 204 is fixedly installed between the upper and lower sliding sleeves 203. The front and right parts of the left and right end plates 201 are fixedly installed with force pile seats 205. The force pile seats 205 in the left and right directions are staggered in an up-and-down arrangement, and the side surfaces of the left and right force pile seats 205 that are close to each other are fixedly installed with servo cylinders 206 through brackets. The output rod ends of the left and right servo cylinders 206 are respectively connected to the left and right sliding sleeves 203 through brackets.

[0038] A clearance opening 207 is formed between the two end plates 201. A guide ring 208 is fixedly mounted on the side of the left and right end plates 201 that is away from each other. The guide ring 208 is located outside the clearance opening 207 and is movably locked inside the three work-shaped wheels 103.

[0039] The driving component 400 includes an AC motor 401 fixedly mounted on the lower right end of the machine stand 101. A driving gear 402 is fixedly mounted on the output shaft of the AC motor 401. A driven gear ring 403 is fixedly mounted on the right side of a guide ring 208 located on the right side. The driven gear ring 403 is located on top of the driving gear 402 and meshes with the driving gear 402.

[0040] Specifically, in this embodiment, the output shaft of the AC motor 401 drives the driving gear 402 to rotate, and the rotation of the driving gear 402 further drives the guide ring 208 to rotate through the driven gear ring 403 meshing therewith, so that the movable component 200 and the longitudinal positioning component 300 rotate as a whole, thereby adjusting the angle of the aircraft wall panel to facilitate maintenance and processing of the side of the aircraft wall panel.

[0041] Embodiment 2: The longitudinal positioning component 300 includes a roller 301 and a pressure roller 304 that are rotatably located between the front and rear connecting plates 204. The roller 301 is located at the bottom of the pressure roller 304. The outer wall of the roller 301 is provided with two supporting wheels 302 distributed front and back. The outer wall of the pressure roller 304 is provided with two pressure rollers 305 distributed front and back. The roller 301 is rotatably installed between the front and rear connecting plates 204. A slide groove 303 is provided between the front and rear connecting plates 204. The central axis of the pressure roller 304 is slidably installed. Between the front and rear slide grooves 303, spring brackets 306 are rotatably mounted on the front and rear parts of the central axis of the pressure roller 304 through bearings. A plunger 307 is fixedly mounted on the bottom of the spring bracket 306. A sliding seat 308 is fixedly mounted on the side of the connecting plate 204 close to the plunger 307. The plunger 307 slides through the top and bottom of the sliding seat 308. A tensioning spring 309 is sleeved on the outer periphery of the plunger 307. The tensioning spring 309 is fixedly mounted between the bottom wall of the spring bracket 306 and the top of the sliding seat 308.

[0042] A motor mounting base 3010 is fixedly mounted on the lower portion of the adjacent side of the two front connecting plates 204. A servo motor 3011 is fixedly mounted on the front of the motor mounting base 3010. A driving pulley 3012 is fixedly mounted on the output shaft of the servo motor 3011. A driven pulley 3013 is fixedly mounted on the front portion of the central axis of the roller 301. A power belt 3014 is sleeved between the driven pulley 3013 and the driving pulley 3012.

[0043] A first torque-limiting groove 3001 is formed on the outer wall of the supporting roller 301, and a first positioning hoop 3002 is fixedly installed on the side away from the front and rear supporting rollers 302. A first fastening bolt 30021 is threadedly connected to the outer wall of the first positioning hoop 3002, and the end of the first fastening bolt 30021 abuts against the bottom wall of the first torque-limiting groove 3001. A second torque-limiting groove 3004 is formed on the outer wall of the pressure roller 304, and a second positioning hoop 3005 is fixedly installed on the side away from the front and rear pressure rollers 305. A second fastening bolt 30051 is threadedly connected to the outer wall of the second positioning hoop 3005, and the end of the second fastening bolt 30051 abuts against the bottom wall of the second torque-limiting groove 3004.

[0044] Specifically, the present embodiment places the processed aircraft wall panel between the supporting wheel 302 and the pressure wheel 305 through any one of the left and right clearance openings 207, and pulls down the spring bracket 306 through the elastic force of the tensioning spring 309, and further drives the pressure wheel 305 to press down the top of the aircraft wall panel through the pressure roller 304, thereby forming a clamping effect on the aircraft wall panel with the supporting wheel 302, longitudinally positioning the aircraft wall panel, and inhibiting the longitudinal movement of the aircraft wall panel, and by sliding the supporting wheel 302 and the pressure wheel 305 back and forth, the distance between the front and rear pressure wheels 305 and the front and rear supporting wheels 302 can be adjusted to cope with the use of aircraft wall panels of different widths, and after the front and rear positions of the supporting wheel 302 and the pressure wheel 305 are adjusted, the positions of the supporting wheel 302 and the pressure wheel 305 are locked by tightening the first fastening bolt 30021 and the second fastening bolt 30051 respectively, to prevent the supporting wheel 302 or the pressure wheel 305 from being displaced again after adjustment. By controlling the output rods of the left and right servo cylinders 206 to extend and retract in opposite directions, the distance between the left and right connecting plates 204 is adjusted, and the distance between the left and right rollers 301 and the left and right pressure rollers 304 is further adjusted through the left and right connecting plates 204, that is, the distance between the left and right supporting rollers 302 and the left and right pressure rollers 305 is adjusted, so as to facilitate the up and down positioning of aircraft wall panels of different lengths. The output shaft of the servo motor 3011 drives the active pulley 3012 to rotate, and further drives the driven pulley 3013 to rotate together with the roller 301 under the connection action of the power belt 3014. The rotation of the roller 301 further drives the supporting roller 302 to rotate. The torque of the supporting roller 302 will directly cause the aircraft wall panel to move left or right, so that while the aircraft wall panel is longitudinally positioned, the left and right position of the aircraft wall panel can be adjusted, which is convenient for adjusting the position of the maintenance area on the aircraft wall panel and has strong flexibility.

[0045] Embodiment 3: A transverse positioning component 500 is provided inside the movable component 200. The transverse positioning component 500 includes two linear guide rails 501 fixedly mounted on opposite surfaces of the left and right end plates 201. Two linear sliders 502 distributed front and back are slidably mounted on the outer walls of the left and right linear guide rails 501. A transverse positioning plate 503 is fixedly mounted between the two linear sliders 502 in the left and right directions. There are two transverse positioning plates 503. A plurality of placement grooves 504 distributed equidistantly on the left and right sides of the two transverse positioning plates 503 are penetrated and opened. A top wheel 505 is rotatably mounted inside each of the transverse positioning plates 503.

[0046] A follower sleeve 506 is fixedly installed on the side of the first positioning hoop 3002 away from the supporting roller 302. The follower sleeve 506 is slidably located on the periphery of the roller 301, and an annular groove 507 is opened on the outer wall of the follower sleeve 506. A follower sleeve 506 is fixedly installed on the side of the first positioning hoop 3002 away from the supporting roller 302. The follower sleeve 506 is slidably located on the periphery of the roller 301, and an annular groove 507 is opened on the outer wall of the follower sleeve 506. The bottom of the horizontal positioning plate 503 is movably engaged with the inside of the annular groove 507.

[0047] Specifically, in this embodiment, the first positioning ring hoop 3002 drives the follower sleeve 506 to move together with the annular groove 507. Due to the clamping effect of the annular groove 507 and the bottom of the transverse positioning plate 503, the annular groove 507 drives the transverse positioning plate 503 to move during the axial movement along the roller 301. The transverse positioning plate 503 can further ensure the stability of the movement of the transverse positioning plate 503 through the guiding effect of the two linear sliders 502 and the two linear guide rails 501 at both ends. The transverse positioning plate 503 moves through multiple mounting grooves 504 and drives multiple top wheels 505 to move together until the outer walls of the multiple top wheels 505 on the front and rear transverse positioning plates 503 respectively abut against the front and rear inner walls of the aircraft wall panel, thereby providing a transverse positioning effect for the aircraft wall panel and preventing the aircraft wall panel from moving laterally. At the same time, since the positions of the front and rear transverse positioning plates 503 can be adjusted front and back in this device, it can be used to perform front and back positioning on aircraft wall panels of different widths, and has a wide range of applications.

[0048] When the fixing device for repairing and processing aircraft wall panels of the present invention is in operation, the processed aircraft wall panel is placed between the supporting wheel 302 and the pressure wheel 305 through any one of the left and right clearance openings 207. The spring bracket 306 is pulled down by the elastic force of the tensioning spring 309, and the pressure wheel 305 is further driven to press down the top of the aircraft wall panel through the pressure roller 304, thereby forming a clamping effect on the upper and lower sides of the aircraft wall panel with the supporting wheel 302, longitudinally positioning the aircraft wall panel and suppressing the longitudinal movement of the aircraft wall panel. The front and rear sliding supporting wheel 302 and the pressure wheel 305 can adjust the distance between the front and rear pressure wheels 305 and the front and rear supporting wheels 302 to cope with the use of aircraft wall panels of different widths. After the front and rear positions of the supporting wheel 302 and the pressure wheel 305 are adjusted, the positions of the supporting wheel 302 and the pressure wheel 305 are locked by tightening the first fastening bolt 30021 and the second fastening bolt 30051 respectively to prevent the supporting wheel 302 or the pressure wheel 305 from being displaced again after adjustment. The first positioning ring 3002 drives the follower sleeve 506 and the annular groove 507 to move together. Due to the clamping effect of the annular groove 507 and the bottom of the transverse positioning plate 503, the annular groove 507 drives the transverse positioning plate 503 to move along the axial movement of the roller 301. The transverse positioning plate 503 can further ensure the stability of the movement of the transverse positioning plate 503 through the two linear sliders 502 at both ends and the two linear guide rails 501. The transverse positioning plate 503 moves through the multiple mounting grooves 504 and drives the multiple top wheels 505 to move together until the outer walls of the multiple top wheels 505 on the front and rear transverse positioning plates 503 respectively abut against the front and rear inner walls of the aircraft wall panel, thereby providing a transverse positioning effect for the aircraft wall panel and preventing the aircraft wall panel from moving laterally. At the same time, since the positions of the front and rear transverse positioning plates 503 can be adjusted front and rear in this device, it can be used to perform front and rear positioning on aircraft wall panels of different widths, and has a wide range of applications.

[0049] By controlling the output rods of the left and right servo cylinders 206 to extend and retract in opposite directions, the distance between the left and right connecting plates 204 is adjusted, and the distance between the left and right rollers 301 and the left and right pressure rollers 304 is further adjusted through the left and right connecting plates 204, that is, the distance between the left and right supporting rollers 302 and the left and right pressure rollers 305 is adjusted, so as to facilitate the up and down positioning of aircraft wall panels of different lengths. The output shaft of the servo motor 3011 drives the active pulley 3012 to rotate, and further drives the driven pulley 3013 to rotate together with the supporting roller 301 under the connection action of the power belt 3014. The rotation of the supporting roller 301 further drives the supporting roller 302 to rotate. The rotating torque of the supporting roller 302 will directly cause the aircraft wall panel to move left or right, so that while the aircraft wall panel is longitudinally positioned, the left and right position of the aircraft wall panel can be adjusted, which is convenient for adjusting the position of the maintenance area on the aircraft wall panel, and has strong flexibility.

[0050] The output shaft of the AC motor 401 drives the driving gear 402 to rotate, and the rotation of the driving gear 402 further drives the guide ring 208 to rotate through the driven gear ring 403 engaged therewith, so that the movable component 200 and the longitudinal positioning component 300 rotate as a whole, thereby adjusting the angle of the aircraft wall panel to facilitate maintenance and processing of the side of the aircraft wall panel.

[0051] While the embodiments of the present invention have been shown and described, it will be appreciated by those skilled in the art that various changes, modifications, substitutions, and variations can be made to the embodiments without departing from the principles and spirit of the invention.

Claims

1. A fixing device for aircraft panel repair and processing, characterized by: The supporting component (100) includes a machine stand (101), and three positioning pins (102) are fixedly mounted on adjacent sides of the machine stand (101), and the outer walls of the positioning pins (102) are rotatably mounted with a work wheel (103); A movable component (200) is provided inside the support component (100) for rotation. The movable component (200) is used for adjusting the angle of the aircraft wall panel. The movable component (200) includes two end plates (201) distributed on the left and right. Four square tubes (202) are fixedly installed between the two end plates (201). The four square tubes (202) are divided into two layers, upper and lower, and each layer has two front and rear. The outer walls of the square tubes (202) are slidably installed with two sliding sleeves (203) distributed on the left and right. A connecting plate (204) is fixedly installed between the upper and lower sliding sleeves (203). The front and right parts of the two end plates (201) on the left and right are fixedly installed. The stressed pile seats (205) are arranged in an upper and lower staggered manner on the left and right directions, and the side surfaces of the stressed pile seats (205) in the left and right directions that are close to each other are fixedly mounted with servo cylinders (206) through brackets, the output rod ends of the left and right servo cylinders (206) are respectively connected to the left and right sliding sleeves (203) through brackets, a clearance opening (207) is opened through the two end plates (201), and the side surfaces of the left and right end plates (201) that are away from each other are fixedly mounted with guide rings (208), the guide rings (208) are located on the periphery of the clearance opening (207), and the guide rings (208) are movably stuck inside the three work-shaped wheels (103); A longitudinal positioning component (300) is provided inside the movable component (200) for rotation. The longitudinal positioning component (300) is used for lateral adjustment of the aircraft wall panel. The longitudinal positioning component (300) includes a roller (301) and a pressure roller (304) that are rotatably located between the front and rear connecting plates (204). The roller (301) is located at the bottom of the pressure roller (304). The outer wall of the roller (301) is provided with two front-to-rear distributed supporting wheels (302). The outer wall of the pressure roller (304) is provided with two front-to-rear distributed pressure wheels (305) that are slidably located. The roller (301) is rotatably installed between the front and rear connecting plates (204). The front and rear connecting plates (204) A slide groove (303) is provided between the two slide grooves (303), the central axis of the pressure roller (304) is slidably installed between the front and rear slide grooves (303), the front and rear parts of the central axis of the pressure roller (304) are both rotatably installed with spring brackets (306) through bearings, the bottom of the spring bracket (306) is fixedly installed with an insertion rod (307), a side of the connecting plate (204) close to the insertion rod (307) is fixedly installed with a sliding seat (308), the insertion rod (307) slides through the top and bottom of the sliding seat (308), and the outer sleeve of the insertion rod (307) is provided with a tensioning spring (309), and the tensioning spring (309) is fixedly installed between the bottom wall of the spring bracket (306) and the top of the sliding seat (308); A driving component (400), wherein the right end of the supporting component (100) is provided with the driving component (400), and the driving component (400) is used for power input to the movable component (200); A transverse positioning component (500) is provided inside the movable component (200), and the transverse positioning component (500) is used for supporting aircraft wall panels.

2. The fixing device for aircraft panel repair and processing according to claim 1, characterized in that: A motor fixing seat (3010) is fixedly mounted on the lower portion of a side surface close to the two connecting plates (204) located at the front, a servo motor (3011) is fixedly mounted on the front of the motor fixing seat (3010), a driving pulley (3012) is fixedly mounted on the output shaft of the servo motor (3011), a driven pulley (3013) is fixedly mounted on the front portion of the central axis of the roller (301), and a power belt (3014) is sleeved between the driven pulley (3013) and the driving pulley (3012).

3. The fixing device for aircraft panel repair and processing according to claim 1, characterized in that: The outer wall of the supporting roller (301) is provided with a first torque limiting groove (3001), and the side surfaces of the front and rear supporting rollers (302) that are away from each other are fixedly mounted with a first positioning hoop (3002), the outer wall of the first positioning hoop (3002) is threadedly connected with a first fastening bolt (30021), and the end of the first fastening bolt (30021) abuts against the bottom wall of the first torque limiting groove (3001), and the outer wall of the pressure roller (304) is provided with a second torque limiting groove (3004), and the side surfaces of the front and rear pressure rollers (305) that are away from each other are fixedly mounted with a second positioning hoop (3005), the outer wall of the second positioning hoop (3005) is threadedly connected with a second fastening bolt (30051), and the end of the second fastening bolt (30051) abuts against the bottom wall of the second torque limiting groove (3004).

4. The fixing device for aircraft panel repair and processing according to claim 3, characterized in that: The driving component (400) includes an AC motor (401) fixedly mounted on the lower right end of the machine stand (101), a driving gear (402) fixedly mounted on the output shaft of the AC motor (401), a driven gear ring (403) fixedly mounted on the right side of one of the guide rings (208) located on the right, the driven gear ring (403) located on the top of the driving gear (402), and the driven gear ring (403) and the driving gear (402) are meshed with each other.

5. The fixing device for aircraft panel repair and processing according to claim 4, characterized in that: The transverse positioning component (500) includes two linear guide rails (501) fixedly mounted on opposite surfaces of the left and right end plates (201), and two linear sliders (502) distributed front and rear are slidably mounted on the outer walls of the left and right linear guide rails (501), wherein a transverse positioning plate (503) is fixedly mounted between the two linear sliders (502) in the left and right directions, and the number of the transverse positioning plates (503) is two, and a plurality of placement grooves (504) distributed at equal distances on the left and right are penetrated on the side surfaces of the two transverse positioning plates (503), and a top wheel (505) is rotatably mounted inside the transverse positioning plates (503).

6. The fixing device for aircraft panel repair and processing according to claim 5, characterized in that: A follower sleeve (506) is fixedly mounted on the side of the first positioning hoop (3002) away from the supporting roller (302). The follower sleeve (506) is slidably positioned on the periphery of the supporting roller (301), and an annular groove (507) is formed on the outer wall of the follower sleeve (506). The bottom of the transverse positioning plate (503) is movably engaged with the inside of the annular groove (507).

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