Fixing device for maintenance and processing of aircraft panel

Abstract

The invention relates to the technical field of fixing tools, in particular to a fixing device for aircraft panel maintenance and processing, which comprises a supporting component, a movable component is rotatably arranged in the supporting component, a longitudinal positioning component is rotatably arranged in the movable component, and a driving component is arranged at the right end of the supporting component. The aircraft panel is longitudinally positioned through the longitudinal positioning part, longitudinal movement of the aircraft panel is restrained, the front pressing wheel and the rear pressing wheel and the distance between the front supporting wheel and the rear supporting wheel can be adjusted by sliding the supporting wheels and the pressing wheels front and back, and therefore the aircraft panel fixing device can be used for the aircraft panels with different widths. And the longitudinal positioning part can act on the aircraft panel to move leftwards or rightwards, so that the aircraft panel can be longitudinally positioned, meanwhile, the left-right position of the aircraft panel can be adjusted, the position of a maintenance area on the aircraft panel can be conveniently adjusted, and the flexibility is high.

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 combined wall panels composed of skins, long stringers and wing spar edge strips. The skins are usually connected to the long stringers and wing spar edge strips 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. According to a Chinese patent with application publication number CN117415650A, a fixture for processing aircraft wall panels is disclosed, which can provide local support for the drilling part of the skin when drilling in the open middle part of the skin, thereby reducing the problem of impact deformation caused by the drilling part being suspended in the air. However, the above-mentioned fixture still has the technical problem of low flexibility, and the adjustment of the processing position of the aircraft wall panel is not convenient enough. Therefore, we propose a fixture for aircraft wall panel maintenance and processing to solve the above-mentioned technical problems. Summary of the invention

[0003] The present invention provides the following technical solution: a fixing device for aircraft wall panel maintenance and processing, comprising a supporting component; A movable component is provided inside the supporting component for rotation, and the movable component is used for adjusting the angle of the aircraft wall panel; 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; A driving component, wherein the right end of the supporting component is provided with a driving component, and the driving component is used for inputting power to the movable component; A transverse positioning component is provided inside the movable component, and the transverse positioning component is used for supporting the aircraft wall panel.

[0004] 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 I-shaped wheels.

[0005] 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 rear 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 force-bearing pile seats are fixedly installed on the front and right parts of the left and right end plates. The force-bearing pile seats in the left and right directions are staggered up and down, and servo cylinders are fixedly installed on the side surfaces of the left and right force-bearing pile seats that are close to each other 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.

[0006] 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 I-shaped wheels.

[0007] As a preferred solution of the present invention, the longitudinal positioning component includes a roller and a pressure roller rotatably located between the front and rear connecting plates, the roller is located at the bottom of the pressure roller, the outer wall of the roller is movably provided with two rollers distributed front and back, the outer wall of the pressure roller is slidably provided with two pressure rollers distributed front and back, the roller is rotatably installed between the front and rear connecting plates, a slide groove is penetrated through the front and rear connecting plates, the central axis of the pressure roller is slidably installed between the front and rear slide grooves, the front and rear parts of the central axis of the pressure roller are rotatably installed with a spring bracket through bearings, the bottom of the spring bracket is fixedly installed with an insertion rod, a sliding seat is fixedly installed on a side of the connecting plate close to the insertion rod, the insertion rod slides through the top and bottom of the sliding seat, and the outer sleeve of the insertion rod is provided with a tensioning spring, and the tensioning spring is fixedly installed between the bottom wall of the spring bracket and the top of the sliding seat.

[0008] As a preferred solution of the present invention, a motor fixing seat is fixedly installed on the lower part of a side surface close to the two connecting plates located at the front, a servo motor is fixedly installed on the front side 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.

[0009] As a preferred solution of the present invention, a first torque limiting groove is formed on the outer wall of the supporting roller, and a first positioning hoop is fixedly installed on the side faces of the front and rear supporting rollers that are away from each other, 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 formed on the outer wall of the pressure roller, and a second positioning hoop is fixedly installed on the side faces of the front and rear pressure rollers that are away from each other, 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.

[0010] 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, wherein a driven gear ring is fixedly mounted on the right side surface of one of the guide rings located on the right part, the driven gear ring is located on the top of the driving gear, and the driven gear ring and the driving gear are meshed with each other.

[0011] 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.

[0012] 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 formed on the outer wall of the follower sleeve. The bottom of the transverse positioning plate is movably clamped in the inner part of the annular groove.

[0013] Compared with the prior art, the present invention has the following beneficial effects: 1. In the present invention, the longitudinal positioning component is used to longitudinally position the aircraft wall panel to inhibit the longitudinal movement of the aircraft wall panel, and the front and rear two pressure wheels and the distance between the front and rear two supporting wheels can be adjusted by sliding the supporting wheel and the pressure wheel forward and backward to cope with the use of aircraft wall panels of different widths. The distance between the left and right connecting plates is adjusted by controlling the output rods of the left and right servo cylinders to extend and retract in the opposite direction. The left and right connecting plates are further used to adjust the distance between the supporting rollers in the left and right directions and the pressure rollers in the left and right directions, that is, the distance between the left and right supporting wheels and the pressure rollers in the left and right directions is adjusted, so that the aircraft wall panels of different lengths can be conveniently positioned up and down. The output shaft of the servo motor drives the active pulley to rotate, and further drives the driven pulley to rotate together with the supporting roller under the connection of the power belt. The rotation of the supporting roller further drives the supporting wheel to rotate. The torque of the supporting wheel rotation 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 positions 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.

[0014] 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 together 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 two linear sliders and two linear guide rails at both ends. The movement of the transverse positioning plate drives multiple top wheels to move together through multiple mounting grooves until the outer walls of the multiple top wheels on the front and rear transverse positioning plates 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 to prevent 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.

[0015] 3. In the present invention, the output shaft of the AC motor drives the driving gear to rotate, and the driving gear further drives the guide ring to rotate through the driven gear ring meshing therewith, so that the movable parts and the longitudinal positioning parts rotate as a whole, thereby adjusting the angle of the aircraft wall panel to facilitate the maintenance and processing of the side of the aircraft wall panel. BRIEF DESCRIPTION OF THE DRAWINGS

[0016] Figure 1 It is a schematic diagram of the structure of the present invention; Figure 2 It is a structural schematic diagram of the supporting component in the present invention; Figure 3 It is a structural schematic diagram of the movable parts in the present invention; Figure 4 It is a schematic diagram of the planar structure of the movable parts in the present invention; Figure 5 For the present invention Figure 3 Schematic diagram of the local structure; Figure 6 For the present invention Figure 5 Schematic diagram of the local structure; Figure 7 For the present invention Figure 6 A schematic diagram of the enlarged structure of part A; Figure 8 It is a structural schematic diagram of the longitudinal positioning component in the present invention; Fig. 9 For the present invention Figure 8 A schematic diagram of the enlarged structure of part B; Fig.10 It is a schematic diagram of the local structure of the roller in the present invention.

[0017] In the figure: 100, supporting component; 101, machine foot frame; 102, positioning shaft pin; 103, I-shaped wheel; 200, movable component; 201, end plate; 202, square tube; 203, sliding sleeve; 204, connecting plate; 205, force pile seat; 206, servo cylinder; 207, yielding port; 208, guide ring; 300, longitudinal positioning component; 301, roller; 302, supporting wheel; 303, slide groove; 304, pressure roller; 305, pressure wheel; 306, spring bracket; 307, plug rod; 308, sliding seat; 309, tension 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, lateral positioning component; 501, linear guide; 502, linear slider; 503, lateral positioning plate; 504, mounting groove; 505, top wheel; 506, follower sleeve; 507, ring groove. DETAILED DESCRIPTION

[0018] The following will be combined with the drawings in the embodiments of the present invention to clearly and completely describe the technical solutions in the embodiments of the present invention. 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 creative work are within the scope of protection of the present invention.

[0019] See also Figure 1-Figure 10 The technical solution provided by the present invention specifically includes the following embodiments: Embodiment 1: A fixing device for aircraft panel repair and processing, comprising a supporting component 100, a movable component 200 is provided for rotation inside the supporting component 100, a longitudinal positioning component 300 is provided for rotation inside the movable component 200, and a driving component 400 is provided at the right end of the supporting component 100; The supporting component 100 includes a machine stand 101, and three positioning pins 102 are fixedly installed on the adjacent side of the machine stand 101, and the outer wall of the positioning pins 102 is rotatably installed with a wheel 103; 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, and each layer has two front and rear ones, and the outer walls of the square tubes 202 are slidably installed with two sliding sleeves 203 distributed on the left and right, wherein a connecting plate 204 is fixedly installed between the upper and lower sliding sleeves 203, and the front and right parts of the left and right end plates 201 are fixedly installed with force pile seats 205, and the force pile seats 205 in the left and right directions are arranged in an up-and-down staggered manner, 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, and 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 formed between the two end plates 201. A guide ring 208 is fixedly installed on the side of the left and right end plates 201 that are away from each other. The guide ring 208 is located outside the clearance opening 207 and is movably stuck inside the three I-shaped wheels 103. The driving component 400 includes an AC motor 401 fixedly mounted at 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, wherein a driven gear ring 403 is fixedly mounted on the right side of a guide ring 208 located at the right part, the driven gear ring 403 is located at the top of the driving gear 402, and the driven gear ring 403 and the driving gear 402 are meshed with each other; 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 the maintenance and processing of the side of the aircraft wall panel.

[0020] 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 movably provided with two supporting wheels 302 distributed front and back. The outer wall of the pressure roller 304 is slidably provided with two pressure wheels 305 distributed front and back. The roller 301 is rotatably installed between the front and rear connecting plates 204. A slide groove 303 is opened 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, the front and rear parts of the central axis of the pressure roller 304 are rotatably mounted with spring brackets 306 through bearings, a plunger 307 is fixedly mounted on the bottom of the spring bracket 306, a sliding seat 308 is fixedly mounted on a 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, and a tensioning spring 309 is sleeved on the outer periphery of the plunger 307, and the tensioning spring 309 is fixedly mounted between the bottom wall of the spring bracket 306 and the top of the sliding seat 308; A motor fixing seat 3010 is fixedly installed at the lower part of the side surface close to the two connecting plates 204 at the front, a servo motor 3011 is fixedly installed at the front of the motor fixing seat 3010, a driving pulley 3012 is fixedly installed on the output shaft of the servo motor 3011, a driven pulley 3013 is fixedly installed at the front 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; A first torque limiting groove 3001 is provided 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 wheels 302, and 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 provided 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 wheels 305, and 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. Specifically, the present embodiment places the processed aircraft panel between the supporting wheel 302 and the pressure wheel 305 through any one of the left and right clearance openings 207, 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 panel through the pressure roller 304, thereby forming a clamping effect on the upper and lower parts of the aircraft panel with the supporting wheel 302, longitudinally positioning the aircraft panel, and inhibiting the longitudinal movement of the aircraft panel, and by sliding the supporting wheel 302 and the pressure wheel 305 forward and backward, the distance between the two front and rear pressure wheels 305 and the two front and rear supporting wheels 302 can be adjusted to cope with aircraft 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, so as 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 can be adjusted, and the distance between the left and right rollers 301 and the left and right pressure rollers 304 can be further adjusted through the left and right connecting plates 204, that is, the distance between the left and right supporting wheels 302 and the left and right pressure wheels 305 can be 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 of the power belt 3014. The rotation of the roller 301 further drives the supporting wheel 302 to rotate. The torque of the supporting wheel 302 will directly cause the aircraft wall panel to move to the 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.

[0021] Embodiment 3: A transverse positioning component 500 is provided inside the movable component 200, and the transverse positioning component 500 includes two linear guide rails 501 fixedly installed on the opposite surfaces of the left and right end plates 201, and two linear sliders 502 distributed front and back are slidably installed on the outer walls of the left and right linear guide rails 501, wherein a transverse positioning plate 503 is fixedly installed 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 that are close to each other, and top wheels 505 are rotatably installed inside the transverse positioning plates 503; A follower sleeve 506 is fixedly installed on one side of the first positioning hoop 3002 away from the supporting roller 302, and the follower sleeve 506 is slidably located on the periphery of the supporting roller 301, and an annular groove 507 is provided on the outer wall of the follower sleeve 506. A follower sleeve 506 is fixedly installed on one side of the first positioning hoop 3002 away from the supporting roller 302, and the follower sleeve 506 is slidably located on the periphery of the supporting roller 301, and an annular groove 507 is provided on the outer wall of the follower sleeve 506, and the bottom of the transverse positioning plate 503 is movably clamped in the inner part of the annular groove 507; Specifically, 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 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 to prevent 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.

[0022] When the fixing device for repairing and processing aircraft wall panels of the present invention is working, the processed aircraft wall panel is placed between the supporting wheel 302 and the pressing wheel 305 through any one of the left and right clearance openings 207, and the spring bracket 306 is pulled down by the elastic force of the tension spring 309, and the pressing wheel 305 is further driven by the pressing roller 304 to press down the top of the aircraft wall panel, 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 inhibiting the longitudinal movement of the aircraft wall panel, and by 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. 02 In the process of front and rear adjustment, 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 together 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 at both ends and the two linear guide rails 501. The transverse positioning plate 503 moves through the multiple placement grooves 504 to drive the multiple top wheels 505 to move together until the outer walls of the multiple top wheels 505 on the front and rear two 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 to prevent the aircraft wall panel from moving laterally. At the same time, since the positions of the front and rear two 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. 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 can be adjusted, and the distance between the left and right rollers 301 and the left and right pressure rollers 304 can be further adjusted through the left and right connecting plates 204, that is, the distance between the left and right supporting wheels 302 and the left and right pressure wheels 305 can be 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 of the power belt 3014. The rotation of the roller 301 further drives the supporting wheel 302 to rotate. The torque of the supporting wheel 302 will directly cause the aircraft wall panel to move to the 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. The output shaft of the AC motor 401 drives the driving gear 402 to rotate, and 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 the maintenance and processing of the side of the aircraft wall panel.

[0023] While the embodiments of the present invention have been shown and described, it will be appreciated by those skilled in the art that many changes, modifications, substitutions and variations may be made to the embodiments without departing from the principles and spirit of the invention.

Claims

1. A fixing device for aircraft panel repair processing, characterized in that: comprising a supporting member (100); A movable component (200), wherein the interior of the support component (100) is provided with the movable component (200) for rotation, and the movable component (200) is used for adjusting the angle of the aircraft wall panel; A longitudinal positioning component (300), the movable component (200) is internally rotatably provided with the longitudinal positioning component (300), and the longitudinal positioning component (300) is used for lateral adjustment of the aircraft wall panel; 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 inputting power 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: The support component (100) comprises a machine stand (101), and three positioning shaft pins (102) are fixedly mounted on adjacent sides of the machine stand (101), and the outer walls of the positioning shaft pins (102) are rotatably mounted with a profile wheel (103).

3. The fixing device for aircraft panel repair and processing according to claim 2, characterized in that: The movable component (200) comprises 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, 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), a connecting plate (204) is fixedly installed between the two upper and lower sliding sleeves (203), front and right parts of the two 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 arranged in an up-and-down staggered manner, and servo cylinders (206) are fixedly installed on the side surfaces of the force pile seats (205) in the left and right directions that are close to each other through brackets, and the output rod ends of the two left and right servo cylinders (206) are respectively connected to the two left and right sliding sleeves (203) through brackets.

4. The fixing device for aircraft panel repair processing according to claim 3, characterized in that: A clearance opening (207) is provided between the two end plates (201), and a guide ring (208) is fixedly installed on the side faces of the left and right end plates (201) that are away from each other. The guide ring (208) is located outside the clearance opening (207), and the guide ring (208) is movably locked inside the three I-shaped wheels (103).

5. The fixing device for aircraft panel repair processing according to claim 4, characterized in that: The longitudinal positioning component (300) comprises a roller (301) and a pressure roller (304) 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 movably provided with two supporting wheels (302) distributed front and rear; the outer wall of the pressure roller (304) is slidably provided with two pressure wheels (305) distributed front and rear; 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 on the front Between the two rear slide grooves (303), the front and rear parts of the central axis of the pressure roller (304) are rotatably mounted with spring brackets (306) via bearings, a plunger (307) is fixedly mounted at the bottom of the spring bracket (306), a sliding seat (308) is fixedly mounted on a 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), and a tensioning spring (309) is provided on the outer sleeve of the plunger (307), and the tensioning spring (309) is fixedly mounted between the bottom wall of the spring bracket (306) and the top of the sliding seat (308).

6. The fixing device for aircraft panel repair processing according to claim 5, characterized in that: A motor fixing seat (3010) is fixedly mounted on the lower part 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 part 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).

7. The fixing device for aircraft panel repair processing according to claim 6, characterized in that: The outer wall of the supporting roller (301) is provided with a first torque limiting groove (3001); a first positioning hoop (3002) is fixedly mounted on a side of the front and rear supporting rollers (302) that are away from each other; a first fastening bolt (30021) is threadedly connected to the outer wall of the first positioning hoop (3002); an 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 provided on the outer wall of the pressure roller (304); a second positioning hoop (3005) is fixedly mounted on a side of the front and rear pressure rollers (305) that are away from each other; a second fastening bolt (30051) is threadedly connected to the outer wall of the second positioning hoop (3005); an end of the second fastening bolt (30051) abuts against the bottom wall of the second torque limiting groove (3004).

8. The fixing device for aircraft panel repair and processing according to claim 7, characterized in that: The driving component (400) comprises 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 surface of a guide ring (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) mesh with each other.

9. The fixing device for aircraft panel repair processing according to claim 8, characterized in that: The transverse positioning component (500) comprises 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 equidistantly on the left and right sides of the two transverse positioning plates (503) are penetrated, and a top wheel (505) is rotatably mounted inside the transverse positioning plates (503).

10. The fixing device for aircraft panel repair processing according to claim 9, characterized in that: A follower sleeve (506) is fixedly mounted on a 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 supporting roller (301); an annular groove (507) is formed on the outer wall of the follower sleeve (506); and the bottom of the transverse positioning plate (503) is movably clamped in the interior of the annular groove (507).

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