Structural surface defect detection device for aircraft composite material maintenance

Abstract

The invention discloses a structure surface defect detection device for aircraft composite material maintenance, and relates to the field of defect detection equipment.The structure surface defect detection device comprises a work platform and a limiting rack fixed to the upper end face of the work platform, and two symmetrically-distributed bearing rollers are rotationally erected on the upper end face of the limiting rack; according to the aircraft duct horn marking device disclosed by the invention, the marking unit extends into the aircraft duct horn under the action of the driving piece, and the inner wall of the aircraft duct horn is subjected to searchlighting scanning treatment through the laser scanning probe; moreover, under the action of the driving unit, the aircraft duct horn can be detected in a self-rotating state, and when flaws are detected, the flawed part can be positioned under the laser scanning probe through the driving unit, so that marking slurry is directly sprayed to the flawed part through triggering of the marking unit, and the detection accuracy is improved. And therefore, a worker can directly know the specific position of the flaw part during repairing operation.

Description

TECHNICAL FIELD

[0001] The application belongs to the field of defect detection equipment, and particularly relates to a structural surface defect detection device for aircraft composite material maintenance. BACKGROUND

[0002] The structural surface of an aircraft needs to be subjected to defect detection treatment (such as defects of pits, scratches and wear of the structural surface of the aircraft) before assembly and before each take-off after being put into use, so as to ensure the safety of the aircraft in the flight process.

[0003] When the inner wall of the aircraft conduit horn is subjected to defect detection, the conduit horn is directly clamped through the claw disc which can rotate, and then the laser probe detector is inserted into the interior of the conduit horn, and the conduit horn is in a rotating state in the process of being inserted into the interior of the conduit horn, so that the inner surface structure of the conduit horn is subjected to omnidirectional defect detection treatment. SUMMARY

[0004] The application aims to provide a structural surface defect detection device for aircraft composite material maintenance to solve the problems in the background art.

[0005] To achieve the above object, the application provides the following technical scheme: a structural surface defect detection device for aircraft composite material maintenance, comprising: a work platform and a limiting rack fixed on the upper end face of the work platform, and the upper end face of the limiting rack is further provided with two symmetrically distributed supporting rollers, an aircraft conduit horn is placed between the two supporting rollers, a driving unit is further arranged on the outer side of the limiting rack, the driving unit is used for driving the aircraft conduit horn to rotate between the two supporting rollers, a driving member is further fixedly arranged on the upper end face of the work platform, the driving member is an electric push rod or a pneumatic push rod, an output end of the driving member is fixedly provided with a connecting rod, and the other end of the connecting rod is fixedly provided with a laser scanning probe for scanning and probing the inner wall of the aircraft conduit horn. Further comprising: a marking unit for marking the defect position of the inner wall of the aircraft conduit, the marking unit is arranged outside the laser scanning probe.

[0006] Preferably, the driving unit comprises a lifting plate, a motor fixed on the upper end surface of the lifting plate, a rotating shaft hung on the lower end surface of the lifting plate, a rubber roller sleeve fixed on the outer surface of the rotating shaft, a straight groove for increasing the friction force when the rubber roller sleeve contacts with the aircraft duct horn, a synchronous gear fixed on the output end of the motor and one end of the rotating shaft, a synchronous gear belt transmission assembled between the two synchronous gears, and an elastic pressure component between the lifting plate and the working platform.

[0007] Preferably, the elastic pressure component comprises a limiting sleeve rod fixed on the upper end surface of the working platform, the limiting sleeve rod is distributed on the outer side of the limiting stand and the lifting plate, a sliding block is slidingly assembled in the limiting sleeve rod, a tension spring is fixed between the lower end surface of the sliding block and the limiting sleeve rod, the sliding block is fixed with the side wall of the lifting plate, and a pull rod is slidingly arranged on the upper end surface of the sliding block.

[0008] Preferably, the rotating shaft and the supporting roller are parallel distributed, and the axis of the rotating shaft is the symmetry center of the two supporting rollers.

[0009] Preferably, the probe of the laser scanning probe is downward, the marking unit comprises a rotating column rotatably assembled on the outer wall of the laser scanning probe, a limiting curved plate is fixed on the outer surface of the rotating column, a spray pipe is fixed on one end of the limiting curved plate away from the rotating column, the axis of the rotating column is perpendicular to the axis of the spray pipe, a conical sleeve is fixed in the interior of the spray pipe, the conical sleeve is located at one end of the spray pipe away from the laser scanning probe, the conical top of the conical sleeve extends into the interior of the spray pipe, a plastic valve membrane pressure relief port is fixedly embedded in the conical top of the conical sleeve, a curved pipe is fixedly and communicatively arranged on the outer wall of the spray pipe, a liquid storage tank is fixedly and communicatively assembled on the other end of the curved pipe, the curved pipe and the liquid storage tank are made of transparent material, a detachable sealing plug is embedded on the outer wall of the liquid storage tank, the butt joint port of the curved pipe and the spray pipe is located on the side of the spray pipe away from the laser scanning probe, and a pressure component and a turnover component are arranged on the outer part of the limiting curved plate.

[0010] Preferably, the pressure applying component comprises a sliding sleeve block axially slidingly assembled on the outer surface of the connecting rod, and a pushing block is fixed on the surface of the sliding sleeve block, a push rod is further fixedly assembled on the outer surface of the sliding sleeve block, a sealing sleeve is slidingly sleeved on the other end of the push rod, a piston disc is further fixedly arranged on the end of the push rod extending into the sealing sleeve, a gas pipe is fixedly and communicatively arranged between the end of the sealing sleeve away from the push rod and the end of the spray pipe away from the conical sleeve, a second spring is fixedly arranged between the end of the piston disc away from the push rod and the sealing sleeve, a first one-way valve is assembled at the joint of the spray pipe and the gas pipe, and a second one-way valve is assembled on the outer wall of the sealing sleeve.

[0011] Preferably, the overturning component comprises a transmission gear fixedly sleeved on the outer surface of the rotating column, the transmission gear is located between the limiting curved plate and the laser scanning probe, a toothed plate is fixedly arranged on the outer surface of the sealing sleeve and movably engaged with the transmission gear, a first baffle is fixedly arranged on the outer surface of the toothed plate in a vertical distribution, the first baffle is located between the transmission gear and the sealing sleeve, a second baffle is fixedly arranged on the outer wall of the laser scanning probe, and the toothed plate is located between the transmission gear and the second baffle.

[0012] Preferably, a V-shaped disc is fixedly and adhesively arranged on the end face of the spray pipe away from the gas pipe, a storage space is arranged between the V-shaped disc and the arc wall of the conical sleeve, and a sponge ring is arranged in the storage space.

[0013] Preferably, a limiting sleeve is fixedly arranged on the outer wall of the connecting rod in a vertical distribution, a sliding disc is slidingly assembled in the limiting sleeve, a first spring is fixedly arranged between the end of the sliding disc close to the connecting rod and the limiting sleeve, a stand is fixedly arranged on the other end of the sliding disc and slidingly penetrating through the limiting sleeve, a cleaning plate is further fixedly arranged on the end of the stand away from the sliding disc, a flexible cleaning strip is further fixedly and adhesively arranged on the end face of the cleaning plate away from the stand, and the limiting sleeve is located on the side close to the laser scanning probe.

[0014] Preferably, the end of the cleaning plate away from the driving member is in a bent head shape.

[0015] Compared with the prior art, the present application has the following beneficial effects: The application can extend the marking unit into the inside of the aircraft conduit horn through the action of the driving member, can make the aircraft conduit horn in the state of self-rotation for detection treatment under the action of the driving unit, and can make the flaw position directly below the laser scanning probe through the driving unit when the flaw is detected, so as to directly spray the marking paste on the flaw position through the triggering of the marking unit, thereby facilitating the staff to directly know the specific position of the flaw when repairing. BRIEF DESCRIPTION OF DRAWINGS

[0016] Figure 1 It is a schematic diagram of the overall structure of the application; Figure 2 It is a schematic diagram of the internal structure of the limiting sleeve rod of the application; Figure 3 It is a schematic diagram of the structure of the cleaning plate and flexible cleaning strip of the application; Figure 4 It is a schematic diagram of the structure of the limiting curved plate of the application; Figure 5 It is a schematic diagram of the internal structure of the sealing sleeve of the application; Figure 6 It is a schematic diagram of the structure of the plastic valve membrane pressure relief port of the application; Figure 5 It is an enlarged view of A in the application; Figure 7 It is a schematic diagram of the structure of the plastic valve membrane pressure relief port of the application; Figure 8 It is a schematic diagram of the structure of the V-shaped disc and sponge ring of the application.

[0017] In the figure: 1, work platform; 2, limiting sleeve rod; 3, sliding block; 4, tension spring; 5, pull rod; 6, lifting plate; 7, motor; 8, rotating shaft; 9, rubber roller sleeve; 10, straight groove; 11, limiting rack; 12, receiving roller; 13, driving member; 14, connecting rod; 15, laser scanning probe; 16, limiting sleeve; 17, sliding disc; 18, first spring; 19, stand column; 20, cleaning plate; 21, flexible cleaning strip; 22, rotating column; 23, limiting curved plate; 24, spray pipe; 25, transmission gear; 26, toothed plate; 27, sealing sleeve; 28, piston disc; 29, second spring; 30, push rod; 31, sliding sleeve block; 32, first baffle; 33, second baffle; 34, first one-way valve; 35, second one-way valve; 36, air pipe; 37, conical sleeve; 38, plastic valve membrane pressure relief port; 39, curved pipe; 40, liquid storage tank; 41, V-shaped disc; 42, sponge ring. DETAILED DESCRIPTION

[0018] With reference to the drawings of the embodiments of the present application, the technical solutions in the embodiments of the present application will be described clearly and completely. Obviously, the described embodiments are only a part of the embodiments of the present application, rather than all the embodiments of the present application. Based on the embodiments of the present application, all the other embodiments obtained by a person of ordinary skill in the art without creative effort belong to the scope of protection of the present application.

[0019] Embodiment one: please refer to Figures 1-6 , the structural surface defect detection device for aircraft composite material maintenance shown in the figure comprises: a work platform 1 and a limiting rack 11 fixed on the upper end face of the work platform 1, and the upper end face of the limiting rack 11 is also rotatably provided with two symmetrically distributed receiving rollers 12, an aircraft conduit horn is placed between the two receiving rollers 12, a driving unit is further arranged on the outer side of the limiting rack 11, the driving unit is used to drive the aircraft conduit horn to rotate between the two receiving rollers 12, a driving member 13 is further fixedly arranged on the upper end face of the work platform 1, the driving member 13 is an electric push rod or a pneumatic push rod, an output end of the driving member 13 is fixedly provided with a connecting rod 14, and the other end of the connecting rod 14 is fixedly provided with a laser scanning probe 15 for scanning and projecting the inner wall of the aircraft conduit horn, the laser scanning probe 15 is directly connected with a computer, and the picture detected by the laser scanning probe 15 can be observed in real time through the display of the computer; Further comprising: a marking unit for marking the defect position detected on the inner wall of the aircraft conduit, the marking unit is arranged outside the laser scanning probe 15.

[0020] The driving unit comprises a lifting plate 6 and an electric motor 7 fixed on the upper end face of the lifting plate 6, the lower end face of the lifting plate 6 is rotatably provided with a rotating shaft 8, a rubber roller sleeve 9 is fixedly sleeved on the outer surface of the rotating shaft 8, a plurality of straight grooves 10 are arranged on the outer surface of the rubber roller sleeve 9 in a circumferential equidistant manner, the straight grooves 10 are used to increase the friction force when the rubber roller sleeve 9 contacts the aircraft conduit horn, a synchronous gear is fixedly sleeved on one end of the rotating shaft 8 and the output end of the electric motor 7, a synchronous gear belt is transmissionally assembled between the two synchronous gears, and an elastic pressure component is further arranged between the lifting plate 6 and the work platform 1, so that the rubber roller sleeve 9 at the bottom of the lifting plate 6 tightly abuts against the outer surface of the aircraft conduit horn under the action of the elastic pressure component.

[0021] The elastic pressure applying component comprises a limiting sleeve rod 2 fixed on the end face of the working platform 1, and the limiting sleeve rod 2 is distributed outside the limiting rack 11 and the lifting plate 6, the inside of the limiting sleeve rod 2 is slidably equipped with a sliding block 3, a tension spring 4 is fixedly arranged between the lower end face of the sliding block 3 and the limiting sleeve rod 2, the sliding block 3 is fixed with the side wall of the lifting plate 6, and the upper end face of the sliding block 3 is fixedly arranged with a pull rod 5 which is slidably arranged in the limiting sleeve rod 2, the pull rod 5 can pull the sliding block 3 upward, and the tension spring 4 is stretched, when the aircraft duct horn is placed between the rubber roller sleeve 9 and the receiving roller 12, the pull rod 5 is loosened, and under the elastic pressure generated by the tension spring 4, the aircraft duct horn can be tightly clamped between the rubber roller sleeve 9 and the receiving roller 12.

[0022] The rotation shaft 8 and the receiving roller 12 are parallel, and the axis of the rotation shaft 8 is the symmetry center of the two receiving rollers 12, so that when the rubber roller sleeve 9 applies elastic pressure to the aircraft duct horn downward, the aircraft duct horn can be stably clamped between the two receiving rollers 12.

[0023] The probe of the laser scanning probe 15 is downward, the marking unit comprises a rotating column 22 which is rotatably arranged on the outer wall of the laser scanning probe 15, a limiting curved plate 23 is fixedly arranged on the outer surface of the rotating column 22, one end of the limiting curved plate 23 away from the rotating column 22 is fixedly arranged with a spray pipe 24, the axis of the rotating column 22 is perpendicular to the axis of the spray pipe 24, the inside of the spray pipe 24 is fixedly arranged with a conical sleeve 37, the conical sleeve 37 is located at one end of the spray pipe 24 away from the laser scanning probe 15, the conical top of the conical sleeve 37 extends into the inside of the spray pipe 24, and the conical top of the conical sleeve 37 is fixedly embedded with a plastic valve membrane pressure relief port 38, the outer wall of the spray pipe 24 is fixedly and continuously arranged with a curved pipe 39, and the other end of the curved pipe 39 is fixedly and continuously arranged with a liquid storage tank 40, the curved pipe 39 and the liquid storage tank 40 are both made of transparent material, and the outer wall of the liquid storage tank 40 is further embedded with a detachable sealing plug, the inside of the liquid storage tank 40 can be added with marking paste through the sealing plug, the butt joint port of the curved pipe 39 and the spray pipe 24 is located at one side of the spray pipe 24 away from the laser scanning probe 15, the outside of the limiting curved plate 23 is provided with a pressure applying component and a turnover component, the pressure applying component will first touch the turnover component when operating, so that the limiting curved plate 23 with the spray pipe 24 is turned over by 90 degrees, after being turned over by 90 degrees, the spray port of the spray pipe 24 is located directly below the probe of the laser scanning probe 15, and then high-pressure gas is input into the inside of the spray pipe 24, so that the marking paste is sprayed out through the plastic valve membrane pressure relief port 38.

[0024] The pressing component comprises a sliding sleeve block 31 axially slidingly assembled on the outer surface of the connecting rod 14, the surface of the sliding sleeve block 31 is fixedly provided with a pushing block, the outer portion of the sliding sleeve block 31 is fixedly assembled with a push rod 30, the other end of the push rod 30 is slidingly sleeved with a sealing sleeve 27, the end of the push rod 30 extending into the inside of the sealing sleeve 27 is further fixedly provided with a piston disc 28 slidingly assembled with the sealing sleeve 27, the end of the sealing sleeve 27 away from the push rod 30 is fixedly and communicatively provided with an air pipe 36 between the end of the air pipe 36 away from the conical sleeve 37 and the end of the air pipe 24 away from the conical sleeve 37, the end of the piston disc 28 away from the push rod 30 is fixedly provided with a second spring 29 between the piston disc 28 and the sealing sleeve 27, the air pipe 24 is assembled with a first one-way valve 34 at the joint with the air pipe 36, the outer wall of the sealing sleeve 27 is assembled with a second one-way valve 35, the flow direction of the first one-way valve 34 is one-way flow from the air pipe 36 to the inside of the air pipe 24, the flow direction of the second one-way valve 35 is one-way flow from the outside to the inside of the sealing sleeve 27, and the marking paste in the inside of the air pipe 24 cannot flow to the inside of the air pipe 36 through the first one-way valve 34.

[0025] The overturning component comprises a transmission gear 25 fixedly sleeved on the outer surface of the rotating column 22, the transmission gear 25 is located between the limiting curved plate 23 and the laser scanning probe 15, the outer surface of the sealing sleeve 27 is fixedly provided with a toothed plate 26, the toothed plate 26 is movably engaged with the transmission gear 25, the outer portion of the toothed plate 26 is fixedly provided with a first baffle 32 vertically distributed, the first baffle 32 is located between the transmission gear 25 and the sealing sleeve 27, the outer wall of the laser scanning probe 15 is fixedly provided with a second baffle 33, the toothed plate 26 is located between the transmission gear 25 and the second baffle 33, when the sealing sleeve 27 with the toothed plate 26 is pushed towards the rotating column 22, the rotating column 22 with the limiting curved plate 23 is rotated through the engagement of the toothed plate 26 with the transmission gear 25, and the first baffle 32 functions to limit the rotating column 22 to rotate only by 90 degrees.

[0026] Embodiment two: please refer to Figure 7 and Figure 8 , the end face of the air pipe 24 away from the air pipe 36 is fixedly bonded with a V-shaped disc 41, the V-shaped disc 41 is provided with a storage space between the circular arc wall of the conical sleeve 37, and the sponge ring 42 is placed in the inside of the storage space, when part of the marking paste is sprayed on the outer wall of the conical sleeve 37, the marking paste can flow to the inside of the storage space along the circular arc wall of the conical sleeve 37, and finally be absorbed and collected by the sponge ring 42, so that the excessive marking paste is prevented from being randomly dropped on the inner wall of the aircraft duct horn, and the later flaw identification is affected. Embodiment three: please refer to Figure 3The embodiment is further illustration of other embodiments, the outer wall of the connecting rod 14 is fixedly provided with the limiting sleeve 16 which is vertically distributed, and the inner part of the limiting sleeve 16 is slidably assembled with the sliding disc 17, the first spring 18 is fixedly arranged between the one end of the sliding disc 17 and the limiting sleeve 16 close to the connecting rod 14, and the other end of the sliding disc 17 is fixedly provided with the stand 19 which is slidably penetrated in the limiting sleeve 16, the one end of the stand 19 away from the sliding disc 17 is also fixedly provided with the cleaning plate 20, the one end surface of the cleaning plate 20 away from the stand 19 is also fixedly bonded with the flexible cleaning strip 21, the limiting sleeve 16 is located at the side close to the laser scanning probe 15, when the laser scanning probe 15 enters the inside of the aircraft conduit horn, the cleaning plate 20 can also enter the inside of the aircraft conduit horn, when the aircraft conduit horn rotates, the flexible cleaning strip 21 can wipe off the impurities and dirt on the inner wall of the aircraft conduit horn, so as to ensure the accuracy of the laser scanning probe 15.

[0027] The one end of the cleaning plate 20 away from the driving part 13 is in the shape of a bent head, through the design of the bent head, the cleaning plate 20 can be directly guided to enter the inside of the aircraft conduit horn, without the need of manually pressing the cleaning plate 20 in advance. Working principle: through the pull rod 5 will be raised after the sliding block 3 and lifting plate 6, the need to be detected aircraft duct horn placed between the two receiving roller 12, so as to release the pull rod 5, under the action of the pull spring 4, can let the rubber roller sleeve 9 will be tightly restricted between the two receiving roller 12 aircraft duct horn, when the motor 7 runs at this time, can let the aircraft duct horn in receiving roller 12 and rubber roller sleeve 9 between the self-rotating, at this time under the action of the driving element 13, through the connecting rod 14 will be gradually extended to the inside of the laser scanning probe 15 aircraft duct horn, with the laser scanning probe 15 gradually into, can let the laser scanning probe 15 all around the aircraft duct horn wall scanning probe processing, at this time the staff can be real-time observation of the aircraft duct horn wall on the computer display, when found a defect site, staff can control the motor 7 and driving element 13 operation, let the defect site in the laser scanning probe 15 probe directly below, at this time stop the motor 7 and driving element 13, through the dial sleeve block 31, make the push rod 30 to seal sleeve 27, in the gear plate 26 and transmission gear 25 cooperation, can let the limit curve plate 23 with the nozzle 24 rotate ninety degrees, the nozzle 24 is transferred to the laser scanning probe 15 directly below, that is, the nozzle 24 port at this time to spray the point of marking color paste, is coincident with the laser scanning probe 15 detection of the defect site, so can mark the defect site accurately, at this time the limit curve plate 23 can't continue to rotate, and in the continuous advancement of the push rod 30, will let the piston disc 28 seal sleeve 27 inside the air through the air pipe 36 input to the inside of the nozzle 24. It should be noted that the rotating column 22 and the outer wall of the laser scanning probe 15 are in shaft-hole rotating cooperation, with small clearance, forming a static friction pair, even if the center of gravity of the limit curve plate 23 deviates from the rotating column 22, the static friction torque is still much larger than the gravity torque (because the assembly pre-tightening force may be artificially increased), ensuring the stability of the limit curve plate 23 when it is not affected by external force.

[0028] The above-mentioned nozzle 24 with swing ninety degrees, before the swing, the inside of the nozzle 24 is filled with marking color paste, and the marking color paste is also adhered to the surface of the plastic valve membrane pressure relief port 38. When the nozzle 24 swings ninety degrees, the marking color paste in the nozzle 24 will be completely gathered into the inside of the storage tank 40 through the curved pipe 39, and a small amount of marking color paste will be adhered to the surface of the plastic valve membrane pressure relief port 38. When the pressure gas is suddenly input into the inside of the nozzle 24, and the pressure in the inside of the nozzle 24 exceeds the pressure threshold of the plastic valve membrane pressure relief port 38, a small amount of marking color paste will be sprayed out at the moment of pressure relief from the plastic valve membrane pressure relief port 38, thereby marking the defect site on the inner wall of the aircraft duct horn, and further facilitating the staff to quickly understand the specific distribution position of the defect when repairing the defect in the later period.

[0029] It is noted that the structure of the plastic valve 38 is similar to the valve jet structure on the "squeezie" bottle cap of a commercially available "squeal" beverage.

[0030] It is to be understood that the terminology used herein such as first and second, and the like, is only used to distinguish one entity or action from another entity or action, and does not necessarily require or imply that there is any such actual relationship or order between such entities or actions. Moreover, the terms "comprising", "including", or any other variation thereof are intended to cover a non-exclusive inclusion, such that a process, method, article, or apparatus that comprises a list of elements does not include only those elements but can also include other elements not expressly listed or inherent to such process, method, article, or apparatus.

[0031] While embodiments of the present application have been shown and described, it is to be understood that the embodiments described are merely divergences, modifications, substitutions and variations of the embodiments and can be made by those skilled in the art without departing from the spirit and principles of the present application, the scope of which is defined by the appended claims and their equivalents.

Claims

1. An apparatus for detecting surface defects of a structure for repairing a composite material of an aircraft, characterized by, The utility model relates to an aircraft conduit horn scanning and marking device, which comprises the following: a work platform (1) and a limiting rack (11) fixed on the upper end face of the work platform (1), and the upper end face of the limiting rack (11) is also provided with two symmetrically distributed supporting rollers (12), an aircraft conduit horn is placed between the two supporting rollers (12), a driving unit is further arranged on the outer side of the limiting rack (11), the driving unit is used to drive the aircraft conduit horn to rotate between the two supporting rollers (12), a driving member (13) is further fixedly arranged on the upper end face of the work platform (1), the output end of the driving member (13) is provided with a connecting rod (14), and the other end of the connecting rod (14) is provided with a laser scanning probe (15) for scanning and projecting the inner wall of the aircraft conduit horn; further comprising: a marking unit for marking the defective position of the inner wall of the aircraft conduit, the marking unit is arranged outside the laser scanning probe (15), and the marking unit comprises a rotating column (22) rotatably arranged on the outer wall of the laser scanning probe (15), a limiting curved plate (23) is fixedly arranged on the outer surface of the rotating column (22), and a spray pipe (24) is fixedly arranged at the end of the limiting curved plate (23) away from the rotating column (22).

2. The structural surface defect detection device for composite material repair of an aircraft according to claim 1, characterized in that: The driving unit comprises a lifting plate (6) and a motor (7) fixed on the upper end face of the lifting plate (6), the lower end face of the lifting plate (6) is rotatably provided with a rotating shaft (8), a rubber roller sleeve (9) is fixedly arranged on the outer surface of the rotating shaft (8), and the output end of the motor (7) is in transmission connection with one end of the rotating shaft (8), and an elastic pressing component is further arranged between the lifting plate (6) and the work platform (1).

3. The structural surface defect detection apparatus for composite material repair of an aircraft according to claim 2, characterized by: The elastic pressing component comprises a limiting sleeve rod (2) fixed on the upper end face of the work platform (1), a sliding block (3) is slidably arranged in the limiting sleeve rod (2), a tension spring (4) is fixedly arranged between the lower end face of the sliding block (3) and the limiting sleeve rod (2), the sliding block (3) is fixed to the lifting plate (6), and a pull rod (5) is fixedly arranged on the upper end face of the sliding block (3) and penetrates through the limiting sleeve rod (2).

4. The structural surface defect detection device for composite material repair of an aircraft according to claim 2, characterized in that: The rotating shaft (8) and the supporting roller (12) are parallel, and the axis of the rotating shaft (8) is the center of symmetry of the two supporting rollers (12).

5. The structural surface defect detection device for composite material repair of an aircraft according to claim 1, characterized in that: The marking unit further comprises a conical sleeve (37) fixed inside the spray pipe (24), and the conical sleeve (37) is located at one end of the spray pipe (24) away from the laser scanning probe (15), the conical top of the conical sleeve (37) extends into the inside of the spray pipe (24), and the conical top of the conical sleeve (37) is fixedly embedded with a plastic valve pressure relief port (38), the outer wall of the spray pipe (24) is fixedly and communicatively provided with a curved pipe (39), and the other end of the curved pipe (39) is fixedly and communicatively provided with a liquid storage tank (40), the butt joint port of the curved pipe (39) and the spray pipe (24) is located on the side of the spray pipe (24) away from the laser scanning probe (15), and the outer portion of the limiting curved plate (23) is provided with a pressure applying component and a turnover component.

6. The structural surface defect detection apparatus for composite material repair of an aircraft according to claim 5, characterized by: The pressure applying component comprises a sliding sleeve block (31) slidingly fitted on the outer surface of the connecting rod (14), the outer portion of the sliding sleeve block (31) is further fixedly provided with a push rod (30), the other end of the push rod (30) is slidingly sleeved with a sealing sleeve (27), and the end of the push rod (30) extending into the inside of the sealing sleeve (27) is further fixedly provided with a piston disc (28) slidingly fitted with the sealing sleeve (27), the end of the sealing sleeve (27) away from the push rod (30) is fixedly and communicatively provided with an air pipe (36) between the end of the spray pipe (24) away from the conical sleeve (37), and the end of the piston disc (28) away from the push rod (30) is fixedly provided with a second spring (29) between the sealing sleeve (27).

7. The apparatus for detecting surface defects of a structure for repairing a composite material of an aircraft according to claim 6, characterized in that: The turnover component comprises a transmission gear (25) fixedly sleeved on the outer surface of the rotating column (22), the outer surface of the sealing sleeve (27) is fixedly provided with a toothed plate (26), and the toothed plate (26) is movably engaged with the transmission gear (25), the outer portion of the toothed plate (26) is fixedly provided with a first baffle (32), and the first baffle (32) is located between the transmission gear (25) and the sealing sleeve (27).

8. The structural surface defect detection apparatus for composite material repair of an aircraft according to claim 6, characterized by: The end of the spray pipe (24) away from the air pipe (36) is fixedly provided with a V-shaped disc (41), and the V-shaped disc (41) and the circular arc wall of the conical sleeve (37) are provided with a storage space, and the inside of the storage space is placed with a sponge ring (42).

9. The structural surface defect detection apparatus for composite material repair of an aircraft according to claim 2, characterized by: The outer wall of the connecting rod (14) is fixedly provided with a limiting sleeve (16) vertically distributed, and the inside of the limiting sleeve (16) is slidingly fitted with a sliding disc (17), the end of the sliding disc (17) close to the connecting rod (14) is fixedly provided with a first spring (18) between the limiting sleeve (16), and the other end of the sliding disc (17) is fixedly provided with a stand (19) slidingly penetrating through the limiting sleeve (16), the end of the stand (19) away from the sliding disc (17) is further fixedly provided with a cleaning plate (20), and the end face of the cleaning plate (20) away from the stand (19) is further fixedly provided with a flexible cleaning strip (21).

10. The apparatus for detecting surface defects of a structure for repairing a composite material of an aircraft according to claim 9, characterized in that: The cleaning plate (20) is provided with a bent head at one end away from the driving member (13).

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