Aircraft structure damage detection device based on machine vision

Abstract

The utility model discloses an aircraft structure damage detection device based on machine vision, which belongs to the technical field of vision detection equipment and comprises a detection main body mounted on the ground, the whole detection main body is of an n-shaped structure, and an electric roller shutter door is arranged on an opening opposite to the detection main body; a plurality of light supplementing lamps are arranged at the upper inner top of the detection main body, and a plurality of irradiation mechanisms are arranged at the lower part of the inner side wall of the detection main body; a plurality of detection mechanisms for flaw detection of the aircraft structure are further arranged on the inner wall of the detection main body in a sliding manner and are uniformly distributed between the two electric roller shutter doors. The n-shaped detection main body is matched with the electric roller shutter door, so that the detection space is prevented from being interfered by external light; the light supplementing lamp on the upper portion is matched with the irradiation mechanisms on the two sides of the lower portion to complete the illumination condition needed during operation in the detection space, finally damage detection of the aircraft structure is completed through the detection mechanism sliding along the inner wall of the detection body, and the accuracy of the detection result can be improved.

Description

Technical Field

[0001] This utility model belongs to the field of visual inspection equipment technology, specifically an aircraft structural damage detection device based on machine vision. Background Technology

[0002] Machine vision flaw detection is a method of damage detection that utilizes machine vision technology. Machine vision technology involves many fields such as artificial intelligence, neurobiology, psychophysics, computer science, image processing, and pattern recognition. It extracts information from images of objective objects by simulating human visual functions through computers, processes and understands it, and ultimately uses it for practical detection, measurement, and control.

[0003] Machine vision flaw detection primarily relies on image acquisition devices (such as CMOS and CCD cameras) to capture images of the object to be inspected, and then transmits these images to a processing unit. The processing unit performs digital processing and, based on information such as pixel distribution, brightness, and color, determines the size, shape, and color of the object, and then uses the results of these determinations to judge whether the object is damaged.

[0004] The machine vision-based aircraft structural damage detection device is a highly efficient and accurate aircraft maintenance tool. This device utilizes machine vision technology, which involves capturing images of the aircraft structure through an image acquisition device and converting them into digital signals for processing and analysis, thereby enabling the detection of whether the aircraft structure is damaged.

[0005] Existing aircraft structural damage detection devices suffer from unstable natural light conditions when detecting damage to aircraft structures, which interferes with the clarity and accuracy of image acquisition and ultimately leads to deviations or misjudgments in the detection results. Utility Model Content

[0006] To address the problem that unstable natural light conditions affect the detection results during aircraft structural damage detection using machine vision, this invention provides an aircraft structural damage detection device based on machine vision.

[0007] This utility model is achieved through the following technical solution:

[0008] The machine vision-based aircraft structural damage detection device includes a detection body installed on the ground. The detection body has a U-shaped structure, and an electric roller shutter door is provided on the opening facing the detection body. When the electric roller shutter door is lowered, it cooperates with the detection body to form a closed detection space. Several supplementary lights are provided on the upper inner top of the detection body, and several illumination mechanisms that provide illumination to the detection space are respectively rotatably provided on the lower part of the inner side wall of the detection body. Multiple detection mechanisms for detecting aircraft structural flaws are also slidably provided on the inner wall of the detection body, and the multiple detection mechanisms are evenly distributed between two electric roller shutter doors.

[0009] The detection main body is matched with the electric roller shutter door, the detection space is avoided from external light interference, the light supplement lamp at the upper portion is matched with the irradiation mechanism at the lower portion, the illumination condition required when working in the detection space is completed, finally, the detection mechanism sliding along the inner wall of the detection main body is used to complete the damage detection of the aircraft structure, and the detection result accuracy is improved.

[0010] Further improvement of the utility model still has, the lower portion of the inner wall of the detection main body is provided with the installation slot that can accommodate the irradiation mechanism.The installation slot recessed on the detection main body can provide the accommodation space for the rotating irradiation mechanism, and the influence caused by the extension of the irradiation mechanism on the aircraft passing through is avoided.

[0011] Further improvement of the utility model still has, the irradiation mechanism includes the rotating pipe that is horizontally rotatably arranged on the inner wall of the detection main body, and the top surface of the rotating pipe is uniformly provided with the irradiation lamp distributed along the axial direction thereof.The sufficient illumination density is provided for the illumination of the detection space.

[0012] Further improvement of the utility model still has, the irradiation mechanism further includes the installation pipe installed on the bottom surface in the installation slot, the axial center line of the installation pipe is perpendicular to the bottom surface in the installation slot, the rotating pipe is integrally in L-shaped structure, the irradiation lamp is installed on the horizontal section of the rotating pipe, and the vertical section bottom of the rotating pipe is rotatably installed on the top of the installation pipe through the fixed ring.The rotating pipe of L-shaped structure carries the illumination lamp and rotates around the installation pipe, and the rotation in and rotation out operation of the illumination lamp in the installation slot is completed.

[0013] Further improvement of the utility model still has, the detection mechanism is slidably arranged in the detection main body through the adjusting mechanism, the adjusting mechanism includes the second electric telescopic column and the fourth electric telescopic column, the second electric telescopic column and the fourth electric telescopic column are horizontally arranged at the top of the two inner walls of the detection main body respectively, and the detection mechanism is detachably installed at the top extension end of the second electric telescopic column and the top extension end of the fourth electric telescopic column.The second electric telescopic column and the fourth electric telescopic column can form the clamping state in cooperation with the detection mechanism, the two telescopic columns form the cooperation state of one extension and one contraction, the stable movement of the detection mechanism in the horizontal direction is formed, and the detection of the top of the aircraft is completed.

[0014] The further improvement of the utility model also has, the above -mentioned adjusting mechanism still includes first electric telescopic column and third electric telescopic column, first electric telescopic column and third electric telescopic column are respectively close to the vertical setting of two inner side walls of detection main part, under the cooperation movement of second electric telescopic column and fourth electric telescopic column, when detection mechanism moves to first electric telescopic column or third electric telescopic column top, by first electric telescopic column or third electric telescopic column ejection and with detection mechanism complete connection, simultaneously operating second electric telescopic column and fourth electric telescopic column action complete the loosening state of detection mechanism, by first electric telescopic column or third electric telescopic column drive detection mechanism complete in vertical direction movement, to realize the both sides and bottom detection of aircraft structure.

[0015] The further improvement of the utility model also has, the above-mentioned detection mechanism includes sliding block, mounting plate, detection rotary motor and detection head, a group of opposite sides of the sliding block are respectively equipped with the first connecting hole that cooperates with second electric telescopic column and fourth electric telescopic column, another opposite side is respectively equipped with the downward extension mounting plate, the detection rotary motor is installed on one mounting plate, and the detection head driven rotation by the output shaft of detected rotary motor is arranged between two mounting plates, the bottom surface of the sliding block of the both sides of detection head is respectively equipped with the second connecting hole that cooperates with first electric telescopic column and third electric telescopic column, the first connecting hole of both sides can be realized respectively with the action end portion connection cooperation of corresponding second electric telescopic column or fourth electric telescopic column, two second connecting holes can realize with the action end portion connection cooperation of first electric telescopic column or third electric telescopic column, under the drive of detection rotary motor, the orientation rotation of detection head is completed.

[0016] The further improvement of the utility model also has, the outside of the above-mentioned mounting plate is equipped with the support plate that detection rotary motor is supported.

[0017] The further improvement of the utility model also has, the sliding groove of the structure of the Chinese character is opened on the inner wall of detection main part, and the first electric telescopic column, second electric telescopic column, third electric telescopic column and fourth electric telescopic column are all arranged in sliding groove, by recessing in the sliding groove of detection main part, it is helpful to reduce the occupation of detection space, avoids the interference influence when airplane enters and exits.

[0018] The further improvement of the utility model also has, the above-mentioned light supplementing lamp is installed at one side of sliding groove, and light supplementing lamp is along the even distribution of second electric telescopic rod movement direction.

[0019] From the above technical scheme can be seen, the beneficial effects of the utility model are: through the cooperation of the detection main body and the electric roller shutter door, the detection space is avoided from external light interference; the light supplement lamp at the upper part and the irradiation mechanism at the lower part complete the illumination condition required when working in the detection space, so that the detection device can provide a stable, controllable and excellent illumination condition environment for the aircraft structure damage detection, thereby ensuring the accuracy and reliability of the detection result.

[0020] The detection mechanism sliding along the inner wall of the detection main body completes the damage detection of the aircraft structure, so that the detection head can perform omnibearing, dead-angle-free scanning and detection on the aircraft structure during the detection process, thereby greatly improving the accuracy and reliability of the detection. BRIEF DESCRIPTION OF DRAWINGS

[0021] In order to more clearly illustrate the technical scheme of the utility model, the following will briefly introduce the drawings needed to be used in the description, and obviously, the drawings in the following description are only some embodiments of the utility model, and for those skilled in the art, other drawings can also be obtained according to these drawings without creative labor.

[0022] Figure 1 It is the overall view of the embodiment of the utility model;

[0023] Figure 2 It is the side view of the embodiment of the utility model;

[0024] Figure 3 It is the structure schematic view of the embodiment of the utility model;

[0025] Figure 4 It is the first schematic view of the half planing structure of the embodiment of the utility model;

[0026] Figure 5 It is the second schematic view of the half planing structure of the embodiment of the utility model;

[0027] Figure 6 It is the structure schematic view of the embodiment of the utility model.

[0028] In the drawings: 100, detection main body; 101, through hole; 200, moving groove; 300, electric roller shutter door; 400, mounting groove; 500, irradiation mechanism; 501, mounting pipe; 502, fixed ring; 503, rotating pipe; 504, irradiation lamp; 600, adjusting mechanism; 601, sliding groove; 602, first electric telescopic column; 603, second electric telescopic column; 604, third electric telescopic column; 605, fourth electric telescopic column; 6051, cylindrical sliding rail part; 6052, annular sliding block part; 606, light supplementing lamp; 700, detection mechanism; 701, sliding block; 702, first connecting hole; 703, mounting plate; 704, second connecting hole; 705, detection rotating motor; 706, support plate; 707, detection head. DETAILED DESCRIPTION

[0029] In order to make the purpose, characteristics and advantages of the utility model more obvious and easy to understand, the technical scheme in the utility model will be described clearly and completely in combination with the drawings in the specific embodiment below. Obviously, the following described embodiments are only part of the embodiments of the utility model, rather than all the embodiments. Based on the embodiments in the patent, all other embodiments obtained by the person skilled in the art without creative labor belong to the scope of protection of the patent.

[0030] As Figures 1-6As shown, the machine vision-based aircraft structure damage detection device comprises a detection main body 100 installed on the ground, the detection main body 100 is in the shape of a rectangle, and an electric roller shutter door 300 is arranged on the opening of the detection main body 100, and the electric roller shutter door 300 falls to cooperate with the detection main body 100 to form a closed detection space; a moving groove 200 vertically arranged and cooperating with the electric roller shutter door 300 is arranged on the two inner side walls of the detection main body 100 to form a moving track of the electric roller shutter door 300. A plurality of light supplementing lamps 606 are arranged on the upper inner top of the detection main body 100, and a plurality of irradiation mechanisms 500 for providing illumination for the detection space are rotatably arranged on the lower part of the inner side wall of the detection main body 100; a plurality of detection mechanisms 700 for aircraft structure detection are slidably arranged on the inner wall of the detection main body 100, and the plurality of detection mechanisms 700 are uniformly distributed between the two electric roller shutter doors 300. The detection mechanism 700 comprises a sliding block 701, a mounting plate 703, a detection rotating motor 705 and a detection head 707; a mounting plate 703 extending downward is arranged on each of the opposite sides of the sliding block 701, the detection rotating motor 705 is mounted on one of the mounting plates 703, and a support plate 706 supporting the detection rotating motor 705 is arranged outside the mounting plate 703; the detection head 707 driven to rotate by the output shaft of the detection rotating motor 705 is arranged between the two mounting plates 703. Under the drive of the detection rotating motor 705, the orientation rotation of the detection head 707 is completed to cooperate with the movement of the detection mechanism 700 along the inner wall of the detection main body 100 to detect the aircraft structure.

[0031] As shown in the drawings, Figures 4-6 A sliding groove 601 in the shape of a rectangle is arranged on the inner wall of the detection main body 100, the detection mechanism 700 is slidably arranged in the detection main body 100 through an adjusting mechanism 600, and the adjusting mechanism 600 is arranged in the sliding groove 601. The sliding groove 601 recessed in the detection main body 100 helps to reduce the occupation of the detection space and avoid the interference influence when the aircraft enters and exits. The adjusting mechanism 600 comprises a second electric telescopic column 603 and a fourth electric telescopic column 605, the second electric telescopic column 603 and the fourth electric telescopic column 605 are horizontally arranged at the top of the sliding groove 601 and connected with the two inner side walls respectively, and the detection mechanism 700 is detachably mounted on the top extension end of the second electric telescopic column 603 and the top extension end of the fourth electric telescopic column 605. The second electric telescopic column 603 and the fourth electric telescopic column 605 can cooperate with the detection mechanism 700 to form a clamping state, and the two telescopic columns form a cooperation state of one extension and one contraction, so that the detection mechanism 700 moves stably in the horizontal direction to complete the detection of the top of the aircraft.

[0032] As shown in the drawings, Figure 5As shown, specifically, the second electric telescopic column 603 and the fourth electric telescopic column 605 are both cylindrical linear guide rails, wherein the cylindrical linear guide rail comprises a ring-shaped slider portion 6052 and a cylindrical rail portion 6051 matched with the ring-shaped slider portion 6052, the ring-shaped slider portion 6052 is installed in the sliding groove 601 and close to the inner side wall of the detection main body 100, the side wall of the detection main body 100 is provided with a through hole 101 allowing the cylindrical rail portion 6051 to move outwards, and a linear bearing matched with the cylindrical rail portion 6051 and a sealing ring are sequentially arranged in the through hole 101 from inside to outside; the linear bearing forms a guide support for the cylindrical rail portion 6051, and the sealing ring helps to avoid light from entering the detection space through the through hole.

[0033] As shown in Figure 5 The adjusting mechanism 600 further comprises a first electric telescopic column 602 and a third electric telescopic column 604, which are respectively arranged in the vertical section of the sliding groove 601. When the detection mechanism 700 moves above the first electric telescopic column 602 or the third electric telescopic column 604 under the cooperation of the second electric telescopic column 603 and the fourth electric telescopic column 605, the first electric telescopic column 602 or the third electric telescopic column 604 is ejected and connected with the detection mechanism 700, and the second electric telescopic column 603 and the fourth electric telescopic column 605 are operated to complete the loosening state of the detection mechanism 700, the detection mechanism 700 is moved in the vertical direction by the first electric telescopic column 602 or the third electric telescopic column 604, so as to realize the detection of the two side parts and the bottom part of the aircraft structure.

[0034] As shown in Figure 6 The mounting plate 703 is provided with a first connecting hole 702 matched with the second electric telescopic column 603 and the fourth electric telescopic column 605 on the side surface of the sliding block 701 adjacent to the mounting plate 703, and is provided with a downwardly extending mounting plate 703 on the other opposite side surface, the detection rotating motor 705 is installed on one of the mounting plates 703, and the second connecting hole 704 matched with the first electric telescopic column 602 and the third electric telescopic column 604 is arranged on the bottom surface of the sliding block 701 on both sides of the detection head 707. The first connecting hole 702 on both sides can be connected and matched with the action end of the corresponding second electric telescopic column 603 or fourth electric telescopic column 605; the two second connecting holes 704 can be connected and matched with the action end of the first electric telescopic column 602 or the third electric telescopic column 604.

[0035] As shown in Figures 1-3As shown, the lower part of the inner wall of the detection body 100 is provided with a mounting groove 400 capable of accommodating the irradiation mechanism 500. The mounting groove 400 recessed on the detection body 100 can provide a storage space for the rotating irradiation mechanism 500, avoiding the influence of the extension of the irradiation mechanism 500 on the passing aircraft. The irradiation mechanism 500 comprises a rotating pipe 503 horizontally arranged on the inner wall of the detection body 100, and the top surface of the rotating pipe 503 is uniformly provided with irradiation lamps 504 distributed along the axial direction. The irradiation mechanism 500 further comprises a mounting pipe 501 mounted on the bottom surface of the mounting groove 400, and the axis of the mounting pipe 501 is perpendicular to the bottom surface of the mounting groove 400. The rotating pipe 503 is in an L-shaped structure as a whole, the irradiation lamps 504 are mounted on the horizontal section of the rotating pipe 503, and the vertical section of the rotating pipe 503 is rotatably mounted on the top of the mounting pipe 501 through a fixing ring 502. The rotating pipe 503 in the L-shaped structure carries the irradiation lamps to rotate around the mounting pipe 501, and the rotating in and out operation of the irradiation lamps in the mounting groove 400 is completed.

[0036] As shown in the drawings, Figures 4-5 The light supplement lamp 606 is mounted on one side of the sliding groove 601, and the light supplement lamp 606 is uniformly distributed along the moving direction of the second electric telescopic rod.

[0037] The aircraft structure damage detection device based on machine vision, by cooperating with the electric roller shutter door through the detection body in the L-shaped structure, realizes the detection space avoiding the external light interference; the upper light supplement lamp and the lower two sides of the irradiation mechanism cooperate to complete the illumination condition required when working in the detection space, so that the detection device can provide a stable, controllable and excellent illumination condition for the aircraft structure damage detection, thereby ensuring the accuracy and reliability of the detection result.

[0038] The detection mechanism sliding along the inner wall of the detection body completes the damage detection of the aircraft structure, so that the detection head can perform omnidirectional and dead-angle-free scanning and detection on the aircraft structure during the detection process, thereby greatly improving the accuracy and reliability of the detection.

[0039] The embodiments in the specification are described in a progressive manner, and each embodiment focuses on the difference from other embodiments. The same or similar parts of each embodiment can be referred to each other.

[0040] The terms "upper", "lower", "outer" "inner" and the like in the description and the claims of the present utility model and the above drawings, if any, are used to distinguish relative positions, and do not have to be given a nature. It should be understood that the data thus used can be interchanged under appropriate circumstances, so that the embodiments of the present utility model described herein can be implemented in an order other than those illustrated or described herein. In addition, the terms "include" and "have" and any variations thereof are intended to cover non-exclusive inclusion.

[0041] The above description of disclosed embodiments enables those skilled in the art to carry out or use the present utility model. Various modifications to these embodiments will be apparent to those skilled in the art, and the general principles defined herein can be implemented in other embodiments without departing from the spirit or scope of the present utility model. Therefore, the present utility model will not be limited to these embodiments shown herein, but will conform to the widest scope consistent with the principles and novel features disclosed herein.

Claims

1. An apparatus for detecting damage of an aircraft structure based on machine vision, comprising a detection main body (100) installed on the ground, characterized in that, The detection main body (100) is in the shape of a square, and the opening of the detection main body (100) is provided with an electric roller shutter door (300), which falls to cooperate with the detection main body (100) to form a closed detection space; the upper inner top of the detection main body (100) is provided with a plurality of light supplement lamps (606), and the lower part of the inner side wall of the detection main body (100) is respectively provided with a plurality of irradiation mechanisms (500) for providing illumination for the detection space; the inner wall of the detection main body (100) is also slidably provided with a plurality of detection mechanisms (700) for detecting the structure of the aircraft, and the plurality of detection mechanisms (700) are evenly distributed between the two electric roller shutter doors (300).

2. The machine vision based aircraft structure damage detection apparatus of claim 1, wherein, The lower part of the inner side wall of the detection main body (100) is provided with a mounting groove (400) capable of accommodating the irradiation mechanism (500).

3. The machine vision-based aircraft structure damage detection apparatus of claim 2, wherein, The irradiation mechanism (500) comprises a rotating pipe (503) horizontally arranged on the inner wall of the detection main body (100), and the top surface of the rotating pipe (503) is evenly provided with irradiation lamps (504) distributed along the axial direction.

4. The machine vision-based aircraft structure damage detection apparatus of claim 3, wherein, The irradiation mechanism (500) further comprises a mounting pipe (501) mounted on the inner bottom surface of the mounting groove (400), and the axis of the mounting pipe (501) is perpendicular to the inner bottom surface of the mounting groove (400); the rotating pipe (503) is in the shape of an L, the irradiation lamps (504) are mounted on the horizontal section of the rotating pipe (503), and the vertical section of the rotating pipe (503) is rotatably mounted on the top of the mounting pipe (501) through a fixing ring (502).

5. The machine vision-based aircraft structure damage detection apparatus according to any one of claims 1 to 4, characterized by, The detection mechanism (700) is slidably arranged in the detection main body (100) through an adjusting mechanism (600); the adjusting mechanism (600) comprises a second electric telescopic column (603) and a fourth electric telescopic column (605), and the second electric telescopic column (603) and the fourth electric telescopic column (605) are respectively arranged horizontally on the top of the two inner side walls of the detection main body (100), and the detection mechanism (700) is detachably mounted on the top extension end of the second electric telescopic column (603) and the top extension end of the fourth electric telescopic column (605).

6. The machine vision-based aircraft structure damage detection apparatus of claim 5, wherein, The adjusting mechanism (600) further comprises a first electric telescopic column (602) and a third electric telescopic column (604), and the first electric telescopic column (602) and the third electric telescopic column (604) are respectively arranged vertically near the two inner side walls of the detection main body (100).

7. The machine vision-based aircraft structure damage detection apparatus of claim 6, wherein, The detection mechanism (700) comprises a sliding block (701), a mounting plate (703), a detection rotating motor (705) and a detection head (707); a group of opposite sides of the sliding block (701) are respectively provided with first connecting holes (702) matched with the second electric telescopic column (603) and the fourth electric telescopic column (605), and the other opposite side is respectively provided with the downwardly extending mounting plate (703), the detection rotating motor (705) is mounted on one of the mounting plates (703), and the detection head (707) driven to rotate by an output shaft of the detection rotating motor (705) is arranged between the two mounting plates (703); the bottom surfaces of the sliding blocks (701) on both sides of the detection head (707) are respectively provided with second connecting holes (704) matched with the first electric telescopic column (602) and the third electric telescopic column (604).

8. The machine vision-based aircraft structure damage detection apparatus of claim 7, wherein, The outer side of the mounting plate (703) is provided with a support plate (706) supporting the detection rotating motor (705).

9. The machine vision-based aircraft structure damage detection apparatus of claim 6, wherein, The inner wall of the detection main body (100) is provided with a sliding groove (601) in the shape of a Chinese character, and the first electric telescopic column (602), the second electric telescopic column (603), the third electric telescopic column (604) and the fourth electric telescopic column (605) are arranged in the sliding groove (601).

10. The machine vision-based aircraft structure damage detection apparatus of claim 9, wherein, The light supplement lamp (606) is mounted on one side of the sliding groove (601), and the light supplement lamp (606) is uniformly distributed along the moving direction of the second electric telescopic column.

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