Airplane hub detection equipment

Abstract

The utility model provides airplane hub detection equipment and a visual positioning detection method thereof. The airplane hub detection equipment comprises a rack; the fastening device comprises a limiting base arranged on the machine frame, a fastening chuck is arranged in the limiting base and driven by a servo motor arranged at the bottom of the machine frame, a clamping jaw set is arranged on the fastening chuck, a corresponding lifting platform is arranged on the limiting base in a sliding mode, and a clamping jaw is arranged on the clamping jaw set. A through groove corresponding to the clamping jaw group is formed in the lifting platform; the visual positioning device comprises a lifting mechanism arranged on the rack, and the lifting mechanism is connected with a positioning recognition module located above the lifting platform; the flaw detection device comprises a mechanical arm arranged on the rack, a detachable detection probe assembly is arranged on the mechanical arm, and even if the aircraft hub is large in size and heavy in weight, the fastening effect of the aircraft hub can be conveniently achieved through a fastening device arranged on the rack; according to the utility model, a visual positioning device is arranged on the rack, so that the positioning is accurate, and an automatic mechanical arm can conveniently carry out the displacement detection of the probe.

Description

Technical Field

[0001] The utility model relates to aircraft wheel hub detection equipment, which is applied to the field of aircraft wheel hub detection. Background Art

[0002] Aircraft wheel inspection equipment is a non-destructive testing (NDT) technology that utilizes eddy current testing, a technique based on electromagnetic principles, to evaluate surface and subsurface defects in conductive materials, such as aluminum alloy aircraft wheels. This technology, crucial for ensuring aircraft flight safety, is typically used in conjunction with ultrasonic testing (UT) and eddy current testing (ET).

[0003] Due to its special structural characteristics, such as large size, heavy weight, and inner and outer rings and inner ring groove surfaces, aircraft wheel hubs face some challenges in automated inspection. Specifically, there are two main problems: (1) Fixing problem: Due to the size and weight of the aircraft wheel hub, existing inspection equipment has inconvenience in fixing the wheel hub, which affects the efficiency and safety of the inspection process. (2) Positioning and movement problem: Although the probe can be moved for inspection by an automated robotic arm, the current positioning accuracy of the aircraft wheel hub is insufficient, which easily leads to probe movement errors, which may not only damage the probe but also scratch the wheel hub surface. In order to solve these problems, the utility model proposes an aircraft wheel hub inspection device. This method aims to improve the convenience of fixing the aircraft wheel hub and the positioning accuracy of the probe during the automated inspection process through improved design, thereby reducing the risk of probe damage and wheel hub damage, and improving the automation level and accuracy of the inspection. In short, the utility model optimizes the inspection process of the aircraft wheel hub through visual positioning technology, and improves the efficiency and reliability of the entire inspection system. Utility Model Content

[0004] The utility model provides an aircraft wheel hub detection device, which can effectively solve the above problems.

[0005] The utility model is achieved in this way:

[0006] An aircraft wheel hub detection device, comprising:

[0007] frame;

[0008] The fastening device includes a limit base provided on the frame, a fastening chuck provided in the limit base, the fastening chuck being driven by a servo motor provided at the bottom of the frame, a clamping claw group provided on the fastening chuck, a corresponding lifting platform slidably provided on the limit base, a through slot corresponding to the clamping claw group provided on the lifting platform, and when the lifting platform descends to the minimum limit height, the clamping claw group passes through the through slot and clamps and fastens the aircraft wheel hub;

[0009] The visual positioning device includes a lifting mechanism provided on a frame, wherein the lifting mechanism is connected to a positioning recognition module located above the lifting platform;

[0010] The detection and flaw detection device includes a mechanical arm arranged on a frame, and a detachable detection probe assembly is provided on the mechanical arm. When the servo motor drives the fastening chuck to drive the aircraft wheel hub to rotate, the mechanical arm controls the detection probe assembly to perform flaw detection on the aircraft wheel hub.

[0011] The lifting platform is driven by a plurality of first cylinders arranged on a frame. A plurality of rollers are arranged on the lifting platform, and the rollers roll along the Y-axis direction.

[0012] A plurality of slide grooves are formed in a circular array on the top of the fastening chuck, and the clamping jaw group includes a long strip slider slidably arranged in the slide groove, and a plurality of positioning blocks are provided in a path array on the long strip slider. A first motor is provided in the limit base, and the first motor drives the strip slider to retract / expand; when the aircraft wheel hub is placed on the lifting platform, two adjacent positioning blocks on the strip slider fix the bottom edge of the aircraft wheel hub, and the strip slider is driven to retract / expand by the first motor, thereby fixing the aircraft wheel hub.

[0013] A material sensor is provided at the bottom of one of the strip-shaped sliding blocks.

[0014] The lifting mechanism includes several positioning optical axes vertically arranged on the frame, and an optical axis slider is slidably arranged on the positioning optical axis. The optical axis slider is driven by a second cylinder vertically arranged on the frame. A positioning identification module is provided on the optical axis slider, and the positioning identification module includes a first mounting bracket arranged on the optical axis slider. A camera module is provided on the first mounting bracket, and the focusing point of the camera module is aligned with the center of the fastening chuck.

[0015] The robotic arm is provided with a first mounting portion, the first mounting portion is provided with a pressure sensor, the detection probe assembly includes a second mounting portion detachably connected to the first mounting portion, the first mounting portion is connected to the second mounting portion to thereby fix the detection probe assembly, the second mounting portion is connected to a second mounting bracket, the second mounting bracket is provided with a guide rail along the axial direction of the mounting portion, the guide rail is provided with a mounting slider, the mounting slider is fixed with a probe mounting bracket, and the probe mounting bracket is fixed with a detection probe.

[0016] The frame is equipped with a quick-change platform, on which a number of detection probe assemblies of different specifications are arranged.

[0017] A standard sample fixing platform is provided on the frame, and a plurality of standard samples with different defect sizes are provided on the standard sample fixing platform.

[0018] The beneficial effect of the present invention is that although the aircraft wheel hub is difficult to operate due to its large size and weight, the present invention can easily achieve stable fixation of the aircraft wheel hub by installing a specific fastening device on the detection frame. By placing the aircraft wheel hub on a lifting platform with adjustable height and lowering the platform to the lowest point, the clamping claw group is used to firmly clamp the wheel hub through the through slot, thereby ensuring its stability during the detection process. In addition, the present invention also includes a visual positioning device, which can ensure the precise positioning of the aircraft wheel hub. This precise positioning mechanism is crucial for automated robotic arms because it allows the robotic arm to accurately control the movement path of the probe and perform efficient detection work. Through this design, the problem of probe damage or hub surface damage caused by inaccurate positioning can be effectively avoided. In short, the present invention not only simplifies the aircraft wheel hub fixing process through the fixing and visual positioning devices on the frame, but also improves the accuracy and safety of automated detection, thereby optimizing the entire detection process. BRIEF DESCRIPTION OF THE DRAWINGS

[0019] In order to more clearly illustrate the technical solutions of the embodiments of the present invention, the following is a brief introduction to the drawings required for use in the embodiments. It should be understood that the following drawings only show certain embodiments of the present invention and therefore should not be regarded as limiting the scope. For ordinary technicians in this field, other relevant drawings can be obtained based on these drawings without creative work.

[0020] Figure 1 It is a structural diagram provided by an embodiment of the present utility model.

[0021] Figure 2 It is a structural schematic diagram of a fastening device and a flaw detection device provided by an embodiment of the utility model.

[0022] Figure 3 The embodiment of the present utility model provides Figure 2 Schematic diagram of the locally enlarged structure at point A.

[0023] Figure 4 It is a schematic diagram of the exploded structure of the fastening device provided in an embodiment of the utility model.

[0024] Figure 5 It is a structural schematic diagram of the visual positioning device provided by an embodiment of the utility model.

[0025] The accompanying drawings are identified as follows:

[0026] 10. Rack;

[0027] 20. Fastening device; 21. Positioning base; 22. Fastening chuck; 221. Slide; 222. Long slider; 223. Positioning block; 224. First motor; 225. Material sensor; 2251. Third mounting bracket; 23. Servo motor; 24. Gripping jaw assembly; 25. Lifting platform; 251. Roller;

[0028] 30. Visual positioning device; 31. Lifting mechanism; 311. Positioning optical axis; 312. Optical axis slider; 313. Second cylinder; 32. Positioning recognition module; 321. First mounting bracket; 322. Camera module;

[0029] 40. Detection and flaw detection device; 41. Robotic arm; 411. First mounting portion; 412. Pressure sensor; 42. Detection probe assembly; 421. Second mounting portion; 422. Second mounting bracket; 423. Guide rail; 424. Mounting slide; 425. Probe mounting bracket; 426. Detection probe;

[0030] 50. Quick change platform;

[0031] 60. Standard sample fixing table; 61. Standard sample;

[0032] 70. Aircraft wheels;

[0033] 80. Safety guardrail; 81. Safety grating;

[0034] 90. Visual display;

[0035] 100. Check the display. DETAILED DESCRIPTION

[0036] In order to make the purpose, technical solutions and advantages of the embodiments of the present invention clearer, the technical solutions in the embodiments of the present invention will be clearly and completely described below in conjunction with the drawings in the embodiments of the present invention. Obviously, the described embodiments are part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without making creative work are within the scope of protection of the present invention. Therefore, the following detailed description of the embodiments of the present invention provided in the drawings is not intended to limit the scope of the utility model for which protection is claimed, but merely represents selected embodiments of the present invention.

[0037] In the description of this utility model, the terms "first" and "second" are used for descriptive purposes only and should not be understood to indicate or imply relative importance or implicitly specify the number of the technical features indicated. Therefore, a feature specified as "first" or "second" may explicitly or implicitly include one or more of such features. In the description of this utility model, "plurality" means two or more, unless otherwise specifically specified.

[0038] Reference Figure 1 As shown, an aircraft wheel hub detection device includes a frame 10, and a safety guardrail is provided on the frame 10. The side wall of the safety guardrail 80 is also provided with a safety grating 81. The safety guardrail 80 and the safety grating 81 can effectively protect the installation of the operator. A visual display 90 and its keyboard assembly are also provided on one side of the safety guardrail 80. The positioning status of the visual positioning device 30 can be clearly viewed through the visual display 90. A detection display 100 and its keyboard assembly are provided on the other side of the safety guardrail 80. The detection status can be viewed in real time through the detection display 100. The frame 10 also includes a fastening device 20 for fixing the aircraft wheel hub 70; the visual positioning device 30 cooperates with the fastening device 20 to achieve precise positioning of the aircraft wheel hub 70, and a detection device 40 for performing flaw detection on the aircraft wheel hub. A quick-change platform 50 is also installed on the frame 10, and the quick-change platform 50 is provided with a plurality of detection probe assemblies 42 of different specifications. A standard sample fixing platform 60 is provided on the frame 10 , and a plurality of standard samples 61 with different defect sizes are provided on the standard sample fixing platform 60 .

[0039] Reference Figures 2-4 As shown, the fastening device 20 includes a limiting base 21 provided on the frame 10. The limiting base 21 is rectangular in shape. A fastening chuck 22 is provided in the limiting base 21. The fastening chuck 22 is driven by a servo motor 23 provided at the bottom of the frame 10. A clamping claw group 24 is provided on the fastening chuck 22. A corresponding lifting platform 25 is slidably provided on the limiting base 21. The lifting platform 25 is driven by a plurality of first cylinders provided on the frame 10 (not shown in the figure). In this embodiment, there are four first cylinders. Since the movement of the lifting platform 25 driven by the cylinder is a prior art, it will not be described in detail here. The lifting platform 25 is provided with a plurality of rollers 251, which roll along the Y-axis direction. By moving the rollers 251 in one direction, the aircraft wheel hub 70 can be moved, and the poor stability caused by the universal rollers can also be prevented. The lifting platform 25 is provided with a through slot corresponding to the clamping claw group 24. When the lifting platform 25 is lowered to the lowest limit height, the clamping claw group 24 passes through the through slot and clamps and fastens the aircraft wheel hub 70.

[0040] Reference Figure 5As shown, the visual positioning device 30 includes a lifting mechanism 31 provided on the frame 10, the lifting mechanism 31 includes a plurality of positioning optical axes 311 vertically provided on the frame 10, an optical axis slider 312 is slidingly provided on the positioning optical axis 311, the optical axis slider 312 is driven by a second cylinder 313 vertically provided on the frame 10, a positioning identification module 32 is provided on the optical axis slider 312, the positioning identification module includes a first mounting bracket 321 provided on the optical axis slider 312, a camera module 322 is provided on the first mounting bracket 321, the focusing point of the camera module 322 is aligned with the center of the fastening chuck 22, which can improve the positioning accuracy of the aircraft wheel hub 70.

[0041] Reference Figures 2-4 As shown, the flaw detection device 40 includes a robotic arm 41 mounted on the frame 10. In this embodiment, the robotic arm 41 is a six-axis robotic arm, a type of robotic arm with six rotational degrees of freedom that can simulate the complex movements of a human arm. This type of robotic arm is widely used in industrial automation, assembly, packaging, painting, welding, and handling, and is favored for its flexibility and precision. The robotic arm 41 is equipped with a detachable detection probe assembly 42. When the servo motor 23 drives the fastening chuck 22 to rotate the aircraft wheel hub 70, the robotic arm 41 controls the detection probe assembly 42 to perform flaw detection on the aircraft wheel hub 70.

[0042] As a further improvement, the robotic arm 41 is provided with a first mounting portion 411, the first mounting portion 411 is provided with a pressure sensor 412, the detection probe assembly 42 includes a second mounting portion 421 detachably connected to the first mounting portion 411, the first mounting portion 411 is connected to the second mounting portion 421 to thereby fix the detection probe assembly 42, the second mounting portion 421 is connected to a second mounting bracket 422, the second mounting bracket 422 is provided with a guide rail 423 along the axial direction of the mounting portion, the guide rail 423 is provided with a mounting slider 424, the mounting slider 424 is fixed with a probe mounting bracket 425, and the probe mounting bracket 425 is fixed with a detection probe 426.

[0043] A plurality of slide grooves 221 are provided in a circular array on the top of the fastening chuck 22. In the present embodiment, there are four slide grooves 221. The clamping jaw group 24 includes a long strip slider 222 slidably arranged in the slide groove 221. A plurality of positioning blocks 223 are provided in a path array on the long strip slider 222. A first motor 224 is provided in the limiting base 21, and the first motor 224 drives the strip slider to retract / expand. When the aircraft wheel hub 70 is placed on the lifting platform 25, two adjacent positioning blocks 223 on the strip slider fix the bottom edge of the aircraft wheel hub 70, and the strip slider is driven to retract / expand by the first motor 224, thereby fixing the aircraft wheel hub 70.

[0044] A material sensor 225 is provided at the bottom of one of the elongated sliders 222. A third mounting bracket 2251 is provided on the limiting base 21 at the bottom of the strip slider 222. The material sensor 225 is provided on the third mounting bracket 2261. When the aircraft wheel hub 70 is fixed to the clamping jaw assembly 24, due to the heavy weight of the aircraft wheel hub 70, the fastening chuck 22 (the fastening chuck 22 is provided with a buffer device) is pressed down to a certain extent, causing the elongated slider 222 to touch the material sensor 225, thereby sensing the installation and fixation of the aircraft wheel hub and providing an electrical signal to the robotic arm 41 for detection.

[0045] Reference Figures 1 to 5 As shown, a method for visually locating and detecting an aircraft wheel hub 70 includes the following steps:

[0046] S10: Select the preset workpiece model program and enter the operation preparation;

[0047] S20: The lifting platform 25 moves to the initial position, the aircraft wheel hub 70 is placed on the lifting platform 25, and the positioning recognition module 32 is used to determine whether the aircraft wheel hub 70 is consistent with the set model and whether the position center is within the specified range;

[0048] If it is determined that the aircraft wheel hub 70 is consistent with the set model and the position center is within the specified range, step S30 is executed, otherwise an alarm is issued and the aircraft is shut down;

[0049] S30: The lifting platform 25 moves downward, fixes the aircraft wheel hub 70 through the clamping claw assembly 24 and rotates the fastening chuck 22;

[0050] S40: The flaw detection device 40 performs eddy current / ultrasonic testing on the aircraft hub 70 according to a preset program.

[0051] Since the aircraft wheel hub needs to bear a weight of more than 100 tons during landing, taking the Boeing 737-300 passenger aircraft as an example, its single tire load is 15,060 kg, the outer diameter is 1 meter, and the weight is 70 kg, which is equivalent to the weight of an adult. Therefore, a lifting mechanism (not shown) is required to assist during loading. During the positioning process, the aircraft wheel hub 70 is set on the lifting platform 25 and is difficult to move. Therefore, it is necessary to use the rollers on the lifting platform 25 to assist in movement. If universal rollers are used to assist in movement, the stability of the aircraft wheel hub 70 during the fixing process may be poor. Therefore, the present invention only provides rollers that move along the Y-axis. In order to prevent frequent movement of the aircraft wheel hub 70, the present invention first limits its position in the X-axis direction during loading, which facilitates loading and improves positioning accuracy. As a further improvement, the steps of placing the aircraft wheel hub 70 on the lifting platform 25 and determining whether the aircraft wheel hub 70 is consistent with the set model and whether the position center is within the specified range through the positioning recognition module 32 further include the following steps:

[0052] S21: The aircraft wheel hub 70 is placed on the side of the lifting platform 25 by the lifting mechanism, and is ready to enter the lifting platform 25;

[0053] S22: Controlling the positioning and recognition module 32 to move to a first recognition distance H1 from the lifting platform 25. The first recognition distance H1 is 0.7 to 1 meter. The purpose is to enable the positioning and recognition module 32 to effectively recognize the outline of the aircraft wheel hub located outside the lifting platform 25 at this distance height, and then predict the movement path of the aircraft wheel hub 70 along the Y-axis direction through the positioning and recognition module 32.

[0054] S23: Determine whether the center of the moving path is consistent with the center of the fastening chuck 22. If so, proceed to step S24. Otherwise, an alarm is triggered. When an alarm is triggered, the position of the aircraft wheel hub 70 along the X-axis direction is adjusted by the jacking mechanism until the alarm signal disappears, that is, whether the center of the moving path is consistent with the center of the fastening chuck 22.

[0055] S24: Manually move the aircraft wheel hub 70 along the Y-axis direction via the roller 251 to a position close to the center of the fastening chuck 22;

[0056] S25: Control the positioning and recognition module 32 to move to a second recognition distance H2 (H1>H2) from the lifting platform 25 to determine the model of the aircraft wheel hub 70. If the model of the aircraft wheel hub 70 is consistent with the pre-set workpiece model, the process proceeds to S26; otherwise, an alarm is issued and the machine is shut down.

[0057] In this embodiment, the second identification distance is 0.5 to 0.7 meters. The purpose is to enable the positioning and identification module 32 to increase the depth of field of the camera module 322 at this distance and height, and then by adjusting the aperture and focal length, a clearer outline of the aircraft wheel hub 70 can be captured. Since the present invention determines whether the center of the aircraft wheel hub 70 is within a specified range by identifying whether the outline of the aircraft wheel hub 70 and the outline of the fastening chuck are concentric, a clear photo of the aircraft wheel hub 70 is required. Because the aircraft wheel hub 70 is a rotating body with many contour lines, if the photo is not clear when photographing from a bird's-eye view, it may lead to failure or error in contour line recognition, resulting in false alarms and affecting the detection efficiency of the equipment.

[0058] S26: Determine whether the position center of the aircraft wheel hub 70 is within a specified range through the positioning recognition module 32. If the position center of the aircraft wheel hub 70 is within the specified range, enter S30; otherwise, an alarm is generated.

[0059] The above description is merely a preferred embodiment of the present invention and is not intended to limit the present invention. Those skilled in the art will readily appreciate that the present invention is susceptible to various modifications and variations. Any modifications, equivalent substitutions, or improvements made within the spirit and principles of the present invention shall be included within the scope of protection of the present invention.

Claims

1. An aircraft wheel hub detection device, characterized in that: include: Frame (10); The fastening device (20) comprises a limiting base (21) provided on a frame (10), a fastening chuck (22) being provided in the limiting base (21), the fastening chuck (22) being driven by a servo motor (23) provided at the bottom of the frame (10), a clamping claw group (24) being provided on the fastening chuck (22), a corresponding lifting platform (25) being slidably provided on the limiting base (21), a through slot corresponding to the clamping claw group (24) being provided on the lifting platform (25), and when the lifting platform (25) descends to a minimum limiting height, the clamping claw group (24) passes through the through slot and clamps and fastens the aircraft wheel hub (70); A visual positioning device (30) includes a lifting mechanism (31) provided on a frame (10), wherein the lifting mechanism (31) is connected to a positioning recognition module (32) located above a lifting platform (25); The flaw detection device (40) comprises a mechanical arm (41) arranged on a frame (10), wherein a detachable detection probe assembly (42) is provided on the mechanical arm (41). When a servo motor (23) drives a fastening chuck (22) to drive an aircraft wheel hub (70) to rotate, the mechanical arm (41) controls the detection probe assembly (42) to perform flaw detection on the aircraft wheel hub (70).

2. The aircraft wheel hub detection device according to claim 1, characterized in that: The lifting platform (25) is driven by a plurality of first cylinders arranged on the frame (10). A plurality of rollers (251) are arranged on the lifting platform (25), and the rollers (251) roll along the Y-axis direction.

3. The aircraft wheel hub detection device according to claim 2, characterized in that: The top annular array of the fastening chuck (22) is provided with a plurality of slide grooves (221); the clamping jaw group (24) includes a long strip slider (222) slidably arranged in the slide groove (221); a plurality of positioning blocks (223) are arranged in a path array on the long strip slider (222); a first motor (224) is provided in the limiting base (21); the first motor (224) drives the strip slider to retract / expand; when the aircraft wheel hub (70) is placed on the lifting platform (25), two adjacent positioning blocks (223) on the strip slider fix the bottom edge of the aircraft wheel hub (70), and the strip slider is driven to retract / expand by the first motor (224), thereby fixing the aircraft wheel hub (70).

4. The aircraft wheel hub detection device according to claim 3, characterized in that: A material sensor (225) is provided at the bottom of one of the strip-shaped sliding blocks.

5. The aircraft wheel hub detection device according to claim 1, characterized in that: The lifting mechanism (31) includes a plurality of positioning optical axes (311) vertically arranged on the frame (10); an optical axis slider (312) is slidably arranged on the positioning optical axis (311); the optical axis slider (312) is driven by a second cylinder (313) vertically arranged on the frame (10); a positioning identification module (32) is provided on the optical axis slider (312); the positioning identification module (32) includes a first mounting bracket (321) arranged on the optical axis slider (312); a camera module (322) is provided on the first mounting bracket (321); a focus point of the camera module (322) is aligned with the center of the fastening chuck (22).

6. The aircraft wheel hub detection device according to claim 1, characterized in that: The robotic arm (41) is provided with a first mounting portion (411), the first mounting portion (411) is provided with a pressure sensor (412), the detection probe assembly (42) includes a second mounting portion (421) detachably connected to the first mounting portion (411), the first mounting portion (411) is connected to the second mounting portion (421) to fix the detection probe assembly (42), the second mounting portion (421) is connected to a second mounting bracket (422), the second mounting bracket (422) is provided with a guide rail (423) along the axis direction of the mounting portion, the guide rail (423) is provided with a mounting slider (424), the mounting slider (424) is fixed with a probe mounting bracket (425), and the probe mounting bracket (425) is fixed with a detection probe (426).

7. The aircraft wheel hub detection device according to claim 6, characterized in that: The frame (10) is equipped with a quick-change platform (50), and a plurality of detection probe assemblies (42) of different specifications are arranged on the quick-change platform (50).

8. The aircraft wheel hub detection device according to claim 1, characterized in that: A standard sample fixing platform (60) is provided on the frame (10), and a plurality of standard samples (61) with different defect sizes are provided on the standard sample fixing platform (60).

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