Crosswise pushing feeding aircraft seal ring visual detection device and detection method

Abstract

The present application relates to the technical field of sealing ring detection, in particular to an aircraft sealing ring visual detection device and method based on transverse pushing and feeding, which comprises a supporting tray, a transfer piece and a double-wheel tension detection device for sealing ring grabbing and flaw detection; the supporting tray is provided with a composite driving structure on the side, the composite driving structure is connected with a deflection arm, and the end of the deflection arm is provided with a transfer mechanism; the transfer mechanism comprises a hollow pipe, a negative pressure generating device arranged on the deflection arm is communicated with the hollow pipe, an inner pipe is connected between the hollow pipe and the inner pipe through an elastic structure, a protruding part is arranged on the inner pipe, the protruding part penetrates through a hollow slot arranged on the side wall of the hollow pipe and extends to the outside of the hollow pipe, and a suction port is arranged on the protruding part; when the suction port is blocked by the aircraft sealing ring, negative pressure can be generated in the hollow pipe and the inner pipe, and the inner pipe is driven to move upward, so that the damage of the sealing ring to the subsequent flaw detection effect is eliminated.

Description

Technical Field

[0001] This invention relates to the field of sealing ring inspection technology, specifically to a visual inspection device and method for aircraft sealing rings with lateral push feeding. Background Technology

[0002] As critical sealing components in aviation hydraulic, fuel, and pneumatic systems, the quality of aircraft seals directly affects the operational safety and reliability of aircraft. Because aircraft seals are typically made of soft, elastic materials such as fluororubber and silicone rubber, and have extremely stringent requirements regarding appearance defects and dimensional accuracy, comprehensive visual inspection is essential during the production process to eliminate defective products with cracks, burrs, dents, and other defects.

[0003] In existing visual inspection devices for aircraft seals, the loading mechanism typically uses a lateral pushing method to transfer the seal to the inspection station. Its typical traditional structure includes a support plate, an intermediate constraint, a push rod, and a dual-wheel gripping inspection mechanism. During operation, the seal is first placed on the support plate, the push rod moves down and inserts into the inside of the seal, then the push rod moves laterally, pulling the seal into the intermediate constraint, constraining it into a near-elliptical structure. Finally, the two tensioning rollers of the dual-wheel gripping inspection mechanism lift the seal from the intermediate constraint, and an industrial CCD camera takes a picture of it during rotation.

[0004] However, in practical applications, it has been found that due to the relative movement required between the push rod and the support plate, they cannot achieve a perfect fit. Furthermore, to avoid wear from movement, a small assembly gap must be maintained between the push rod and the support plate. When the soft, elastic sealing ring is laterally pulled on the support plate by the push rod, the sealing ring is subjected to friction with the surface of the support plate, easily causing localized deformation. This allows it to be squeezed into the gap between the push rod and the support plate, resulting in rubbing, squeezing, or even shearing damage to the sealing ring. In addition, a completely seamless connection between the support plate and the intermediate constraint platform is also difficult to achieve. When the sealing ring passes through this connection point, the frictional resistance increases further, exacerbating the deformation and damage to the sealing ring. This mechanical damage generated during the feeding process not only destroys the surface integrity of the sealing ring but also causes uneven internal stress distribution, directly affecting the accuracy and reliability of subsequent visual inspection. Summary of the Invention

[0005] The purpose of this invention is to provide a visual inspection device and method for aircraft sealing rings that are laterally pushed and fed, so as to solve the problems mentioned in the background art.

[0006] To achieve the above objectives, the present invention provides the following technical solution:

[0007] A visual inspection device for aircraft seal rings with lateral push feeding includes: a support tray, a transfer component, and a dual-wheel tensioning inspection device for gripping the seal rings and detecting defects in them.

[0008] The side of the tray is provided with a composite drive structure, a deflection arm is connected to the composite drive structure, and a sliding mechanism is installed at the end of the deflection arm.

[0009] The allocation agency includes:

[0010] A hollow tube is connected to the deflection arm, and a negative pressure generating device disposed on the deflection arm is connected to the hollow tube.

[0011] An internal tube is sealed and slidably installed inside the hollow tube. The internal tube and the hollow tube are connected by an elastic structure. The internal tube is provided with a protrusion that penetrates a hollow groove on the side wall of the hollow tube and extends to the outside of the hollow tube.

[0012] An adsorption port is located on the protrusion. When the adsorption port is blocked by the aircraft sealing ring, negative pressure can be generated inside the hollow tube and the inner tube, driving the inner tube to move upward.

[0013] The aircraft sealing ring visual inspection device for lateral push feeding as described above: the elastic structure includes a stop ring and a cylindrical spring disposed in the hollow tube, one end of the cylindrical spring is connected to the stop ring, and the other end is connected to the upper end of the inner tube.

[0014] The aircraft sealing ring visual inspection device for lateral push feeding as described above: the hollow tube and the lower end of the inner tube are connected by an abutment structure. The abutment structure includes a stop groove provided at the lower end of the inner tube and a stop block detachably installed at the lower end of the hollow tube. The stop block abuts and cooperates with the stop groove, so that the lower ends of the hollow tube and the inner tube are flush.

[0015] The aircraft sealing ring visual inspection device with lateral push feeding as described above: the composite drive structure includes a linear drive module disposed on the side of the support tray, a rotary lifting control device is connected to the actuating end of the linear drive module, and the drive shaft of the rotary lifting control device is connected to the deflection arm.

[0016] The aircraft sealing ring visual inspection device for lateral push feeding as described above: the hollow tube includes a first hollow tube and a second hollow tube fixedly installed on the deflection arm, and a collar is detachably installed on the second hollow tube. The collar is rotatably connected to an annular groove provided on the first hollow tube.

[0017] The collar is provided with a first gear that is coaxially fixedly connected to it. A drive device is fixedly installed on the deflection arm. A second gear is connected to the output shaft of the drive device. The first gear and the second gear mesh.

[0018] The aircraft sealing ring visual inspection device with lateral push feeding as described above: the protrusions are arranged in multiple sets at equal intervals around the circumference, and the adsorption ports arranged on the multiple sets of protrusions are sequentially increased or decreased.

[0019] The visual inspection device for lateral pushing and feeding of aircraft seals as described above: the sliding mechanism further includes:

[0020] A sealing cover is rotatably disposed inside the built-in tube, and the sealing cover can keep one group of the adsorption ports in a conductive state.

[0021] The telescopic rod is fixedly connected at one end to the first hollow tube and at the other end to the sealing cover. The telescopic rod can keep the sealing cover and the first hollow tube axially locked.

[0022] The aircraft sealing ring visual inspection device with lateral push feeding as described above: a limit ring is provided inside the built-in tube, and the limit ring is slidably connected to the sealing cover;

[0023] The telescopic rod includes a connecting shaft fixedly installed on the first hollow tube and a connecting rod fixedly connected to the sealing cover, wherein the connecting rod is slidably fitted with the connecting shaft.

[0024] The connecting rod is provided with a limit block along its length, and the connecting shaft is provided with a limit groove along its length, the limit groove being slidably connected to the limit block.

[0025] The aircraft seal ring visual inspection device with lateral pushing and feeding as described above: the transfer component includes:

[0026] A pneumatic device, wherein a support plate is connected to the output shaft of the pneumatic device, and the support plate is provided with a groove along its width direction;

[0027] Two sets of extrusion members are disposed on the support plate. Each extrusion member is provided with an inner groove and a slider, and the slider can slide within the groove.

[0028] A bidirectional drive device is fixedly connected to the support plate, and the two actuating ends of the bidirectional drive device are connected to the two sets of extrusion components.

[0029] The method for inspecting aircraft sealing rings using the aforementioned transverse push-feed aircraft sealing ring visual inspection device includes the following steps:

[0030] Step 1: The robotic arm picks up the aircraft seal to be inspected and places it onto the tray;

[0031] Step 2: The rotary lifting control device controls the deflection arm to perform downward and lateral movements in sequence. When the deflection arm moves downward, the sliding mechanism is inside the aircraft seal ring. When it moves laterally, the sliding mechanism can drive the aircraft seal ring to move laterally.

[0032] Step 3: When the lateral movement of the arranging mechanism is completed, the negative pressure generating device is activated, and the aircraft sealing ring is sucked up by the suction port. Then, under the action of negative pressure, the internal tube moves upward to lift the front end of the aircraft sealing ring in the direction of movement upward.

[0033] Step 4: The allocation mechanism pushes the aircraft sealing ring into the transfer component, and the internal groove in the transfer component makes the aircraft sealing ring into a near-elliptical structure;

[0034] Step 5: The dual-wheel tension detection device grabs and tests the aircraft seal ring located inside the transfer component.

[0035] Compared with the prior art, the beneficial effects of the present invention are:

[0036] By using a negative pressure generating device, hollow tubing, and an internal tube, the internal tube can stably adsorb the aircraft sealing ring when the hollow tubing drives its movement, and then lift the front end of the aircraft sealing ring in the direction of movement upwards. This physically separates the aircraft sealing ring from the gap between the hollow tubing and the support tray, effectively preventing the aircraft sealing ring from being squeezed into the gap between the hollow tubing and the support tray due to deformation when the hollow tubing directly pushes it. This eliminates the risk of the aircraft sealing ring being rubbed, squeezed, or even damaged, ensuring the integrity and surface quality of the aircraft sealing ring during the transfer process. It also provides a precise and defect-free inspection object for subsequent visual inspection, significantly improving the reliability and accuracy of the inspection results.

[0037] By using a sealing cover, telescopic rods, and multiple sets of suction ports of different specifications, the optimal contact area and sealing effect between the suction port and the aircraft sealing ring can be ensured. This avoids the risk of insufficient suction area due to an excessively small suction port, causing the aircraft sealing ring to fall off due to vibration during transport. It also prevents gaps between the aircraft sealing ring and the suction port due to an excessively large suction port, which would prevent the establishment of a stable and sufficient negative pressure. This allows for stable adsorption and lifting of aircraft sealing rings of different specifications, improving the equipment's compatibility and production changeover efficiency, while ensuring adsorption stability and transport reliability for each specification. Attached Figure Description

[0038] Figure 1 A schematic diagram of the structure of a visual inspection device for aircraft seals that is used for laterally pushing and feeding materials.

[0039] Figure 2 A schematic diagram of the rotating lifting control device, deflection arm, and sliding mechanism in a visual inspection device for aircraft seal rings that is used for lateral pushing and feeding.

[0040] Figure 3 A schematic diagram of the sliding mechanism in a visual inspection device for lateral pushing and feeding of aircraft seal rings.

[0041] Figure 4 This is a partial cross-sectional view of the sliding mechanism in a visual inspection device for aircraft seals that uses lateral feeding.

[0042] Figure 5 An exploded view of a portion of the sliding mechanism in a visual inspection device for lateral feeding of aircraft seal rings.

[0043] Figure 6 An exploded view of the telescopic rod structure in a visual inspection device for lateral feeding of aircraft sealing rings.

[0044] Figure 7 Cross-sectional view of the sealing cover and internal tube in the visual inspection device for the aircraft sealing ring of the horizontal push feeding.

[0045] Figure 8 A schematic diagram of the transfer component in a visual inspection device for aircraft seals that is used for lateral pushing and feeding.

[0046] Figure 9 An exploded view of a portion of the transfer component in a visual inspection device for aircraft seals that is used for laterally pushed feeding.

[0047] In the diagram: 1. Supporting tray; 2. Linear drive module; 3. Rotary lifting control device; 4. Deflection arm; 5. Negative pressure generating device; 6. First hollow tube; 601. Annular groove; 7. Collar; 8. First gear; 9. Second gear; 10. Drive device; 11. Second hollow tube; 1101. Hollow groove; 1102. Stop ring; 12. Internal tube; 1201. Protrusion; 1202. Suction port; 1203. Stop groove; 1204. Limiting ring; 13. Stop block; 14. Cylindrical spring; 15. Sealing cover; 16. Connecting rod; 1601. Limiting block; 17. Connecting shaft; 1701. Limiting groove; 18. Pneumatic device; 19. Supporting plate; 1901. Slide groove; 20. Extrusion part; 2001. Inner groove; 2002. Slider; 21. Bidirectional drive device. Detailed Implementation

[0048] The technical solutions of the present invention will be clearly and completely described below with reference to the accompanying drawings of the embodiments of the present invention. Obviously, the described embodiments are only some embodiments of the present invention, and not all embodiments.

[0049] Please see Figures 1-9 As an embodiment of the present invention, the aircraft sealing ring visual inspection device for lateral pushing and feeding includes a support tray 1, a transfer component, and a dual-wheel tensioning detection device for gripping the sealing ring and detecting defects in the sealing ring.

[0050] The pallet 1 is provided with a composite drive structure on its side, and a deflection arm 4 is connected to the composite drive structure. A sliding mechanism is installed at the end of the deflection arm 4. The composite drive structure includes a linear drive module 2 provided on the side of the pallet 1. A rotary lifting control device 3 is connected to the actuating end of the linear drive module 2. The drive shaft of the rotary lifting control device 3 is connected to the deflection arm 4.

[0051] In this embodiment, in the initial state, the rotary lifting control device 3 first lifts the deflection arm 4, so that the lower end of the dipping mechanism and the upper surface of the tray 1 maintain a certain gap. This gap is much larger than the thickness of the largest size aircraft seal ring, so as to avoid interference between the deflection arm 4 and the aircraft seal ring when the deflection arm 4 is reset. At the same time, in this state, the deflection arm 4 is parallel to the length direction of the linear drive module 2, providing sufficient space for the external gripping manipulator (not shown in the figure) to place the aircraft seal ring, ensuring that the aircraft seal ring will not interfere with the deflection arm 4 during the placement process.

[0052] After the aircraft sealing ring is placed, the rotary lifting control device 3 first drives the deflection arm 4 to rotate to a direction perpendicular to the linear drive module 2. At this time, the sliding mechanism is located directly above the aircraft sealing ring, and its projection on the support tray 1 falls on the inner side of the aircraft sealing ring.

[0053] Subsequently, the rotary lifting control device 3 controls the deflection arm 4 to move downward until the lower end of the sliding mechanism is almost in contact with the upper surface of the support tray 1. Then, the linear drive module 2 drives the deflection arm 4 and the sliding mechanism to move laterally, smoothly pushing the aircraft sealing ring from the support tray 1 into the transfer component, so that the aircraft sealing ring is constrained into an elliptical structure.

[0054] Finally, the two tensioning wheels on the dual-wheel tensioning detection device (not shown in the figure) approach each other and move down synchronously. After reaching the predetermined height, the two wheels unfold and support the aircraft seal ring. The rotation of the two wheels, in conjunction with an industrial CCD camera, performs a comprehensive photographic inspection of the aircraft seal ring.

[0055] Please see Figures 3-5 , Figure 7 The allocation mechanism includes: a hollow tube, an internal tube 12, and an adsorption port 1202.

[0056] The hollow tube is connected to the deflection arm 4, and the negative pressure generating device 5 installed on the deflection arm 4 is connected to the hollow tube.

[0057] The built-in tube 12 is slidably installed inside the hollow tube. The built-in tube 12 and the hollow tube are connected by an elastic structure. The elastic structure includes a stop ring 1102 and a cylindrical spring 14 disposed inside the hollow tube. One end of the cylindrical spring 14 is connected to the stop ring 1102, and the other end is connected to the upper end of the built-in tube 12.

[0058] The adsorption port 1202 is provided on the protrusion 1201. When the adsorption port 1202 is blocked by the sealing ring, negative pressure can be generated in the hollow tube and the built-in tube 12, which will drive the built-in tube 12 to move upward.

[0059] In the initial state, the cylindrical spring 14 is compressed. Under the elastic force provided by the cylindrical spring 14, the lower end of the inner tube 12 is flush with the lower end of the hollow tube to ensure that the height of the two lower ends is uniform. Thus, the height of the inner tube 12 can be precisely controlled by controlling the position of the hollow tube.

[0060] As the deflecting arm 4 drives the aircraft sealing ring from the carrier tray 1 to the transfer unit via the hollow tube and the internal tube 12, the internal tube 12 abuts against the aircraft sealing ring and drives its movement. At this time, the aircraft sealing ring will adhere to the adsorption port 1202. Simultaneously, the negative pressure generating device 5 is in operation, causing the air inside the hollow tube and the internal tube 12 to be extracted. The moment the aircraft sealing ring adheres to the adsorption port 1202, a negative pressure state is rapidly established inside the hollow tube and the internal tube 12. Under the action of negative pressure, the adsorption port 1202 produces a stable adsorption effect on the aircraft sealing ring, ensuring that the aircraft sealing ring will not shift or fall off during the transfer process.

[0061] Furthermore, when a negative pressure is established inside the hollow tube and the inner tube 12, the negative pressure drives the inner tube 12 to move upwards along the inside of the hollow tube, while simultaneously compressing the cylindrical spring 14. This upward movement lifts the front end of the aircraft sealing ring in the direction of movement, physically separating the aircraft sealing ring from the gap between the hollow tube and the support tray 1. This effectively avoids the aircraft sealing ring being squeezed into the gap between the hollow tube and the support tray 1 due to deformation when the hollow tube directly pushes the aircraft sealing ring, thus eliminating the risk of the aircraft sealing ring being rubbed, squeezed, or even damaged. Based on the above settings, the integrity and surface quality of the aircraft sealing ring are ensured during the transfer process, and a precise and defect-free inspection object is provided for subsequent visual inspection, significantly improving the reliability and accuracy of the inspection results.

[0062] Furthermore, the upward movement of the built-in tube 12 depends entirely on the establishment of negative pressure within the hollow tube and the built-in tube 12. This establishment of negative pressure, in turn, requires a tight fit between the suction port 1202 and the aircraft sealing ring. This necessitates that the built-in tube 12, when acting on the aircraft sealing ring, inevitably follows the inherent sequence of "suction first, then lifting." This ensures the precision and irreversibility of the timing sequence, achieving self-locking and interlocking of the action without the need for additional sensors or electrical control, fundamentally avoiding timing errors caused by control signal delays or misjudgments. Simultaneously, because suction must be established first, the aircraft sealing ring is firmly fixed before lifting, effectively preventing slippage or detachment during the lifting process, further enhancing the stability of the transfer process.

[0063] The built-in tube 12 is provided with a protrusion 1201, which penetrates the hollow groove 1101 opened on the side wall of the hollow tube and extends to the outside of the hollow tube. Because the protrusion 1201 protrudes from the surface of the hollow tube, when the adsorption port 1202 adsorbs the aircraft sealing ring, the protrusion 1201 partially supports the aircraft sealing ring, creating a partial separation between the aircraft sealing ring and the outer wall of the hollow tube. That is, the aircraft sealing ring may only maintain contact with the hollow tube in certain areas on its sides, while the area supported by the protrusion 1201 is completely detached. This significantly reduces the contact area between the aircraft sealing ring and the hollow tube when the built-in tube 12 subsequently moves the aircraft sealing ring upwards, thereby reducing the frictional force generated by their relative movement. This effectively prevents accidental separation of the aircraft sealing ring from the adsorption port 1202 due to excessive frictional resistance, ensuring the stability of the adsorption and the reliability of the transfer process. Meanwhile, due to the reduced friction, the upward movement of the built-in tube 12 is smoother, which helps to maintain the stability of the aircraft seal ring and avoid twisting or deformation caused by uneven force, further ensuring the integrity of the aircraft seal ring during the transfer process and the accuracy of subsequent testing.

[0064] The hollow tube is connected to the lower end of the built-in tube 12 by an abutment structure. The abutment structure includes a stop groove 1203 provided at the lower end of the built-in tube 12 and a stop block 13 detachably installed at the lower end of the hollow tube. The stop block 13 abuts against the stop groove 1203, so that the lower ends of the hollow tube and the built-in tube 12 are flush. The detachable connection method is a bolt connection.

[0065] In the initial state, under the elastic force provided by the cylindrical spring 14, the inner tube 12 is driven to move downward. Under the action of this force, the stop block 13 can maintain a contact state with the stop groove 1203, so that the lower end of the inner tube 12 and the lower end of the hollow tube are kept flush, so as to ensure that the lower ends of the two are at the same height.

[0066] Please see Figures 2-4 , Figure 7 Furthermore, the hollow tube includes a first hollow tube 6 and a second hollow tube 11 fixedly installed on the deflection arm 4. A collar 7 is detachably installed on the second hollow tube 11. The collar 7 is sealed and rotatably connected to the annular groove 601 provided on the first hollow tube 6. The detachable connection method is a bolt connection.

[0067] The collar 7 is provided with a first gear 8 that is coaxially fixedly connected to it. A drive device 10 is fixedly installed on the deflection arm 4. A second gear 9 is connected to the output shaft of the drive device 10. The first gear 8 and the second gear 9 mesh.

[0068] The protrusions 1201 are arranged in multiple groups at equal intervals around the circumference, and the adsorption ports 1202 provided on the multiple groups of protrusions 1201 are successively increased or decreased.

[0069] In this embodiment, by controlling the operation of the drive device 10, the second gear 9 connected to its output shaft can be rotated. Since the second gear 9 meshes with the first gear 8, the first gear 8 rotates accordingly, driving the collar 7 and the second hollow tube 11 to rotate. The rotation of the second hollow tube 11 further drives the inner tube 12 to rotate synchronously, thereby realizing the switching of the adsorption port 1202 that cooperates with the aircraft sealing ring. The inner tube 12 is provided with multiple sets of adsorption ports 1202, whose diameters increase or decrease sequentially to adapt to different models of aircraft sealing rings. When switching to the adsorption port 1202 that matches the current aircraft sealing ring model, it can ensure that the adsorption port 1202 and the aircraft sealing ring form the best contact area and sealing effect: it avoids the risk of insufficient adsorption area due to the adsorption port 1202 being too small, causing the aircraft sealing ring to fall off due to vibration during the transfer, and also prevents the gap between the aircraft sealing ring and the adsorption port 1202 being too large, making it impossible to establish a stable and sufficient negative pressure strength. Based on the above settings, stable adsorption and lifting can be achieved for aircraft sealing rings of different specifications, improving the compatibility and production change efficiency of the equipment, while ensuring adsorption stability and transfer reliability for each specification.

[0070] It should be noted that the different specifications of aircraft sealing rings in this application refer to the different cross-sectional areas of the aircraft sealing rings, that is, the different thicknesses of the aircraft sealing rings.

[0071] Please see Figures 4-6 The allocation mechanism also includes: a sealing cover 15 and a telescopic rod.

[0072] The sealing cover 15 is rotatably disposed inside the built-in tube 12. The sealing cover 15 enables one of the adsorption ports 1202 to remain in a conductive state. A limiting ring 1204 is provided inside the built-in tube 12, and the limiting ring 1204 is slidably connected to the sealing cover 15.

[0073] One end of the telescopic rod is fixedly connected to the first hollow tube 6, and the other end is fixedly connected to the sealing cover 15. The telescopic rod can keep the sealing cover 15 and the first hollow tube 6 in an axially locked state.

[0074] The telescopic rod includes a connecting shaft 17 fixedly installed on the first hollow tube 6 and a connecting rod 16 fixedly connected to the sealing cover 15, wherein the connecting rod 16 is slidably fitted with the connecting shaft 17;

[0075] The connecting rod 16 is provided with a limiting block 1601 along its length direction, and the connecting shaft 17 is provided with a limiting groove 1701 along its length direction. The limiting groove 1701 is slidably connected to the limiting block 1601.

[0076] In this embodiment, the first hollow tube 6 is fixedly connected to the deflection arm 4, while the connecting shaft 17 is fixedly connected to the first hollow tube 6, thus locking the connecting shaft 17 in the axial direction. The connecting rod 16 is connected to the connecting shaft 17 through the cooperation of the limiting groove 1701 and the limiting block 1601, so the connecting rod 16 is also restricted to a fixed axial position. Based on this structure, when the second hollow tube 11 rotates, it can drive the inner tube 12 to rotate relative to the axially fixed sealing cover 15. This relative movement causes the set of adsorption ports 1202 that match the current aircraft sealing ring specifications to rotate to the open position, while the adsorption ports 1202 of other specifications are completely blocked by the sealing cover 15. This structure ensures that only one set of adsorption ports 1202 is in working condition, thereby concentrating all the adsorption force provided by the negative pressure generating device 5 on the currently used adsorption port 1202, significantly improving the adsorption strength of the aircraft sealing ring, avoiding the problems of airflow dispersion and insufficient suction caused by multiple sets of adsorption ports 1202 being open at the same time, effectively preventing the aircraft sealing ring from falling off due to insufficient adsorption force during the transfer process, and ensuring the stability and reliability of equipment operation.

[0077] Please see Figure 1 , Figures 8-9 The transfer component includes: a pneumatic device 18, a pressing component 20, and a bidirectional drive device 21.

[0078] A support plate 19 is connected to the output shaft of the pneumatic device 18, and the support plate 19 is provided with a sliding groove 1901 along its width direction.

[0079] Two sets of extrusion members 20 are provided and are disposed on the support plate 19. The extrusion member 20 is provided with an inner groove 2001 and a slider 2002. The slider 2002 can slide within the groove 1901.

[0080] The bidirectional drive device 21 is fixedly connected to the support plate 19, and the two actuating ends of the bidirectional drive device 21 are connected to the two sets of the extrusion members 20.

[0081] In this embodiment, when the aircraft sealing ring is pulled into the two sets of extrusion members 20, the aircraft sealing ring can be precisely restricted in the corresponding inner groove 2001, thereby constrained into a quasi-elliptical structure. This quasi-elliptical shape is more convenient for the subsequent dual-wheel tension detection device to grasp.

[0082] Furthermore, considering that the transfer component needs to adapt to different specifications of aircraft seals, if the distance between the two sets of extrusion components 20 remains fixed, the thicker seal may form an overly flat, elliptical structure when compressed, causing the dual-wheel tensioning detection device to be unable to smoothly enter the aircraft seal for opening and gripping. Therefore, this embodiment sets up a bidirectional drive device 21, which can automatically or manually adjust the relative distance between the two sets of extrusion components 20 according to the current specifications of the aircraft seal: when processing a thicker aircraft seal, the bidirectional drive device 21 appropriately increases the distance between the two sets of extrusion components 20, so that the aircraft seal is constrained into a moderately flat, elliptical shape, which not only ensures the positioning stability of the aircraft seal during the detection process, but also reserves sufficient space for the entry of the dual-wheel tensioning detection device, ensuring that it can smoothly insert into the aircraft seal and open it smoothly.

[0083] As an embodiment of the present invention, a method for inspecting aircraft sealing rings using the aforementioned transverse push-feed aircraft sealing ring visual inspection device is also proposed, comprising the following steps:

[0084] Step 1: The robotic arm picks up the aircraft seal to be inspected and places it onto tray 1;

[0085] Step 2: The rotary lifting control device 3 controls the deflection arm 4 to perform downward and lateral movements in sequence. When the deflection arm 4 moves downward, the sliding mechanism is inside the aircraft seal ring. When it moves laterally, the sliding mechanism can drive the aircraft seal ring to move laterally.

[0086] Step 3: When the lateral movement of the arranging mechanism is completed, the negative pressure generating device 5 is activated, and the aircraft sealing ring is sucked up by the suction port 1202. Then, under the action of negative pressure, the internal tube 12 moves upward to lift the front end of the aircraft sealing ring in the direction of movement upward.

[0087] Step 4: The allocation mechanism pushes the aircraft sealing ring into the transfer component, and uses the inner groove 2001 in the transfer component to make the aircraft sealing ring into a near-elliptical structure;

[0088] Step 5: The dual-wheel tension detection device grabs and tests the aircraft seal ring located inside the transfer component.

[0089] It will be apparent to those skilled in the art that the present invention is not limited to the details of the exemplary embodiments described above, and that the invention can be implemented in other specific forms without departing from its spirit or essential characteristics. Therefore, the embodiments should be considered in all respects as exemplary and non-limiting, and the scope of the invention is defined by the appended claims rather than the foregoing description. Thus, all variations falling within the meaning and scope of equivalents of the claims are intended to be included within the present invention. No reference numerals in the claims should be construed as limiting the scope of the claims.

[0090] Furthermore, it should be understood that although this specification describes embodiments, not every embodiment contains only one independent technical solution. This narrative style is merely for clarity. Those skilled in the art should consider the specification as a whole, and the technical solutions in each embodiment can also be appropriately combined to form other embodiments that can be understood by those skilled in the art.

Claims

1. A visual inspection device for aircraft sealing rings with lateral pushing and feeding, comprising: Pallets, transfer components, and a dual-wheel tensioning detection device for gripping and inspecting seals for defects; The side of the tray is provided with a composite drive structure, a deflection arm is connected to the composite drive structure, and a sliding mechanism is installed at the end of the deflection arm. The allocation mechanism is characterized by comprising: A hollow tube is connected to the deflection arm, and a negative pressure generating device disposed on the deflection arm is connected to the hollow tube. An internal tube is sealed and slidably installed inside the hollow tube. The internal tube and the hollow tube are connected by an elastic structure. The internal tube is provided with a protrusion that penetrates a hollow groove on the side wall of the hollow tube and extends to the outside of the hollow tube. An adsorption port is provided on the protrusion. When the adsorption port is blocked by the aircraft sealing ring, negative pressure can be generated inside the hollow tube and the inner tube, which will drive the inner tube to move upward. The elastic structure includes a stop ring and a cylindrical spring disposed inside the hollow tube. One end of the cylindrical spring is connected to the stop ring, and the other end is connected to the upper end of the inner tube. The hollow tube includes a first hollow tube and a second hollow tube fixedly installed on the deflection arm. A collar is detachably installed on the second hollow tube, and the collar is rotatably and sealingly connected to an annular groove provided on the first hollow tube. The collar is provided with a first gear that is coaxially fixedly connected to it, the deflection arm is fixedly mounted with a drive device, and the output shaft of the drive device is connected to a second gear, the first gear meshing with the second gear; The protrusions are arranged in multiple groups at equal intervals around the circumference, and the adsorption ports on the multiple groups of protrusions are sequentially increased or decreased in size. The allocation mechanism also includes: A sealing cover is rotatably disposed inside the built-in tube, and the sealing cover can keep one group of the adsorption ports in a conductive state. The telescopic rod is fixedly connected at one end to the first hollow tube and at the other end to the sealing cover. The telescopic rod can keep the sealing cover and the first hollow tube in an axially locked state. A limiting ring is provided inside the built-in tube, and the limiting ring is slidably connected to the sealing cover; The telescopic rod includes a connecting shaft fixedly installed on the first hollow tube and a connecting rod fixedly connected to the sealing cover, wherein the connecting rod is slidably fitted with the connecting shaft. The connecting rod is provided with a limit block along its length, and the connecting shaft is provided with a limit groove along its length, the limit groove being slidably connected to the limit block.

2. The visual inspection device for aircraft sealing rings with lateral pushing and feeding according to claim 1, characterized in that, The hollow tube is connected to the lower end of the inner tube by an abutment structure. The abutment structure includes a stop groove provided at the lower end of the inner tube and a stop block detachably installed at the lower end of the hollow tube. The stop block abuts against the stop groove, so that the lower ends of the hollow tube and the inner tube are flush. The detachable connection method is a bolt connection.

3. The visual inspection device for aircraft sealing rings with lateral pushing and feeding according to claim 1, characterized in that, The composite drive structure includes a linear drive module disposed on the side of the support tray. A rotary lifting control device is connected to the actuating end of the linear drive module, and the drive shaft of the rotary lifting control device is connected to the deflection arm.

4. The visual inspection device for aircraft sealing rings with lateral pushing and feeding according to claim 1, characterized in that, The transfer device includes: A pneumatic device, wherein a support plate is connected to the output shaft of the pneumatic device, and the support plate is provided with a groove along its width direction; Two sets of extrusion members are disposed on the support plate. Each extrusion member is provided with an inner groove and a slider, and the slider can slide within the groove. A bidirectional drive device is fixedly connected to the support plate, and the two actuating ends of the bidirectional drive device are connected to the two sets of extrusion components.

5. A method for inspecting aircraft sealing rings using a visual inspection device for laterally pushed feeding as described in any one of claims 1 to 4, characterized in that, Includes the following steps: Step 1: The robotic arm picks up the aircraft seal to be inspected and places it onto the tray; Step 2: The rotary lifting control device controls the deflection arm to perform downward and lateral movements in sequence. When the deflection arm moves downward, the sliding mechanism is inside the aircraft seal ring. When it moves laterally, the sliding mechanism can drive the aircraft seal ring to move laterally. Step 3: When the lateral movement of the arranging mechanism is completed, the negative pressure generating device is activated, and the aircraft sealing ring is sucked up by the suction port. Then, under the action of negative pressure, the internal tube moves upward to lift the front end of the aircraft sealing ring in the direction of movement upward. Step 4: The allocation mechanism pushes the aircraft sealing ring into the transfer component, and the internal groove in the transfer component makes the aircraft sealing ring into a near-elliptical structure; Step 5: The dual-wheel tension detection device grabs and tests the aircraft seal ring located inside the transfer component.

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