An apparatus and method for automatic detection of internal wear in an aircraft landing gear sleeve

Abstract

An automatic wear detection device and method for the internal structure of an aircraft landing gear sleeve, belonging to the field of aircraft component inspection technology, is disclosed. The detection device includes a platform with a rotatable support and limiting frame for supporting and limiting the vertically placed aircraft landing gear sleeve. A laser ultrasonic detector is vertically movable above the platform, emitting a detection signal parallel to the horizontal plane. Two traction mechanisms are positioned opposite each other on the upper and lower sides of the platform. The upper traction mechanism is fixedly connected to the laser ultrasonic detector below it via a traction rope, while the lower traction mechanism is fixedly connected to a locking mechanism via a traction rope. The locking mechanism is detachably connected to the lower part of the laser ultrasonic detector. The vertical placement of the landing gear sleeve, combined with the vertically movable laser ultrasonic detector, ensures a vertical alignment between the detection end and the inner wall of the sleeve, eliminating the need for direct contact and preventing additional wear on the sleeve's inner wall.

Description

Technical Field

[0001] This invention relates to the field of aircraft component testing technology, and in particular to an automatic testing device and method for internal wear of aircraft landing gear sleeves. Background Technology

[0002] As the core load-bearing component of the landing gear retraction system, the inner wall of the aircraft landing gear sleeve is subjected to high-frequency reciprocating friction, alternating loads, and complex environments for a long time. This makes it prone to wear, scratches, and even pitting defects. If these wear defects are not detected in time, they can lead to an increase in the clearance between the sleeve and the piston rod, causing landing gear retraction jamming, hydraulic oil leakage, and other malfunctions, which seriously threaten flight safety.

[0003] The existing automatic wear detection device for aircraft landing gear sleeves (announcement number CN115615679B) includes a movable worktable. A linear motion module is slidably connected to the upper surface of the movable worktable along its length. The aircraft landing gear sleeve is placed on the linear motion module. An operating table is provided at one end of the movable worktable. The operating table is connected to a rotary motion module. An adaptive chuck is fixed to the rotary motion module. A probe is clamped on the adaptive chuck. The linear motion module moves closer to the rotary motion module until the probe penetrates into the interior of the aircraft landing gear sleeve-like part. The rotary motion module rotates within the cavity to perform internal detection.

[0004] The above-mentioned method uses a probe detection method. Since the probe needs to be in constant contact with the inner wall of the aircraft landing gear sleeve during detection, the inner wall of the aircraft landing gear sleeve is prone to wear. In addition, during detection, the aircraft landing gear sleeve is placed horizontally, and a long support rod is required to support and fix the probe. However, only one end of the support rod is fixed and in a horizontal state. As a result, the end of the support rod with the probe will bend slightly under the weight of the support rod itself, causing the detection end to be unable to be perpendicular to the inner wall of the aircraft landing gear sleeve, which in turn leads to errors in the detection results. Summary of the Invention

[0005] To address the technical problems mentioned above, this invention provides an automatic detection device and method for internal wear of aircraft landing gear sleeves. It replaces the traditional rigid support rod with a dual upper and lower traction mechanism combined with a snap-fit ​​mechanism. The sleeve is placed vertically, and the dual traction units maintain the stability of the detector's posture through synchronized action, ensuring the detection end is perpendicular to the inner wall of the sleeve. This avoids angular deviation and signal distortion caused by support rod bending, improving detection accuracy. Furthermore, it eliminates the need for pre-reserved horizontal space for the support rod, significantly reducing the equipment's size and footprint, and enhancing site adaptability.

[0006] The technical solution of this invention is as follows: This invention provides an automatic wear detection device for the internal structure of an aircraft landing gear sleeve, comprising a platform on which a support and limiting frame is rotatably mounted for supporting and limiting the vertically placed aircraft landing gear sleeve; a laser ultrasonic detector is vertically movable above the platform, the direction of the detection signal emitted by the laser ultrasonic detector being parallel to the horizontal plane; two traction mechanisms are provided on the upper and lower sides of the platform, the upper traction mechanism being fixedly connected to the laser ultrasonic detector below it via a traction rope, and the lower traction mechanism being fixedly connected to a locking mechanism via a traction rope, the locking mechanism being detachably connected to the lower part of the laser ultrasonic detector. The landing gear sleeve is supported by a vertically placed structure, which, combined with a vertically movable laser ultrasonic testing instrument, eliminates the need for horizontal support rods, avoiding bending issues caused by the weight of the support rods and ensuring the vertical alignment between the testing end of the laser ultrasonic testing instrument and the inner wall of the sleeve. The laser ultrasonic testing instrument uses a non-contact testing method, eliminating direct contact with the inner wall of the sleeve and preventing additional wear on the inner wall during testing. At the same time, the traction mechanisms on the upper and lower sides, together with the locking mechanism, provide stable vertical traction support for the laser ultrasonic testing instrument, ensuring the stability of the instrument's posture during testing and further improving the accuracy of the test results.

[0007] Preferably, the two traction mechanisms are linked synchronously, with the traction ropes of the two traction mechanisms being pulled in and out in opposite directions and at the same speed. The synchronous linkage of the traction mechanisms can keep the vertical traction force on the laser ultrasonic detector balanced during the lifting and lowering process, avoiding tilting or shaking of the detector due to uneven traction force, ensuring that the detector moves smoothly vertically, ensuring the stability of the detection signal transmission direction, and thus improving the consistency and reliability of the detection data.

[0008] Preferably, each traction mechanism is equipped with multiple traction ropes, which are divided into two groups and symmetrically distributed about the center of gravity of the laser ultrasonic detector. This allows the traction force to be applied evenly to the laser ultrasonic detector, avoiding excessive local stress that could cause deformation or attitude deviation of the detector. At the same time, the multiple traction ropes enhance the stability of the traction structure, further improving the attitude stability of the detector during the lifting and lowering detection process, and ensuring that the detection accuracy is not affected by the traction structure.

[0009] Preferably, the lower end of the laser ultrasonic testing instrument is fixedly connected to a first locking seat, and the locking mechanism is fixedly connected to the traction rope through a second locking seat. The locking mechanism is locked with the first locking seat. Through the cooperation of the first locking seat and the locking mechanism, the laser ultrasonic testing instrument and the lower traction mechanism can be quickly and detachably connected. At the same time, the locking structure can ensure the stability of the connection and avoid the testing instrument's posture shifting due to loosening of the connection during the testing process, thus ensuring the smooth progress of the testing work.

[0010] Preferably, the first snap-fit ​​seat has a snap-fit ​​cavity, and the lower end of the first snap-fit ​​seat has a through groove communicating with the snap-fit ​​cavity. The snap-fit ​​mechanism includes a first rotary driver, and a snap-fit ​​block is fixedly installed at the output end of the first rotary driver. The snap-fit ​​block has an elongated structure and its horizontal projection shape is the same as that of the through groove. The snap-fit ​​block can enter the snap-fit ​​cavity through the through groove, and after being driven to rotate by the first rotary driver, it achieves a stable snap-fit ​​with the first snap-fit ​​seat. The snap-fit ​​structure is simple and reliable, and can quickly complete the connection and fixation, avoiding the snap-fit ​​loosening caused by vibration and other factors during the testing process, and ensuring the stability of the laser ultrasonic testing instrument.

[0011] Preferably, the lower end of the first connector has an insertion port, and a slot is located within the insertion port. Several limiting strips are fixedly provided at circumferential intervals on the inner wall of the insertion port, extending vertically. Several limiting grooves are vertically provided on the outer peripheral wall of the second connector, and the limiting strips slide in engagement with the limiting grooves. This sliding engagement between the limiting strips and the limiting grooves guides and limits the connection between the first and second connectors, ensuring that the connector block can accurately align with the slot, improving connector efficiency. Simultaneously, it prevents relative rotation after connection, ensuring the stability of the laser ultrasonic testing instrument's detection direction and further improving detection accuracy.

[0012] Preferably, a magnet is fixedly installed on the second card holder, and the first card holder is made of ferromagnetic material. The magnetic attraction of the magnet can generate an adsorption force when the first card holder and the second card holder are close together, guiding them to quickly and accurately align, reducing alignment adjustment time, improving installation efficiency, and at the same time, the magnetic attraction can help enhance the stability of the connection, avoid slight displacement during the testing process, and ensure the stability of the laser ultrasonic testing instrument.

[0013] Preferably, the support and limiting frame is connected to a rotary drive mechanism. The support and limiting frame is equipped with two opposing clamping mechanisms. The clamping mechanisms can stably limit the vertically placed landing gear sleeve, preventing the sleeve from shifting or shaking during the inspection process and ensuring the accuracy of the inspection position. The rotary drive mechanism can drive the support and limiting frame and the sleeve to rotate along the axis. In conjunction with the vertical inspection stroke of the laser ultrasonic detector, it can achieve a comprehensive sweep inspection of the inner wall of the sleeve, ensuring no blind spots in the inspection and improving the integrity of the inspection results.

[0014] A detection method, comprising: Place the aircraft landing gear sleeve vertically on the support limit frame and limit its position; The upper traction mechanism releases the traction rope, and the laser ultrasonic detector moves downward inside the aircraft landing gear sleeve to approach the locking mechanism. The locking mechanism locks with the laser ultrasonic detector. The two traction mechanisms distributed above and below drive the laser ultrasonic detector to rise and fall at the same speed. One rise or fall of the laser ultrasonic detector is one detection stroke. After each inspection cycle is completed, the support limiter rotates at a set angle along the axis of the aircraft landing gear sleeve and stops. Then, the laser ultrasonic detector begins the next inspection cycle, repeating the process until the inner wall of the aircraft landing gear sleeve is completely swept.

[0015] The vertically positioned limiting sleeve, combined with a rotatable support and limiting frame, and the vertical detection stroke of the laser ultrasonic testing instrument, enables all-round sweeping inspection of the inner wall of the sleeve, ensuring no omissions in the inspection coverage. The upper and lower traction mechanisms drive the testing instrument to rise and fall at the same speed, ensuring smooth movement and stable posture of the testing instrument during the inspection process. Combined with the non-contact laser ultrasonic testing method, it avoids additional wear on the inner wall of the sleeve and ensures the accuracy of the inspection. At the same time, the precise connection of the locking mechanism ensures the continuity and stability of the inspection stroke, improving the overall inspection efficiency and the reliability of the results.

[0016] Preferably, the engagement process between the locking mechanism and the laser ultrasonic testing instrument is as follows: as the first and second locking seats gradually approach each other, the magnet on the second locking seat generates a magnetic attraction, pulling the first locking seat to automatically align. Simultaneously, the limiting strip slides along the limiting groove, achieving initial positioning. The locking block passes through the slot and enters the locking cavity, where the first rotary driver drives the locking block to rotate at a set angle. The combination of magnetic attraction and limiting guidance achieves precise alignment during the locking process, reducing manual adjustment steps and improving locking efficiency. The rotational drive of the locking block ensures stability during locking, preventing loosening during testing and ensuring the stability of the laser ultrasonic testing instrument's posture during subsequent lifting and lowering testing, thus guaranteeing accurate testing.

[0017] As can be seen from the above technical solutions, the advantages of the present invention are: 1. The landing gear sleeve is supported by a vertically placed structure, which, combined with a vertically movable laser ultrasonic testing instrument, eliminates the need for horizontal support rods, avoiding bending issues caused by the weight of the support rods and ensuring the vertical alignment between the testing end of the laser ultrasonic testing instrument and the inner wall of the sleeve. The laser ultrasonic testing instrument uses a non-contact testing method, eliminating direct contact with the inner wall of the sleeve and preventing additional wear on the inner wall during testing. At the same time, the traction mechanisms on the upper and lower sides, together with the locking mechanism, provide stable vertical traction support for the laser ultrasonic testing instrument, ensuring the stability of the instrument's posture during testing and further improving the accuracy of the test results.

[0018] 2. The symmetrical distribution of multiple traction ropes and the locking mechanism enhance the stability and reliability of the detection. The symmetrical layout of the traction ropes in groups achieves balanced force distribution at multiple points, preventing swaying or rotation during the lifting and lowering of the detector, and ensuring that the detection trajectory matches the preset requirements. The locking mechanism integrates limit and magnetic attraction to achieve fast and accurate locking, reduce the impact of torsional force on the traction rope, extend the service life of components, and improve the long-term stability of the equipment.

[0019] 3. By combining non-contact detection with cyclic sweeping, the detection efficiency is upgraded. Laser ultrasonic detection does not require contact with the inner wall, avoiding wear at the source. At the same time, it accurately identifies deep and minute defects. With the linkage of the support and the rotary drive mechanism, the sleeve is driven to rotate after completing one detection stroke, and the cycle achieves full circumference sweeping, eliminating detection blind spots, reducing manual intervention, and improving detection efficiency. Attached Figure Description

[0020] To more clearly illustrate the technical solution of the present invention, the accompanying drawings used in the description will be briefly introduced below. Obviously, the accompanying drawings described below are only some embodiments of the present invention. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0021] Figure 1 This is a three-dimensional structural diagram of an automatic wear detection device for the internal structure of an aircraft landing gear sleeve according to one or more embodiments of the present invention. Figure 1 ; Figure 2 This is a three-dimensional structural diagram of an automatic wear detection device for the internal structure of an aircraft landing gear sleeve according to one or more embodiments of the present invention. Figure 2 ; Figure 3 for Figure 2 A magnified view of the structure at position A in the diagram shown. Figure 4 This is a schematic diagram of the cooperation structure between the aircraft landing gear sleeve and two traction mechanisms according to one or more embodiments of the present invention. Figure 5 This is a partial cross-sectional structural schematic diagram of the mating position of the aircraft landing gear sleeve and the lower traction mechanism according to one or more embodiments of the present invention. Figure 6 for Figure 5 A magnified schematic diagram of the local structure at position B in the structure shown; Figure 7 for Figure 5 A magnified schematic diagram of the structure at position C in the diagram; Figure 8 This is an exploded structural diagram of the connection position between the first and second card holders according to one or more embodiments of the present invention; The components represented by the various reference numerals in the diagram are: 1. Platform; 11. Aircraft landing gear sleeve; 2. Laser ultrasonic detector; 3. Traction mechanism; 31. Traction rope; 4. Snap-fit ​​mechanism; 421. Snap-fit ​​block; 422. First rotary actuator; 5. Support limit frame; 51. Clamping mechanism; 6. Rotary drive mechanism; 61. Second rotary actuator; 62. Gear; 63. Gear ring; 7. First snap-fit ​​seat; 71. Snap-fit ​​cavity; 72. Through groove; 73. Limiting strip; 8. Second snap-fit ​​seat; 81. Limiting groove; 9. Magnet. Detailed Implementation

[0022] To make the objectives, features, and advantages of this invention more apparent and understandable, the technical solutions of this invention will be clearly and completely described below with reference to the accompanying drawings of the specific embodiments. Obviously, the embodiments described below are only some embodiments of this invention, and not all embodiments. Based on the embodiments of this patent, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of this patent.

[0023] Example 1 In a typical embodiment of the present invention, such as Figures 1-8 As shown, an automatic wear detection device for the internal structure of an aircraft landing gear sleeve is proposed, comprising: a platform 1, a laser ultrasonic detector 2, a traction mechanism 3, a locking mechanism 4, and a support and limiting frame 5. The support and limiting frame 5 is rotatably mounted on the platform 1, and the upper part of the support and limiting frame 5 is used to support and limit the vertically placed aircraft landing gear sleeve 11. The laser ultrasonic detector 2 is vertically movable and mounted above the platform 1, and the direction of the detection signal emitted by the laser ultrasonic detector 2 is parallel to the horizontal plane. Two traction mechanisms 3 are provided and are arranged opposite each other on the upper and lower sides of the platform 1. Both traction mechanisms 3 are fixedly connected to the platform 1, and both traction mechanisms 3 include a traction rope 31. The laser ultrasonic detector 2 is fixedly mounted on the end of the traction rope 31 of the upper traction mechanism 3. The locking mechanism 4 is fixedly mounted on the end of the traction rope 31 of the lower traction mechanism 3. The initial position of the locking mechanism 4 is placed on the platform 1, and the locking mechanism 4 is detachably connected to the lower part of the laser ultrasonic detector 2. Both the locking mechanism 4 and the laser ultrasonic detector 2 are vertically movable inside the aircraft landing gear sleeve 11.

[0024] To address the issue of component wear caused by contact-based inspection, the laser ultrasonic inspection instrument 2 uses a laser to excite ultrasonic waves and then captures the echo signal through a receiving device to determine internal defects. The entire process does not require physical contact with the inner wall of the sleeve, thus avoiding the risk of wear on the inner wall of the aircraft landing gear sleeve 11 from the source. At the same time, it can also achieve accurate identification of deeper and more subtle defects.

[0025] like Figures 1-3As shown, the support limit frame 5 is rotatably mounted on the platform 1, and the aircraft landing gear sleeve 11 is vertically mounted on the support limit frame 5. The axis of rotation formed when the support limit frame 5 rotates is coaxial with the aircraft landing gear sleeve 11. The rotation drive mechanism 6 is located on one side of the support limit frame 5 to drive the rotation of the support limit frame 5.

[0026] Specifically, the rotary drive mechanism 6 includes a second rotary driver 61 and a transmission assembly. The second rotary driver 61 is fixedly installed at the bottom of the platform 1 and located on one side of the support limit frame 5. The transmission assembly is connected to the end of the second rotary driver 61 and the support limit frame 5 respectively. The second rotary driver 61 drives the support limit frame 5 to rotate through the transmission assembly.

[0027] The transmission component can be a gear drive or a belt drive. In this embodiment, the transmission component includes a gear 62 and a gear ring 63. The gear ring 63 is fixedly sleeved on the periphery of the support limit frame 5. The gear 62 is fixedly mounted on the output end of the second rotary driver 61. The gear 62 meshes with the gear ring 63. The second rotary driver 61 is a servo motor.

[0028] A clamping mechanism 51 is provided on the support limit frame 5 to limit the vertically arranged aircraft landing gear sleeve 11. The clamping mechanism 51 is an arc-shaped claw structure. There are two clamping mechanisms 51 arranged opposite each other. The clamping mechanism 51 can be electrically driven, pneumatically driven or hydraulically driven according to the actual situation. Since the clamping mechanism 51 is existing technology, it will not be described in detail here.

[0029] When the aircraft landing gear sleeve 11 is placed vertically on the support limit frame 5, the two oppositely arranged clamping mechanisms 51 can clamp and fix the aircraft landing gear sleeve 11; after the test is completed, the clamping mechanism 51 releases the aircraft landing gear sleeve 11, and then the aircraft landing gear sleeve 11 can be removed.

[0030] Since the detection end of the laser ultrasonic testing instrument 2 needs to transmit laser signals through optical fiber, and the optical fiber itself is a flexible material, it cannot provide sufficient rigid support for the detection end, nor can it guide the detection end to stably penetrate into the narrow internal space of the sleeve. In order to improve the detection accuracy and reduce the size of the testing equipment, this embodiment has a support limiting frame 5 rotatably set on the platform 1. First, the aircraft landing gear sleeve 11 is placed vertically on the support limiting frame 5. Then, the aircraft landing gear sleeve 11 placed on the support limiting frame 5 is limited to prevent the vertically placed aircraft landing gear sleeve 11 from tipping over. The traction mechanism 3 is started. The traction mechanism 3 located on the upper side runs first. The traction mechanism 3 located on the upper side releases its traction rope 31, so that... As the laser ultrasonic detector 2 descends, the locking mechanism 4 connects to the lower traction mechanism 3 and is positioned above the platform 1. As the laser ultrasonic detector 2 continues to descend, its lower part eventually contacts the locking mechanism 4, completing the locking. Subsequently, the lower traction mechanism 3 and the upper traction mechanism 3 work in sync. The traction rope 31 moves in opposite directions at the same speed. Specifically, when the upper traction mechanism 3 winds up its internal traction rope 31 at a constant speed, the lower traction mechanism 3 releases its internal traction rope 31 at the same speed. Under the traction of the upper and lower traction ropes 31, the laser ultrasonic detector 2 rises or falls stably.

[0031] In this embodiment, the traction mechanism 3 is a winch-type traction structure, which includes a motor, drum, reducer and brake, etc. This is an existing technology, and the specific structure will not be described in detail here. The laser ultrasonic detector 2 uses cyclic detection during the detection process, that is, the laser ultrasonic detector 2 needs to repeatedly rise and fall. Each rise or fall is a detection stroke. After each detection stroke is completed, the support limit frame 5 will drive the aircraft landing gear sleeve 11 to rotate a set angle. Then the laser ultrasonic detector 2 will start the next round of detection stroke until the inner wall of the aircraft landing gear sleeve 11 is completely swept. After the sweep is completed, the laser ultrasonic detector 2 will descend to the initial connection position, that is, the laser ultrasonic detector 2 will descend to the lowest position. The locking mechanism 4 will separate from the lower part of the laser ultrasonic detector 2. The traction mechanism 3 located on the upper side will pull the laser ultrasonic detector 2 to rise and reset through its traction rope 31.

[0032] Compared to traditional horizontal placement testing, vertical placement of the aircraft landing gear sleeve 11, along with two traction mechanisms 3 to pull the laser ultrasonic testing instrument 2, avoids the situation where the horizontal length of the testing equipment is too large due to the support rod. That is, the length of the testing equipment is at least twice that of the aircraft landing gear sleeve 11. In this embodiment, considering the lowering amount of the laser ultrasonic testing instrument 2, the height of the equipment is only 1.2 times that of the aircraft landing gear sleeve 11, while ensuring that the aircraft landing gear sleeve 11 can be installed, thus reducing the footprint. At the same time, under the dual traction of the two traction mechanisms 3, the testing end of the laser ultrasonic testing instrument 2 is always perpendicular to the inner wall of the aircraft landing gear sleeve 11, ensuring the accuracy of the test.

[0033] In this embodiment, each traction mechanism 3 is provided with multiple traction ropes 31. This is because when the traction mechanism 3 is provided with only one traction rope 31, the contact points between the traction rope 31 and the laser ultrasonic detector 2 converge at one point. When the upper traction mechanism 3 releases the traction rope 31, the laser ultrasonic detector 2 will sway as it descends with the traction rope 31. This can cause the laser ultrasonic detector 2 to easily come into contact with the inner wall of the aircraft landing gear sleeve 11 during descent, resulting in damage to both the laser ultrasonic detector 2 and the aircraft landing gear sleeve 11 during the inspection process. In addition, during the testing process, although the upper and lower parts of the laser ultrasonic testing instrument 2 are connected to traction ropes 31 to prevent the laser ultrasonic testing instrument 2 from swaying around the end of a single traction rope 31, it is still unavoidable that the laser ultrasonic testing instrument 2 will sway left and right on the horizontal plane during the lifting and lowering process. This causes the actual testing trajectory of the laser ultrasonic testing instrument 2 to deviate from the preset testing trajectory after completing one testing stroke. The preset testing trajectory should be a straight line and parallel to the axis of the aircraft landing gear sleeve 11, while the actual testing trajectory is an undulating curve.

[0034] Therefore, in order to reduce the vertical rotation of the laser ultrasonic detector 2, each traction mechanism 3 in this embodiment is equipped with multiple traction ropes 31, so that the laser ultrasonic detector 2 can be subjected to force at multiple points. By subjecting the laser ultrasonic detector 2 to force at multiple points, it is impossible for the laser ultrasonic detector 2 to rotate in the vertical direction, and it is also less prone to shaking, which improves the stability during descent. This makes the detection trajectory of the laser ultrasonic detector 2 tend to be straight, improves the detection accuracy, and avoids the detection blind zone caused by the rotation of the laser ultrasonic detector 2.

[0035] In this embodiment, the multiple traction ropes 31 of each traction mechanism 3 are divided into two groups and symmetrically distributed about the center of gravity of the laser ultrasonic detector 2. By dividing the multiple traction ropes 31 into two groups and symmetrically distributing them about the center of gravity of the laser ultrasonic detector 2, the traction ropes 31 are not all set on one side of the center of gravity of the laser ultrasonic detector 2, and the stability of the laser ultrasonic detector 2 during the lifting process is further improved.

[0036] like Figure 8 As shown, the testing equipment also includes a first locking seat 7 and a second locking seat 8. The first locking seat 7 is fixedly installed at the lower end of the laser ultrasonic testing instrument 2, and a locking cavity 71 is opened inside the first locking seat 7. The second locking seat 8 is fixedly installed at the upper end of the traction rope 31 located on the lower side. The locking mechanism 4 is installed on the second locking seat 8. The locking mechanism 4 is used to detachably connect with the locking cavity 71. Specifically, under the traction of the traction mechanism 3 located on the upper side, the laser ultrasonic testing instrument 2 drives the first locking seat 7 to gradually approach the second locking seat 8. When the bottom end of the first locking seat 7 contacts the upper end of the second locking seat 8, the locking mechanism 4 engages into the locking cavity 71 to realize the fixed connection between the laser ultrasonic testing instrument 2 and the two traction mechanisms 3. Then, the upper and lower traction mechanisms 3 start to drive the laser ultrasonic testing instrument 2 to rise and fall.

[0037] like Figures 6-8 As shown, the snap-fit ​​mechanism 4 includes a snap-fit ​​block 421 and a first rotary driver 422. The snap-fit ​​block 421 is an elongated structure and is rotatably disposed at the upper end of the second snap-fit ​​seat 8. A through groove 72 with the same horizontal projection shape as the snap-fit ​​block 421 is provided at the lower end of the first snap-fit ​​seat 7, and the through groove 72 communicates with the snap-fit ​​cavity 71. The first rotary driver 422 is fixedly disposed in the second snap-fit ​​seat 8, and the output end of the first rotary driver 422 is fixedly connected to the snap-fit ​​block 421 to drive the snap-fit ​​block 421 to rotate around the axis.

[0038] As the first contact seat 7 gradually approaches the second contact seat 8 along with the laser ultrasonic detector 2, it is in the pre-detection preparation stage. With the descent of the first contact seat 7, the contact block 421 first passes through the through slot 72 and then enters the contact cavity 71. The contact block 421, upon entering the contact cavity 71, does not yet fully engage with it. The first rotary driver 422 drives the contact block 421 to rotate at a set angle, causing the horizontal projection of the through slot 72 to be misaligned with (e.g., perpendicular to) the horizontal projection of the contact block 421, thus completing the engagement. After engagement, the upper and lower... Two traction mechanisms 3 pull the laser ultrasonic detector 2 at the same speed. If the upper traction mechanism 3 retracts its traction rope 31, the lower traction mechanism 3 releases its traction rope 31; conversely, if the upper traction mechanism 3 releases its traction rope 31, the lower traction mechanism 3 retracts its traction rope 31. The traction speed of the upper and lower traction mechanisms 3 on the laser ultrasonic detector 2 is always the same. In practical applications, a synchronizer can be set to synchronize the traction speed of the two traction mechanisms 3, ensuring the stable lifting and lowering of the laser ultrasonic detector 2.

[0039] The lower end of the first card holder 7 is provided with an insertion port, and the slot 72 is located in the insertion port. Several limiting strips 73 are fixedly provided on the inner wall of the insertion port at intervals along its circumference. The limiting strips 73 extend vertically. Several limiting grooves 81 are vertically provided on the outer peripheral wall of the second card holder 8. The limiting strips 73 slide with the limiting grooves 81. The upper edge of the upper end face of the second card holder 8 and the upper end of the limiting grooves 81 are both provided with chamfers, which improves the fault tolerance when the limiting strips 73 slide into the limiting grooves 81.

[0040] When the locking block 421 engages with the locking cavity 71, the distance between the laser ultrasonic detector 2 and the upper traction mechanism 3 is relatively large, causing the laser ultrasonic detector 2 to still experience slight shaking before the engagement is completed. The limiting groove 81 and the limiting strip 73 can achieve preliminary positioning of the first locking seat 7 and the second locking seat 8, ensuring that the locking block 421 can coincide with the through groove 72, thereby ensuring that the locking block 421 can smoothly pass through the through groove 72 and engage with the locking cavity 71. In addition, when the locking block 421 engages with the locking cavity 71, the locking block 421 needs to rotate within the locking cavity 71, which may cause the locking block 421 to come into contact with the inner wall of the locking cavity 71, causing the first locking seat 7 to be subjected to torsional force. However, by limiting the first locking seat 7 and the second locking seat 8 through the cooperation of the limiting strip 73 and the limiting groove 81, the pulling effect of the torsional force on the traction rope 31 can be reduced, extending the service life of the traction rope 31.

[0041] A magnet 9 is fixedly installed on the second card holder 8. The first card holder 7 is made of ferromagnetic material. The magnet 9 can generate a magnetic attraction to the first card holder 7. Under the magnetic attraction, the first card holder 7, which is located at the lower end of the laser ultrasonic detector 2, generates a vertical downward pulling force on the laser ultrasonic detector 2, so that the traction rope 31, which is located at the upper part of the laser ultrasonic detector 2, is straightened. Before the limiting strip 73 slides into the limiting groove 81, the first card holder 7 and the second card holder 8 can be automatically aligned, ensuring that the limiting strip 73 can slide smoothly into the limiting groove 81.

[0042] Example 2 In another typical embodiment of the present invention, a detection method is proposed, which uses the automatic detection equipment for internal wear of aircraft landing gear sleeves mentioned in Example 1. The detection method specifically includes: The aircraft landing gear sleeve 11 is placed vertically on the support limit frame 5 to limit the aircraft landing gear sleeve 11. The upper traction mechanism 3 releases the traction rope 31, and the laser ultrasonic detector 2 descends with the traction rope 31 and enters the aircraft landing gear sleeve 11. When the lower end face of the laser ultrasonic detector 2 is at the same height as the upper end face of the platform 1, the locking mechanism 4 locks with the laser ultrasonic detector 2. The two traction mechanisms 3 distributed at the top and bottom drive the laser ultrasonic detector 2 to rise and fall at the same speed. One rise or fall of the laser ultrasonic detector 2 is one detection stroke. After each inspection cycle is completed, the support limiter 5 rotates at a set angle along the axis of the aircraft landing gear sleeve 11 and stops. Then the laser ultrasonic detector 2 begins to complete the next inspection cycle, repeating the cycle until the inner wall of the aircraft landing gear sleeve 11 is completely swept.

[0043] Specifically, the aircraft landing gear sleeve 11 to be inspected is first placed vertically on the support limit frame 5 of the platform 1. Then, the gripper-type clamping mechanism 51 on the support limit frame 5 is activated. The clamping force is adjusted according to the size of the aircraft landing gear sleeve 11 to firmly limit it and prevent it from tipping over or shifting during the inspection. At the same time, it is ensured that the rotation axis of the support limit frame 5 is coaxial with the axis of the sleeve, laying the foundation for the subsequent full-circumference sweep inspection.

[0044] At this time, the upper and lower traction mechanisms 3 are in the initial state. The multiple traction ropes 31 of the upper traction mechanism 3 are divided into two groups and are symmetrically distributed about the center of gravity of the laser ultrasonic detector 2, suspending the laser ultrasonic detector 2. The ends of the traction ropes 31 of the lower traction mechanism 3 are connected to the second locking seat 8 with the locking mechanism 4, and both are in the standby state.

[0045] The upper traction mechanism 3 is activated, and its traction rope 31 is slowly released at a preset speed. The laser ultrasonic detector 2 then descends and gradually passes through the vertically placed landing gear sleeve. During the descent, the symmetrical distribution of multiple traction ropes 31 reduces the swaying amplitude of the laser ultrasonic detector 2 and prevents the laser ultrasonic detector 2 from rotating in the vertical direction, thus preventing it from colliding with the inner wall of the sleeve.

[0046] When the laser ultrasonic detector 2 descends to the point where its lower end face is flush with the upper end face of the platform 1, the first locking seat 7 fixed at its lower end and the second locking seat 8 on its lower side gradually approach each other. The magnet 9 on the second locking seat 8 generates a magnetic attraction, pulling the first locking seat 7 to automatically align. At the same time, the limiting strip 73 at the lower part of the first locking seat 7 slides along the limiting groove 81 on the outer side of the second locking seat 8 to achieve initial positioning. Then, the locking block 421 passes through the through groove 72 of the first locking seat 7 and enters the locking cavity 71. The first rotary driver 422 drives the locking block 421 to rotate at a set angle, so that the horizontal projection of the locking block 421 and the through groove 72 are misaligned, thus completing the stable locking.

[0047] Subsequently, the upper and lower traction mechanisms 3 operate simultaneously. The upper traction rope 31 retracts at the same speed as the lower traction rope 31 releases, or vice versa, to drive the laser ultrasonic detector 2 to rise or fall stably along the sleeve axis. Each rise or fall constitutes one complete detection stroke. During the detection process, the laser ultrasonic detector 2 emits detection signals in a horizontal direction. Due to the dual constraints of the dual traction mechanisms 3 and the multi-point force of the multiple symmetrical traction ropes 31, the detector maintains a stable posture at all times. The detection end is perpendicular to the inner wall of the sleeve, effectively avoiding detection errors caused by the bending of traditional support rods. At the same time, the non-contact detection mode avoids inner wall wear at the source.

[0048] After each inspection cycle is completed, the second rotary driver 61 drives the support limit frame 5 to rotate at a set angle through the gear 62 and the gear ring 63, so as to drive the sleeve to rotate synchronously. Then the laser ultrasonic detector 2 starts the next round of lifting and lowering inspection. This cycle repeats until the entire circumference of the inner wall of the aircraft landing gear sleeve 11 is swept to ensure that there are no blind spots in the inspection.

[0049] After the test is completed, the laser ultrasonic testing instrument 2 is first lowered to the lowest position. The first rotary driver 422 rotates in the opposite direction, so that the locking block 421 coincides with the horizontal projection of the through slot 72, releasing the locking constraint. The lower traction mechanism 3 stops running. Then the upper traction mechanism 3 winds up the traction rope 31, driving the laser ultrasonic testing instrument 2 to rise and reset. When the laser ultrasonic testing instrument 2 returns to the initial suspension position, the clamping mechanism 51 on the support limit frame 5 releases the limit on the sleeve, and the operator removes the tested aircraft landing gear sleeve 11.

[0050] The above description of the disclosed embodiments enables those skilled in the art to make or use the invention. Various modifications to these embodiments will be readily apparent to those skilled in the art, and the general principles defined herein may be implemented in other embodiments without departing from the spirit or scope of the invention. Therefore, the invention is not to be limited to the embodiments shown herein, but is to be accorded the widest scope consistent with the principles and novel features disclosed herein.

Claims

1. An automatic wear detection device for the internal structure of an aircraft landing gear sleeve, comprising: Platform (1), characterized in that a support limiting frame (5) is rotatably provided on the platform (1), and the support limiting frame (5) is used to support and limit the vertically placed aircraft landing gear sleeve (11). A laser ultrasonic detector (2) is vertically mounted above the platform (1), and the direction in which the laser ultrasonic detector (2) emits detection signals is parallel to the horizontal plane. The platform (1) has two traction mechanisms (3) on its upper and lower sides. The upper traction mechanism (3) is fixedly connected to the laser ultrasonic detector (2) below it via a traction rope (31). The lower traction mechanism (3) is fixedly connected to a snap-fit ​​mechanism (4) via a traction rope (31). The snap-fit ​​mechanism (4) is detachably connected to the lower part of the laser ultrasonic detector (2).

2. The automatic wear detection device for the internal structure of aircraft landing gear sleeves according to claim 1, characterized in that, The two traction mechanisms (3) are linked synchronously, and the traction ropes (31) of the two traction mechanisms (3) are pulled in and out in opposite directions and at the same speed.

3. The automatic wear detection device for the internal structure of aircraft landing gear sleeves according to claim 1, characterized in that, Each traction mechanism (3) is equipped with multiple traction ropes (31), which are divided into two groups and are symmetrically distributed about the center of gravity of the laser ultrasonic detector (2).

4. The automatic wear detection device for the internal wear of aircraft landing gear sleeves according to claim 1, characterized in that, The lower end of the laser ultrasonic detector (2) is fixedly connected to a first snap-fit ​​seat (7), and the snap-fit ​​mechanism (4) is fixedly connected to the traction rope (31) through a second snap-fit ​​seat (8). The snap-fit ​​mechanism (4) is snapped into the first snap-fit ​​seat (7).

5. The automatic wear detection device for the internal structure of aircraft landing gear sleeves according to claim 4, characterized in that, The first card holder (7) has a card cavity (71) and a through groove (72) at the lower end of the first card holder (7). The through groove (72) communicates with the card cavity (71). The card mechanism (4) includes a first rotary driver (422). A card block (421) is fixedly installed at the output end of the first rotary driver (422). The card block (421) is a long strip structure and its horizontal projection shape is the same as that of the through groove (72).

6. The automatic wear detection device for the internal structure of aircraft landing gear sleeves according to claim 5, characterized in that, The lower end of the first card holder (7) is provided with an insertion port, and the slot (72) is located inside the insertion port. Several limiting strips (73) are fixedly provided on the inner wall of the insertion port along its circumferential interval. The limiting strips (73) extend vertically. Several limiting grooves (81) are vertically provided on the outer peripheral wall of the second card holder (8). The limiting strips (73) and the limiting grooves (81) slide together.

7. The automatic wear detection device for the internal wear of aircraft landing gear sleeves according to claim 4, characterized in that, A magnet (9) is fixedly installed on the second card holder (8), and the first card holder (7) is made of ferromagnetic material.

8. The automatic wear detection device for the internal wear of aircraft landing gear sleeves according to claim 1, characterized in that, The support limit frame (5) is connected to a rotary drive mechanism (6), and the support limit frame (5) is provided with two clamping mechanisms (51) arranged opposite to each other.

9. A detection method, characterized in that, The automatic wear detection equipment for the internal wear of aircraft landing gear sleeves as described in any one of claims 1-8 includes: Place the aircraft landing gear sleeve (11) vertically on the support limit frame (5) and limit its position; The upper traction mechanism (3) releases the traction rope (31), and the laser ultrasonic detector (2) moves downward inside the aircraft landing gear sleeve (11) to approach the locking mechanism (4). The locking mechanism (4) locks with the laser ultrasonic detector (2). The two traction mechanisms (3) distributed above and below drive the laser ultrasonic detector (2) to rise and fall at the same speed. The laser ultrasonic detector (2) completes one rise or one fall, which is one detection stroke. After each test stroke is completed, the support limit frame (5) rotates at a set angle along the axis of the aircraft landing gear sleeve (11) and stops. Then the laser ultrasonic detector (2) starts the next test stroke, repeating the cycle until the inner wall of the aircraft landing gear sleeve (11) is completely swept.

10. The detection method according to claim 9, characterized in that, The process of the snap-fit ​​mechanism (4) snapping with the laser ultrasonic detector (2) is as follows: when the first snap-fit ​​seat (7) and the second snap-fit ​​seat (8) gradually approach each other, the magnet (9) on the second snap-fit ​​seat (8) generates a magnetic attraction, pulling the first snap-fit ​​seat (7) to automatically align. At the same time, the limiting strip (73) slides along the limiting groove (81) to achieve preliminary positioning. After the snap-fit ​​block (421) passes through the through groove (72), it enters the snap-fit ​​cavity (71). The first rotary driver (422) drives the snap-fit ​​block (421) to rotate at a set angle.

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