A wing compression detection device for target drone production

Abstract

The present application relates to a kind of wing compression detection device for target machine production, including detection table, detection mechanism and bearing mechanism;The detection mechanism and bearing mechanism are installed on detection table, and the bearing mechanism is in the middle position of detection mechanism;The bearing mechanism includes bearing table, bearing frame and bearing shell, the bearing table is installed on the surface of detection table, the bearing frame is installed on bearing table by support column, the bearing shell is configured to the surface of bearing frame, and bearing frame and bearing shell form cavity and provide movement space for iron core.This wing compression detection device can automatically adjust the telescopic distance of each iron core according to the wing curvature by the independent telescopic movement of multiple iron cores and the meshing mechanism of linkage disc and long gear, realize personalized fitting, avoid the problem of inadaptation to arc surface by traditional fixed bearing mode.

Description

Technical Field

[0001] This invention belongs to the field of pressure resistance testing technology, specifically a pressure resistance testing device for the wings of a target drone. Background Technology

[0002] In the field of target drone production, the wings are a key component, and their compressive strength directly affects the overall structural stability and operational safety.

[0003] Since the surface of the wing itself is not flat but curved, the wing placement platform is usually flat or fixed in shape, which cannot effectively adapt to the curvature characteristics of the target aircraft wing. This results in uneven support at different positions, and the workpiece is prone to local warping or displacement during the testing process, affecting the accuracy of the test data. Furthermore, as the extrusion test progresses, the wing will shift from the placement seat, affecting the efficiency of the compression test.

[0004] In view of this, a wing pressure resistance testing device for target drone production is proposed. Summary of the Invention

[0005] The purpose of this section is to outline some aspects of embodiments of the present invention and to briefly describe some preferred embodiments. Simplifications or omissions may be made in this section, as well as in the abstract and title of this application, to avoid obscuring the purpose of these documents; however, such simplifications or omissions should not be construed as limiting the scope of the invention.

[0006] Given the following technical problems in the existing technology: Since the surface of the wing itself is not flat but curved, the wing placement platform is usually flat or fixed in shape, which cannot effectively adapt to the curvature characteristics of the target aircraft wing, resulting in uneven support at different positions. The workpiece is prone to local warping or displacement during the testing process, affecting the accuracy of the test data. Furthermore, as the extrusion test progresses, the wing will shift from the placement seat, affecting the efficiency of the compression test.

[0007] To solve the above-mentioned technical problems, the present invention provides the following technical solution: a wing compression resistance testing device for target drone production, comprising a testing table, a testing mechanism, and a supporting mechanism;

[0008] The testing mechanism and the supporting mechanism are installed on the testing platform, with the supporting mechanism located in the middle of the testing mechanism;

[0009] The bearing mechanism includes a bearing platform, a bearing frame, and a bearing shell. The bearing platform is installed on the surface of the testing table, the bearing frame is installed on the bearing platform by a support column, and the bearing shell is disposed on the surface of the bearing frame. The bearing frame and the bearing shell form a cavity to provide movement space for the iron core.

[0010] The support frame includes an upper ring frame, an inner toothed ring, and a bottom shell. The upper ring frame is connected to a support column on the support platform. The inner toothed ring is hinged to the bottom of the upper ring frame. The bottom shell is hinged to the bottom of the inner toothed ring. The outer periphery of the bottom shell is installed on the support column of the support platform by a clamp to ensure that the inner toothed ring does not drive the bottom shell to rotate when it rotates.

[0011] A positioning plate is installed on the inner edge of the upper ring frame, the iron core is telescopically engaged with the positioning plate, and a spiral winding is arranged between the bearing shell and the upper ring frame.

[0012] The bearing shell and bearing frame contain multiple iron cores that can move telescopically. The spiral winding is spirally wrapped around the iron cores. After the spiral winding is input current, it can magnetize the iron cores. A suction cup is movably installed at the end of the iron core that extends out of the bearing shell.

[0013] A pipe is fixedly connected to the inner edge of the iron core, and a fixed plate is installed on the inner edge of the top end of the pipe. A spline shaft is telescopically mounted on the fixed plate. The special shape of the spline shaft ensures that the spline shaft will not rotate on its own.

[0014] As a preferred technical solution for a wing pressure testing device used in target drone production, the device (200) includes a support arm, a movable frame, a hydraulic assembly, and a testing head. The support arm is mounted on a testing platform and is arranged in a pair, symmetrically distributed on both sides of the bearing mechanism. The movable frame extends and retracts along the inner edge of the pair of support arms. The support arm is equipped with a Y-axis motion mechanism that can drive the movable frame to extend and retract. This mechanism is common knowledge and will not be elaborated on here. The hydraulic assembly is mounted below the movable frame, and the testing head is mounted at the output end of the testing head. The movable frame drives the hydraulic assembly and the testing head to approach the surface of the target drone wing. The hydraulic assembly drives the testing head to perform a pressure test on the surface of the target drone wing, and the pressure sensor in the hydraulic assembly outputs data.

[0015] As a preferred technical solution for a wing pressure testing device used in target drone production, multiple long gears are hinged between the positioning disk and the bottom shell.

[0016] As a preferred technical solution for a wing pressure testing device used in target drone production, a linkage disc is installed at the bottom of the iron core. The outer contour of the linkage disc is milled with tooth grooves. The thickness of the long gear and the inner gear ring is greater than the thickness of the linkage disc, ensuring that multiple iron cores can mesh when they extend and retract to different positions. The linkage disc meshes with the long gear, and the outermost linkage disc meshes with the inner gear ring. The remaining linkage discs are driven to rotate synchronously by the long gear.

[0017] As a preferred technical solution for a wing pressure testing device used in target drone production, an elastic element A is configured between the linkage disk and the bottom shell. The elastic element A facilitates the reset of multiple iron cores, making it convenient to apply them to another wing in the future. The surface of the iron core is milled with multiple equally spaced limiting grooves.

[0018] As a preferred technical solution for a wing pressure testing device for target drone production, the surface of the bearing shell is reserved with multiple guide channels, the iron core moves telescopically on the guide channels, a pair of cavities are milled along the inner edge of the guide channels, a magnetic block moves telescopically in the cavity, and the magnetic block and the limiting groove are fitted together.

[0019] As a preferred technical solution for a wing pressure testing device used in target drone production, the upper and lower inner edges of the cavity are milled with guide grooves. Guide blocks are fixedly connected to the upper and lower sides of the end of the magnetic block in the cavity. The guide blocks extend and retract in the guide grooves. After the iron core is magnetized, the magnetic block will move toward the position of the iron core. The guide blocks and guide grooves play a guiding and stabilizing role in this process.

[0020] As a preferred technical solution for a wing pressure testing device used in target drone production, a sealing block is fitted at the top of the spline shaft, and an elastic element B is installed between the back of the sealing block and the surface of the fixed plate. The elastic element B surrounds the outer periphery of the spline shaft, and can drive the sealing block to perform a reset operation when the sealing block is not under force.

[0021] As a preferred technical solution for a wing pressure testing device used in target drone production, a baffle is fixedly connected to the inner edge of the suction cup, and a connecting channel is opened on the baffle. The shape of the connecting channel is adapted to the top shape of the sealing block.

[0022] As a preferred technical solution for a wing pressure testing device used in target drone production, a top block A is installed on the outer contour of the sealing block, with the arc-shaped end of the top block A facing upwards, and a top block B is installed on the back of the baffle, with the arc-shaped end of the top block B facing downwards.

[0023] The beneficial effects of this invention are:

[0024] 1. The wing compression testing device can automatically adjust the extension distance of each iron core according to the wing curvature through the independent telescopic movement of multiple iron cores and the meshing mechanism of the linkage disc and the long gear, so as to achieve personalized fit and avoid the problem of the traditional fixed bearing method being unsuitable for curved surfaces.

[0025] 2. The wing compression testing device uses a helical winding to magnetize the iron core, combined with the interlocking connection of the magnetic block and the limiting groove, as well as the rotation drive of the internal gear ring, to achieve synchronous fixation of multiple iron cores and suction cups, ensuring that the wing is not prone to misalignment, warping or sliding during the testing process, and improving the overall load-bearing stability.

[0026] 3. The wing pressure testing device can effectively discharge the gas between the suction cup and the wing by combining the plastic deformation of the upper part of the suction cup with the sealing mechanism of the pipe, the sealing block and the elastic element B, so as to maintain a small gas space and further improve the contact stability and the anti-displacement ability during pressure testing.

[0027] 4. The wing compression testing device is equipped with elastic element A and elastic element B, as well as a magnetic block release mechanism under reverse current control, which facilitates the rapid reset of the iron core and sealing block, simplifies the operation process, improves the reusability of the device, and is suitable for batch production testing.

[0028] Other features and advantages of the invention will be set forth in the description which follows, and will be apparent in part from the description, or may be learned by practicing the invention. The objects and other advantages of the invention may be realized and obtained by means of the structures particularly pointed out in the description and the drawings. Attached Figure Description

[0029] To more clearly illustrate the technical solutions of the embodiments of the present invention, the accompanying drawings used in the description of the embodiments will be briefly introduced below. Obviously, the 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. Wherein:

[0030] Figure 1 This is a schematic diagram of the overall structure of the present invention.

[0031] Figure 2 This is a schematic diagram of the support shell of the present invention.

[0032] Figure 3 Based on the present invention Figure 2 Cross-sectional diagram.

[0033] Figure 4 This is a schematic diagram of the iron core of the present invention.

[0034] Figure 5 Based on the present invention Figure 4 Schematic diagram at point X in the middle.

[0035] Figure 6 This is a schematic diagram of the pipeline of the present invention.

[0036] Figure 7 This is a schematic diagram of the baffle and sealing block of the present invention.

[0037] Figure 8 Based on the present invention Figure 7 A schematic diagram from another perspective.

[0038] Figure label:

[0039] 100. Testing table; 200. Testing mechanism; 201. Support arm; 202. Moving frame; 203. Hydraulic assembly; 204. Testing head; 300. Bearing mechanism; 301. Bearing platform; 302. Bearing frame; 302a. Upper ring frame; 302b. Internal gear ring; 302c. Bottom shell; 303. Bearing shell; 304. Positioning plate; 305. Helical winding; 306. Long gear; 400. Iron core; 401. Suction cup; 402. Linkage plate; 403. Elastic element A; 404. Limiting groove; 500. Guide channel; 501. Cavity; 502. Guide trench; 503. Magnetic block; 504. Guide block; 600. Pipe; 601. Baffle; 602. Connecting channel; 603. Fixed plate; 604. Splined shaft; 606. Elastic element B; 607. Sealing block; 608. Top block A; 609. Top block B. Detailed Implementation

[0040] To make the above-mentioned objects, features and advantages of the present invention more apparent and understandable, the specific embodiments of the present invention will be described in detail below with reference to the accompanying drawings.

[0041] Many specific details are set forth in the following description in order to provide a full understanding of the invention. However, the invention may also be practiced in other ways different from those described herein, and those skilled in the art can make similar extensions without departing from the spirit of the invention. Therefore, the invention is not limited to the specific embodiments disclosed below.

[0042] Secondly, the term "an embodiment" or "embodiment" as used herein refers to a specific feature, structure, or characteristic that may be included in at least one implementation of the present invention. The phrase "in one embodiment" appearing in different places throughout this specification does not necessarily refer to the same embodiment, nor is it a single embodiment or an embodiment selectively excluded from other embodiments.

[0043] Secondly, the present invention is described in detail with reference to the schematic diagrams. When detailing the embodiments of the present invention, for ease of explanation, the cross-sectional views illustrating the device structure may be partially enlarged, not according to the usual scale. Furthermore, the schematic diagrams are merely examples and should not limit the scope of protection of the present invention. In addition, actual fabrication should include three-dimensional spatial dimensions of length, width, and depth.

[0044] Example, reference Figure 1 A wing pressure resistance testing device for target drone production includes a testing platform 100, a testing mechanism 200, and a support mechanism 300.

[0045] The testing mechanism 200 and the supporting mechanism 300 are installed on the testing table 100, with the supporting mechanism 300 located in the middle of the testing mechanism 200;

[0046] refer to Figure 1The testing mechanism 200 includes a support arm 201, a movable frame 202, a hydraulic assembly 203, and a testing head 204. The support arm 201 is mounted on the testing table 100. The support arms 201 are arranged in a pair, symmetrically distributed on both sides of the bearing mechanism 300. The movable frame 202 extends and retracts along the inner edge of the pair of support arms 201. The support arm 201 is equipped with a Y-axis motion mechanism that can drive the movable frame 202 to extend and retract. This mechanism is common knowledge and will not be elaborated on here. The hydraulic assembly 203 is mounted below the movable frame 202. The testing head 204 is mounted at the output end of the testing head 204. The movable frame 202 drives the hydraulic assembly 203 and the testing head 204 to approach the surface of the target aircraft wing. The hydraulic assembly 203 drives the testing head 204 to perform a pressure test on the surface of the target aircraft wing, and the pressure sensor in the hydraulic assembly 203 outputs data.

[0047] refer to Figure 1 and 2 The bearing mechanism 300 includes a bearing platform 301, a bearing frame 302, and a bearing shell 303. The bearing platform 301 is mounted on the surface of the testing table 100. The bearing frame 302 is mounted on the bearing platform 301 by a support column. The bearing shell 303 is disposed on the surface of the bearing frame 302. The bearing frame 302 and the bearing shell 303 form a cavity to provide movement space for the iron core 400.

[0048] refer to Figure 2 and 3 The support frame 302 includes an upper ring frame 302a, an internal toothed ring 302b, and a bottom shell 302c. The upper ring frame 302a is connected to the support column on the support platform 301. The internal toothed ring 302b is hinged to the bottom of the upper ring frame 302a. The bottom shell 302c is hinged to the bottom of the internal toothed ring 302b. The outer periphery of the bottom shell 302c is installed on the support column of the support platform 301 by a clamp to ensure that the internal toothed ring 302b will not drive the bottom shell 302c to rotate when it rotates.

[0049] refer to Figure 3 A positioning disk 304 is installed on the inner edge of the upper ring frame 302a. The iron core 400 is telescopically engaged with the positioning disk 304. A spiral winding 305 is configured between the bearing shell 303 and the upper ring frame 302a. Multiple long gears 306 are hinged between the positioning disk 304 and the bottom shell 302c.

[0050] refer to Figure 2 , 34 and 5, multiple iron cores 400 telescopically move within the bearing shell 303 and the bearing frame 302. A helical winding 305 spirally wraps around the iron cores 400. Upon input current, the helical winding 305 magnetizes the iron cores 400. A suction cup 401 is movably mounted on one end of the iron core 400 extending from the bearing shell 303. The upper part of the suction cup 401 is plastic, and the lower part is the bearing portion. A linkage disk 402 is mounted on the bottom end of the iron core 400. The outer contour of the linkage disk 402 is milled with toothed grooves. The thickness of the long gear 306 and the internal gear ring 302b is greater than the thickness of the linkage disk 402, ensuring the multiple iron cores 400... When the telescopic movement reaches different positions, it can play a meshing role. The linkage disk 402 meshes with the long gear 306. The outermost linkage disk 402 meshes with the internal gear ring 302b. The other linkage disks 402 are driven to rotate synchronously by the long gear 306. An elastic element A403 is arranged between the linkage disk 402 and the bottom shell 302c. The elastic element A403 facilitates the reset of multiple iron cores 400, which can be easily reused in another wing. The elastic element A403 and the linkage disk 402 only touch. The surface of the iron core 400 is milled with multiple equally spaced limiting grooves 404.

[0051] refer to Figure 4 and 5 The surface of the bearing shell 303 is provided with multiple guide channels 500. The iron core 400 moves telescopically on the guide channels 500. A pair of cavities 501 are milled along the inner edge of the guide channels 500. A magnetic block 503 moves telescopically in the cavity 501. The magnetic block 503 and the limiting groove 404 are fitted together. Guide grooves 502 are milled along the upper and lower inner edges of the cavity 501. Guide blocks 504 are fixedly connected to the upper and lower sides of the end of the magnetic block 503 in the cavity 501. The guide blocks 504 move telescopically in the guide grooves 502. After the iron core 400 is magnetized, the magnetic block 503 will move toward the position of the iron core 400. The guide blocks 504 and the guide grooves 502 play a guiding and stabilizing role in this process.

[0052] refer to Figure 6 The inner edge of the iron core 400 is fixedly connected to the pipe 600. The top inner edge of the pipe 600 is equipped with a fixed plate 603. The fixed plate 603 has a spline shaft 604 that can move telescopically. The special shape of the spline shaft 604 ensures that the spline shaft 604 will not rotate on its own. The top of the spline shaft 604 is equipped with a sealing block 607. An elastic element B606 is installed between the back of the sealing block 607 and the surface of the fixed plate 603. The elastic element B606 surrounds the outer circumference of the spline shaft 604. When the sealing block 607 is not under force, the elastic element B606 can drive it to perform a reset operation. The inner edge of the suction cup 401 is fixedly connected to the baffle 601. The baffle 601 has a connecting channel 602. The shape of the connecting channel 602 is adapted to the top shape of the sealing block 607.

[0053] refer to Figure 7 and 8 A top block A608 is installed on the outer contour of the sealing block 607, with the arc-shaped end of the top block A608 facing upwards. A top block B609 is installed on the back of the baffle 601, with the arc-shaped end of the top block B609 facing downwards.

[0054] This implementation achieves the following: In the initial state, the magnetic block 503 is not directly aligned with the limiting slot 404, while the top blocks A608 and B609 are directly aligned. When the target drone wing is placed on the supporting mechanism 300, the wing first contacts the suction cup 401. After deformation, the upper part of the suction cup 401 drives the iron core 400 to extend and retract. Due to the curvature of the wing, the extension and retraction distances of each iron core 400 are different. After the movement of each iron core 400 stabilizes, current is passed through the helical winding 305, which magnetizes the iron core 400. At this moment, the magnetic block 503 moves towards the position of the iron core 400. Subsequently, the internal gear ring 302b rotates, driving one of the outermost linkage disks 402 to rotate. This linkage disk 402 drives the long gear 306 to rotate, causing multiple linkage disks 402 to rotate synchronously. In this step… Since the thickness of the long gear 306 and the internal gear ring 302b is greater than the thickness of the linkage disk 402, it ensures that multiple iron cores 400 can mesh when they move to different positions. At this moment, the limiting groove 404 moves to the position directly opposite the magnetic block 503, and the magnetic block 503 is embedded in the limiting groove 404. At this moment, the position of each iron core 400 is limited. Multiple iron cores 400 and the suction cup 401 are all in contact with the wing, providing stable support for the wing pressure test, ensuring that the wing is not prone to misalignment or lifting during the test, and improving the accuracy of the test. During this process, the end of the magnetic block 503 facing the iron core 400 is "-", and the iron core 400 is "+". After the wing test is completed, the current flowing through the spiral winding 305 is reversed, and the iron core 400 becomes "-". At this time, the magnetic block 503 will move towards the cavity 501, and the iron core 400 is no longer restricted.

[0055] When the wing is placed on the suction cup 401, the wing compresses the upper part of the suction cup 401. The gas between the upper part of the suction cup 401 and the wing is introduced into the pipe 600 through the connecting channel 602. After the iron core 400 rotates, the pipe 600 rotates accordingly. The pipe 600 drives the fixed plate 603, and the fixed plate 603 drives the spline shaft 604 and the sealing block 607. At this time, the top block A608 rotates and is misaligned with the top block B609. Under the action of the elastic element B606, the sealing block 607 pushes to the position of the connecting channel 602. At this time, the gas between the upper part of the suction cup 401 and the wing is removed and sealed, ensuring the contact stability between the wing and the suction cup 401, and preventing the wing from shifting during the pressure test, thereby improving the stability of the test.

[0056] The mobile frame 202 drives the detection head 204 to move to the upper surface of the wing, and the hydraulic component 203 outputs control to squeeze the detection head 204, thereby performing a pressure test on the wing.

[0057] It should be understood that numerous specific implementation decisions can be made during the development of any actual implementation method, and in any engineering or design project. Such development efforts may be complex and time-consuming, but for those of ordinary skill in the art who benefit from this disclosure, the development effort will be a routine task in design, manufacturing, and production without requiring extensive experimentation.

[0058] It should be noted that the above embodiments are only used to illustrate the technical solutions of the present invention and are not intended to limit it. Although the present invention has been described in detail with reference to preferred embodiments, those skilled in the art should understand that modifications or equivalent substitutions can be made to the technical solutions of the present invention without departing from the spirit and scope of the technical solutions of the present invention, and all such modifications or substitutions should be covered within the scope of the claims of the present invention.

Claims

1. A wing compression resistance testing device for target drone production, characterized in that: It includes a testing platform (100), a testing mechanism (200), a load-bearing mechanism (300), and an iron core (400). The testing mechanism (200) and the supporting mechanism (300) are installed on the testing table (100), and the supporting mechanism (300) is located in the middle of the testing mechanism (200); The bearing mechanism (300) includes a bearing platform (301), a bearing frame (302), and a bearing shell (303). The bearing platform (301) is mounted on the surface of the testing platform (100), the bearing frame (302) is mounted on the bearing platform (301) by a support column, and the bearing shell (303) is disposed on the surface of the bearing frame (302). The support frame (302) includes an upper ring frame (302a), an inner toothed ring (302b), and a bottom shell (302c). The upper ring frame (302a) is connected to the support column on the support platform (301). The inner toothed ring (302b) is hinged to the bottom of the upper ring frame (302a). The bottom shell (302c) is hinged to the bottom of the inner toothed ring (302b). The outer periphery of the bottom shell (302c) is installed on the support column of the support platform (301) by clamps. A positioning disk (304) is installed on the inner edge of the upper ring frame (302a), the iron core (400) is telescopically engaged with the positioning disk (304), and a spiral winding (305) is arranged between the bearing shell (303) and the upper ring frame (302a). Multiple iron cores (400) telescopically move within the bearing shell (303) and the bearing frame (302). The spiral winding (305) spirally surrounds the iron cores (400), and a suction cup (401) is movably mounted on one end of the iron core (400) extending out of the bearing shell (303). The inner edge of the iron core (400) is fixedly connected to a pipe (600), and a fixed plate (603) is installed on the inner edge of the top end of the pipe (600). A spline shaft (604) is telescopically mounted on the fixed plate (603). Multiple long gears (306) are hinged between the positioning disk (304) and the bottom shell (302c). The bottom end of the iron core (400) is provided with a linkage disk (402), the outer contour of the linkage disk (402) is milled with tooth grooves, and the linkage disk (402) meshes with a long gear (306).

2. The wing compression resistance testing device for target drone production according to claim 1, characterized in that: The testing mechanism (200) includes a support arm (201), a movable frame (202), a hydraulic component (203), and a testing head (204). The support arm (201) is mounted on the testing table (100). The support arms (201) are arranged in pairs, and the pair of support arms (201) are symmetrically distributed on both sides of the bearing mechanism (300). The movable frame (202) moves telescopically along the inner edge of the pair of support arms (201). The hydraulic component (203) is mounted below the movable frame (202). The testing head (204) is mounted at the output end of the hydraulic component (203).

3. The wing compression resistance testing device for target drone production according to claim 1, characterized in that: An elastic element A (403) is disposed between the linkage disk (402) and the bottom shell (302c), and a plurality of equally spaced limiting grooves (404) are milled on the surface of the iron core (400).

4. The wing compression resistance testing device for target drone production according to claim 1, characterized in that: The surface of the bearing shell (303) is reserved with multiple guide channels (500). The iron core (400) moves telescopically on the guide channels (500). A pair of cavities (501) are milled along the inner edge of the guide channels (500). A magnetic block (503) moves telescopically in the cavity (501). The magnetic block (503) and the limiting groove (404) are fitted together.

5. The wing compression resistance testing device for target drone production according to claim 4, characterized in that: The upper and lower inner edges of the cavity (501) are milled with guide grooves (502). The magnetic block (503) is fixedly connected to guide blocks (504) on both the upper and lower sides of one end in the cavity (501). The guide blocks (504) extend and retract in the guide grooves (502).

6. The wing compression resistance testing device for target drone production according to claim 1, characterized in that: The top end of the spline shaft (604) is fitted with a sealing block (607), and an elastic element B (606) is installed between the back of the sealing block (607) and the surface of the fixed plate (603). The elastic element B (606) surrounds the outer periphery of the spline shaft (604).

7. The wing compression resistance testing device for target drone production according to claim 6, characterized in that: A baffle (601) is fixedly connected to the inner edge of the suction cup (401), and a connecting channel (602) is provided on the baffle (601). The shape of the connecting channel (602) is adapted to the top shape of the sealing block (607).

8. The wing compression resistance testing device for target drone production according to claim 7, characterized in that: The sealing block (607) has a top block A (608) installed on its outer contour, with the arc-shaped end of the top block A (608) facing upwards, and a top block B (609) is installed on the back of the baffle (601), with the arc-shaped end of the top block B (609) facing downwards.

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