Deployment synchronism testing device

Abstract

The utility model discloses an unfolding synchronism testing device. The unfolding synchronism testing device comprises a placing platform, a mounting platform, a clamping mechanism, a blocking mechanism, a releasing mechanism and a reflective laser sensor, the releasing mechanism comprises a mounting seat, a sliding rod, a sliding seat, an extension spring, a first mounting cylinder, a positioning lock head, a first pull rod and a first compression spring; the sliding rod is fixedly connected to the mounting platform, the sliding seat is fixedly connected to the bottom of the mounting seat and slidably connected with the sliding rod, the two ends of the extension spring are connected with the mounting seat and the mounting platform respectively, a triangular positioning groove is formed in the bottom of the mounting seat, the first mounting cylinder is fixedly connected with the mounting platform, and one side of the bottom of the positioning lock is slidably connected into the first mounting cylinder. The top of the positioning lock is matched with the positioning groove, two ends of the first compression spring are respectively connected with the positioning lock and the first mounting cylinder, and the first pull rod is fixedly connected to the bottom of the positioning lock; the blocking mechanism is connected with the mounting base. Through the design, testing can be conveniently carried out, and the testing efficiency can be improved.

Description

Technical Field

[0001] This utility model belongs to the field of aircraft manufacturing technology, specifically a deployment synchronization test device. Background Technology

[0002] In aerospace, drones, and missiles, folding wing structures are widely used due to their space-saving advantages in storage and transportation. Their deployment synchronization directly affects the aerodynamic performance, flight stability, and mission accuracy of the equipment. Therefore, accurate testing of folding wing deployment synchronization is a crucial step in ensuring product performance, and there is an urgent need for a device that can efficiently and reliably perform synchronization testing to meet the industry's requirements for quality control and performance evaluation of folding wing components.

[0003] Existing technologies for testing the synchronization of folding wing deployment suffer from several technical bottlenecks: Firstly, traditional release mechanisms struggle to precisely control the starting point of folding wing deployment, locking structures are prone to loosening leading to inconsistent test benchmarks, and release response is slow. Furthermore, asynchronous disengagement of the blocking mechanism prevents the folding wing from deploying under uniform conditions. Secondly, monitoring methods lack precision, making it difficult to capture subtle positional changes during folding wing deployment in real time, resulting in large data acquisition errors. Additionally, the complex structure and cumbersome operation of these devices lead to low testing efficiency, failing to meet the adaptability testing requirements of various folding wing specifications. Therefore, structural optimization is urgently needed to improve the accuracy and reliability of the tests.

[0004] A patent application with application number CN202310002673.X discloses a multi-bladed folding wing deployment consistency testing device. It includes a folding wing fixing assembly and a blade assembly; the blade assembly includes a folding wing fixing plate, a positioning photoelectric sensor, and a folding wing fixing base plate; the folding wing mechanism to be tested is clamped and fixed between the folding wing fixing base plate and the folding wing fixing plate; the positioning photoelectric sensor monitors whether the blades of the folding wing mechanism are fully deployed; the blade assembly includes a assembly base, a blade assembly base plate, an electric push rod, and a locking assembly. In use, the blade assembly limits or releases the blades of the folding wing, resulting in a complex structure and cumbersome operation, which affects the testing efficiency. Utility Model Content

[0005] The purpose of this invention is to provide a device for testing the synchronization of deployment, so as to solve the following technical problems mentioned in the background art:

[0006] Existing testing devices are complex in structure and cumbersome in operation, resulting in low testing efficiency.

[0007] To solve the above-mentioned technical problems, the technical solution adopted by this utility model is as follows:

[0008] A deployment synchronization testing device includes a placement platform, a mounting platform, a clamping mechanism, a blocking mechanism, a release mechanism, and a reflective laser sensor. The clamping mechanism and the reflective laser sensor are mounted on the placement platform. The clamping mechanism is used to clamp a folding wing, and the reflective laser sensor is used to monitor the position of the folding wing. The release mechanism includes a mounting base, a slide rod, a slide block, a tension spring, a first mounting cylinder, a positioning lock head, a first pull rod, and a first compression spring. The slide rod is fixed to the mounting platform, the slide block is fixed to the bottom of the mounting base and slidably connected to the slide rod, the two ends of the tension spring are respectively connected to the mounting base and the mounting platform, the bottom of the mounting base is provided with a triangular positioning groove, the first mounting cylinder is fixed to the mounting platform, one side of the bottom of the positioning lock head is slidably connected to the first mounting cylinder, the top of the positioning lock head cooperates with the positioning groove, the two ends of the first compression spring are respectively connected to the positioning lock head and the first mounting cylinder, and the first pull rod is fixed to the bottom of the positioning lock head. The blocking mechanism is connected to the mounting base and is used to block the deployment of the folding wing.

[0009] Furthermore, the blocking mechanism includes a connecting plate, an adjusting screw, a limiting rod, a connector, and a pressure plate; the connecting plate is connected to the mounting base, the adjusting screw is rotatably connected to the connecting plate, the limiting rod is located on both sides of the adjusting screw and fixedly connected to the connecting plate, the connector is threadedly connected to the adjusting screw and slidably connected to the limiting rod, and the pressure plate is connected to the connector.

[0010] Furthermore, the pressure plate and the connector are detachably connected.

[0011] Furthermore, two clamping mechanisms are symmetrically arranged on the placement platform.

[0012] Furthermore, an adjustment box is fixedly connected to the mounting base, and a worm gear mechanism is installed inside the adjustment box; a connecting column is fixedly connected to one side of the connecting plate, the connecting column is rotatably connected to the mounting base, and one side of the connecting column extends into the adjustment box and is connected to the worm gear mechanism.

[0013] Furthermore, the cross-section of the positioning groove is a right-angled triangle structure, with the inclined side of the right-angled triangle structure located on the side closer to the tension spring, and the top side of the positioning lock head is adapted to the shape of the positioning groove.

[0014] Furthermore, an anti-reverse mechanism is provided on the installation platform. The anti-reverse mechanism includes a second mounting cylinder, an anti-reverse lock head, a second compression spring, and a second pull rod. The second mounting cylinder is fixedly connected to the installation platform. One side of the bottom of the anti-reverse lock head is movably connected inside the second mounting cylinder. The two ends of the second compression spring are respectively connected to the anti-reverse lock head and the second mounting cylinder. The pull rod is fixedly connected to the bottom of the anti-reverse lock head. The top cross-section of the anti-reverse lock head is a right-angled triangle structure, and the inclined side of the right-angled triangle structure is located on the side closer to the mounting base.

[0015] Compared with the prior art, the present invention has the following beneficial effects:

[0016] The release mechanism of this utility model utilizes the cooperation of the positioning lock head and the positioning groove to achieve precise locking and rapid release of the mounting base. The tension spring drives the blocking mechanism to withdraw synchronously, ensuring that the starting point of the folding wing unfolds uniformly. The reflective laser sensor monitors the position of the folding wing in real time with high precision, providing data support for synchronization analysis. The overall structure is compact, easy to operate, and can efficiently complete the test of the folding wing unfolding synchronization. Attached Figure Description

[0017] Figure 1 This is one of the overall structural schematic diagrams of this utility model;

[0018] Figure 2 This is the second schematic diagram of the overall structure of this utility model;

[0019] Figure 3 This is a cross-sectional view of the present invention.

[0020] The markings in the diagram are: 1-Placement platform, 2-Mounting platform, 3-Release mechanism, 4-Blocking mechanism, 5-Reflective laser sensor, 6-Clamping mechanism, 7-Folding wing, 8-Pressure plate, 9-Connector, 10-Limit rod, 11-Adjusting screw, 12-Connecting plate, 13-Tension spring, 14-Slide rod, 15-Mounting base, 16-Adjusting box, 17-Worm gear mechanism, 18-Connecting column, 19-Positioning groove, 20-Second mounting cylinder, 21-Anti-reverse lock head, 22-Second pull rod, 23-Second compression spring, 24-First mounting cylinder, 25-First pull rod, 26-First compression spring, 27-Positioning lock head, 28-Slide base. Detailed Implementation

[0021] The technical solutions of the present utility model will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of the present utility model, and not all embodiments. Based on the embodiments of the present utility model, all other embodiments obtained by those of ordinary skill in the art without creative effort are within the protection scope of the present utility model.

[0022] Example:

[0023] A deployment synchronization testing device includes a placement platform 1, a mounting platform 2, a clamping mechanism 6, a blocking mechanism 4, a release mechanism 3, and a reflective laser sensor 5. The clamping mechanism 6 and the reflective laser sensor 5 are mounted on the placement platform 1. The clamping mechanism 6 is used to clamp a folding wing 7, and the reflective laser sensor 5 is used to monitor the position of the folding wing 7. The release mechanism 3 includes a mounting base 15, a slide rod 14, a slide block 28, a tension spring 13, a first mounting cylinder 24, a positioning lock head 27, a first pull rod 25, and a first compression spring 26. The slide rod 14 is fixedly connected to the mounting platform 2, and the slide block 28 is fixedly connected to the mounting platform 2. The bottom of the mounting base 15 is slidably connected to the slide rod 14. The two ends of the tension spring 13 are respectively connected to the mounting base 15 and the mounting platform 2. The bottom of the mounting base 15 is provided with a triangular positioning groove 19. The first mounting cylinder 24 is fixedly connected to the mounting platform 2. The bottom side of the positioning lock head 27 is slidably connected to the first mounting cylinder 24. The top of the positioning lock head 27 cooperates with the positioning groove 19. The two ends of the first compression spring 26 are respectively connected to the positioning lock head 27 and the first mounting cylinder 24. The first pull rod 25 is fixedly connected to the bottom of the positioning lock head 27. The blocking mechanism 4 is connected to the mounting base 15 and is used to prevent the folding wing 7 from unfolding.

[0024] Specifically, firstly, the folding wing 7 is clamped and fixed on the placement platform 1 by the clamping mechanism 6. At this time, the mounting base 15 in the release mechanism 3 can move within a certain range through the sliding connection between the slide block 28 and the slide rod 14, and the tension spring 13 is in a certain tension state, applying tension to the mounting base 15. Under the action of the first compression spring 26, the top of the positioning lock head 27 cooperates with the triangular positioning groove 19 at the bottom of the mounting base 15, so that the mounting base 15 is restricted in position by the positioning lock head 27, maintaining a relatively stable state, and the blocking mechanism 4 is in the position to prevent the folding wing 7 from unfolding. The reflective laser sensor 5 is in a standby state to monitor the position of the folding wing 7, ready to detect the positional changes of the folding wing 7 during the subsequent unfolding process, such as... Figure 3 As shown.

[0025] When it is necessary to test the synchronization of the unfolding of the folding wing 7, by pulling the first lever 25, the elastic force of the first compression spring 26 is overcome, causing the positioning lock head 27 to move downwards, disengaging from the positioning groove 19 at the bottom of the mounting base 15, and releasing the positioning restriction on the mounting base 15. At this time, under the pulling force of the tension spring 13, the mounting base 15 will slide along the slide rod 14, driving the connected blocking mechanism 4 to move together, so that the blocking mechanism 4 no longer obstructs the unfolding of the folding wing 7, and the folding wing 7 can begin to unfold. Figure 2 As shown.

[0026] During the deployment of the folding wing 7, the reflective laser sensor 5 monitors the positional changes of the folding wing 7 in real time. Because the reflective laser sensor 5 can accurately sense the position of an object, it can accurately capture the position of the folding wing 7 at each stage of deployment. Furthermore, based on the data fed back by the sensors corresponding to different folding wings 7, the synchronicity of the deployment of each folding wing 7 can be analyzed, such as... Figure 1 As shown.

[0027] It should be noted that the reflective laser sensor 5 is a sensor that utilizes laser technology for detection. It emits a laser beam onto a target object and then receives the laser signal reflected back from the object. Based on changes in the light signal, such as changes in light intensity and time, it determines the target object's position, distance, and other relevant information. In the aforementioned deployment synchronization testing device, it can accurately monitor the positional changes of the folding wing 7 during deployment, providing crucial data for analyzing the deployment synchronization of the folding wing 7. At least two reflective laser sensors 5 are provided; one corresponds to the position of the folding wing 7 after folding, and the other corresponds to the position of the folding wing 7 after deployment. The signals fed back by these two reflective laser sensors 5 enable accurate detection of the deployment time of the folding wing 7, thus facilitating synchronous deployment analysis. The reflective laser sensor 5 is used in conjunction with a central processing unit. In this embodiment, both the reflective laser sensor 5 and the central processing unit employ existing technology; their specific structures and working principles are not detailed here. For example, the reflective laser sensor 5 can be a GL6-P4111 model reflective laser sensor.

[0028] In the deployment synchronization testing device, the clamping mechanism 6 stably clamps the folding wing 7, ensuring that it is in a fixed initial position during the test preparation stage, preventing premature or accidental deployment, and providing a prerequisite for accurate subsequent testing of deployment synchronization. The positioning lock 27 in the release mechanism 3 cooperates with the positioning groove 19 of the mounting base 15 to accurately position the mounting base 15 in the initial state, ensuring the accurate relative positions of all components of the device, allowing the test process to start in an orderly manner according to the set state. The release mechanism 3, through the cooperation of the pull rod, positioning lock 27, compression spring, and tension spring 13, controls the position of the blocking mechanism 4, thereby controlling the start time of the folding wing 7's deployment. The operator can operate the first pull rod 25 as needed to determine when to release the obstruction of the folding wing 7, allowing it to begin its deployment, ensuring the test process can be conducted in an orderly manner under human control.

[0029] In a preferred embodiment, the blocking mechanism 4 includes a connecting plate 12, an adjusting screw 11, a limiting rod 10, a connecting head 9, and a pressure plate 8; the connecting plate 12 is connected to the mounting base 15, the adjusting screw 11 is rotatably connected to the connecting plate 12, the limiting rod 10 is disposed on both sides of the adjusting screw 11 and fixedly connected to the connecting plate 12, the connecting head 9 is threadedly connected to the adjusting screw 11 and slidably connected to the limiting rod 10, and the pressure plate 8 is connected to the connecting head 9. Figure 2 As shown.

[0030] Specifically, the blocking mechanism 4 is fixed to the mounting base 15 via the connecting plate 12. In the initial state, when the mounting base 15 is locked by the release mechanism 3, the pressure plate 8 abuts against the folding wing 7, restricting its unfolding. When the blocking position needs to be adjusted, the adjusting screw 11, which is rotatably connected to the connecting plate 12, is rotated. Since the connecting head 9 is threadedly engaged with the screw and constrained by the limit rods 10 on both sides, rotating the screw will drive the connecting head 9 to move linearly along the limit rods 10, thereby causing the pressure plate 8 to adjust its position up and down to accommodate folding wings 7 of different sizes or unfolding angles. When the release mechanism 3 unlocks the mounting base 15, the mounting base 15 slides along the slide rod 14 under the tension of the tension spring 13, and the entire blocking mechanism 4 is disengaged via the connecting plate 12, releasing the obstruction of the folding wing 7. By adjusting the engagement between the adjusting screw 11 and the limit rods 10, the position of the pressure plate 8 can be finely adjusted to meet the blocking requirements of folding wings 7 of different specifications.

[0031] Furthermore, the pressure plate 8 and the connector 9 are detachably connected. This detachable connection allows for the replacement of pressure plates 8 with different specifications according to the shape, size, or testing requirements of the folding wing 7, improving the device's adaptability to various folding wings 7 and enhancing testing flexibility and versatility.

[0032] In a preferred embodiment, two clamping mechanisms 6 are symmetrically arranged on the placement platform 1. This design allows for the simultaneous detection of the deployment times of the two folding wings 7, facilitating a comparison of their deployment times and enabling more efficient and accurate analysis of the synchronicity of the folding wing 7 deployments, thus improving detection efficiency. Figure 1 As shown.

[0033] In a preferred embodiment, an adjustment box 16 is fixedly connected to the mounting base 15, and a worm gear mechanism 17 is provided inside the adjustment box 16; a connecting column 18 is fixedly connected to one side of the connecting plate 12, the connecting column 18 is rotatably connected to the mounting base 15, and one side of the connecting column 18 extends into the adjustment box 16 and connects to the worm gear mechanism 17. The worm gear mechanism 17 drives the connecting column 18 to rotate, which in turn drives the connecting plate 12 to rotate, thereby adjusting the angle of the connecting plate 12. Through this design, the worm gear mechanism 17 can precisely control the angle of the connecting plate 12, thereby flexibly adjusting the angle of the pressure plate 8, better adapting to different placement postures and shapes of the folding wings 7, ensuring stable and precise blocking of the folding wings 7, and further improving the adaptability and accuracy of the device for synchronous testing of the folding wing 7 deployment under various working conditions, such as... Figure 3 As shown.

[0034] In a preferred embodiment, the positioning groove 19 has a right-angled triangular cross-section, with the inclined side of the right-angled triangle located near the tension spring 13. The top side of the positioning lock head 27 is adapted to the shape of the positioning groove 19. The right-angled triangular structure of the positioning groove 19, with its inclined side near the tension spring 13, combined with the matching positioning lock head 27, allows the positioning lock head 27 to disengage from the positioning groove 19 more smoothly when pulled by the pull rod. The structure of the mounting base 15 and the positioning lock head 27 also facilitates their connection when blocking the folding wing 7.

[0035] In a preferred embodiment, the mounting platform 2 is provided with an anti-reverse mechanism, which includes a second mounting cylinder 20, an anti-reverse lock head 21, a second compression spring 23, and a second pull rod 22. The second mounting cylinder 20 is fixedly connected to the mounting platform 2, the bottom side of the anti-reverse lock head 21 is movably connected to the second mounting cylinder 20, the two ends of the second compression spring 23 are respectively connected to the anti-reverse lock head 21 and the second mounting cylinder 20, and the pull rod is fixedly connected to the bottom of the anti-reverse lock head 21. The top cross-section of the anti-reverse lock head 21 is a right-angled triangle structure, and the inclined side of the right-angled triangle structure is located on the side closer to the mounting base 15. Figure 3 As shown. The anti-reverse mechanism pushes the anti-reverse lock head 21 out through the second compression spring 23. The inclined side of the right-angled triangle at the top of the anti-reverse lock head 21 is matched with the moving direction of the mounting base 15. When the mounting base 15 is pulled by the tension spring 13, the inclined side is compressed, causing the lock head to retract, and the mounting base 15 can move smoothly. If the mounting base 15 attempts to rebound, the right-angled side of the anti-reverse lock head 21 will abut against the mounting base 15, using the one-way blocking characteristic of the right-angled structure to prevent it from retracting, avoiding the rebound impact from damaging the folding wing 7, and ensuring the stability and safety of the folding wing 7 in the unfolded state during the test.

[0036] In the description of this utility model, it should be understood that the terms "coaxial", "bottom", "one end", "top", "middle", "other end", "upper", "side", "top", "inner", "front", "center", "both ends", etc., indicate the orientation or positional relationship based on the orientation or positional relationship shown in the drawings. They are only for the convenience of describing this utility model and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation. Therefore, they should not be construed as limitations on this utility model.

[0037] In this utility model, unless otherwise explicitly specified and limited, the terms "installation," "setting," "connection," "fixing," "screw connection," etc., should be interpreted broadly. For example, they can refer to a fixed connection, a detachable connection, or an integral part; they can refer to a mechanical connection or an electrical connection; they can refer to a direct connection or an indirect connection through an intermediate medium; they can refer to the internal communication of two components or the interaction between two components. Unless otherwise explicitly limited, those skilled in the art can understand the specific meaning of the above terms in this utility model according to the specific circumstances.

[0038] Although embodiments of the present invention have been shown and described, it will be understood by those skilled in the art that various changes, modifications, substitutions and alterations can be made to these embodiments without departing from the principles and spirit of the present invention, the scope of which is defined by the appended claims and their equivalents.

Claims

1. A device for testing the synchronization of deployment, characterized in that: It includes a placement platform (1), an installation platform (2), a clamping mechanism (6), a blocking mechanism (4), a release mechanism (3), and a reflective laser sensor (5); the clamping mechanism (6) and the reflective laser sensor (5) are set on the placement platform (1), the clamping mechanism (6) is used to clamp the folding wing (7), and the reflective laser sensor (5) is used to monitor the position of the folding wing (7); The release mechanism (3) includes a mounting base (15), a slide bar (14), a slide block (28), a tension spring (13), a first mounting cylinder (24), a positioning lock head (27), a first pull rod (25), and a first compression spring (26); The slide bar (14) is fixed to the mounting platform (2), the slide seat (28) is fixed to the bottom of the mounting base (15) and slidably connected to the slide bar (14), the two ends of the tension spring (13) are respectively connected to the mounting base (15) and the mounting platform (2), the bottom of the mounting base (15) is provided with a triangular positioning groove (19), the first mounting cylinder (24) is fixed to the mounting platform (2), the bottom side of the positioning lock head (27) is slidably connected to the first mounting cylinder (24), the top of the positioning lock head (27) cooperates with the positioning groove (19), the two ends of the first compression spring (26) are respectively connected to the positioning lock head (27) and the first mounting cylinder (24), the first pull rod (25) is fixed to the bottom of the positioning lock head (27); the blocking mechanism (4) is connected to the mounting base (15), and the blocking mechanism (4) is used to block the unfolding of the folding wing (7).

2. The deployment synchronization testing device according to claim 1, characterized in that: The blocking mechanism (4) includes a connecting plate (12), an adjusting screw (11), a limiting rod (10), a connector (9), and a pressure plate (8); the connecting plate (12) is connected to the mounting base (15), the adjusting screw (11) is rotatably connected to the connecting plate (12), the limiting rod (10) is set on both sides of the adjusting screw (11) and fixedly connected to the connecting plate (12), the connector (9) is threadedly connected to the adjusting screw (11) and slidably connected to the limiting rod (10), and the pressure plate (8) is connected to the connector (9).

3. The deployment synchronization testing device according to claim 2, characterized in that: The pressure plate (8) and the connector (9) are detachably connected.

4. The deployment synchronization testing device according to claim 1, characterized in that: Two clamping mechanisms (6) are symmetrically arranged on the placement platform (1).

5. The deployment synchronization testing device according to claim 1, characterized in that: An adjustment box (16) is fixedly connected to the mounting base (15), and a worm gear mechanism (17) is provided inside the adjustment box (16); a connecting column (18) is fixedly connected to one side of the connecting plate (12), and the connecting column (18) is rotatably connected to the mounting base (15). One side of the connecting column (18) extends into the adjustment box (16) and is connected to the worm gear mechanism (17).

6. The deployment synchronization testing device according to claim 1, characterized in that: The positioning groove (19) has a right-angled triangle structure in cross section. The inclined side of the right-angled triangle structure is located on the side closer to the tension spring (13). The top side of the positioning lock head (27) is adapted to the shape of the positioning groove (19).

7. The deployment synchronization testing device according to claim 1, characterized in that: The mounting platform (2) is equipped with an anti-reverse mechanism, which includes a second mounting cylinder (20), an anti-reverse lock head (21), a second compression spring (23), and a second pull rod (22). The second mounting cylinder (20) is fixedly connected to the mounting platform (2), and the bottom side of the anti-reverse lock head (21) is movably connected to the second mounting cylinder (20). The two ends of the second compression spring (23) are respectively connected to the anti-reverse lock head (21) and the second mounting cylinder (20), and the pull rod is fixedly connected to the bottom of the anti-reverse lock head (21). The top section of the anti-reverse lock head (21) is a right-angled triangle structure, and the inclined side of the right-angled triangle structure is located on the side close to the mounting base (15).

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