Movable rack for static test of unmanned aerial vehicle

Abstract

The invention discloses a movable stand for a static test of an unmanned aerial vehicle, relates to the technical field of static test stands, and aims to solve the technical problem of low follow-up maintenance efficiency caused by a plurality of hydraulic actuators at present. The movable stand comprises a load mechanism, an elastic plate and an assembly plate, and the elastic plate comprises a plurality of folding parts; a plurality of positioning mechanisms are arranged on the bottom surface of the assembly plate, each positioning mechanism comprises a storage cover, two embedding blocks and two guide plates, a cover plate is connected to the bottom surface of each storage cover through screws, a driving assembly is arranged on the bottom surface of each cover plate, and each driving assembly comprises an extrusion plate and a driving plate. The device has the advantages that wing gradient load application is achieved through the multi-folding-part elastic plate, the use amount of hydraulic actuators is reduced, cost is reduced, maintenance is simplified, accurate load transmission is guaranteed through the design of the guide plate and the embedded block, meanwhile, wing breakage and separation are prevented, test stability and safety are improved, real flight lift force distribution can be attached, and the device is suitable for large-scale popularization and application. And the accuracy of test data is ensured.

Description

Technical Field

[0001] This invention relates to the field of static test bench technology, and more specifically, to a movable test bench for static testing of unmanned aerial vehicles (UAVs). Background Technology

[0002] Unmanned aerial vehicles (UAVs) are aircraft managed by control stations. UAVs are mainly divided into straight-wing, swept-wing, and delta-wing types. Straight-wing fixed-wing UAVs have no obvious sweep angle, generally less than 20°, and their planar shape is rectangular, trapezoidal, or semi-elliptical. Static testing of UAVs is a key test to verify the structural load-bearing capacity. By applying static loads to simulate extreme working conditions, it is determined whether the structure meets the design requirements. Its main purpose is to verify the strength and stiffness of key structures such as the fuselage, wings, and tail of the UAV, detect whether the structure undergoes permanent deformation or failure under extreme loads, ensure flight safety, and provide data support for structural optimization, such as weight reduction design or strengthening of weak parts. The test bench is the frame used to support and position the UAV during static testing.

[0003] Currently, when conducting static tests on UAV wings, different pressure magnitudes are applied to different positions of the wing using multi-point hydraulic actuators, thereby achieving load testing on the entire wing. This traditional multi-point pressure application method has a significant drawback of high cost, requiring multiple hydraulic actuators to work together during static testing, resulting in high testing costs and cumbersome subsequent maintenance procedures, affecting the efficiency of equipment maintenance. In view of this, we propose a movable test bench for UAV static testing. Summary of the Invention

[0004] The purpose of this invention is to overcome the shortcomings of the prior art, adapt to practical needs, and provide a movable test bench for static testing of unmanned aerial vehicles (UAVs) to solve the technical problem of low subsequent maintenance efficiency caused by multiple hydraulic actuators.

[0005] To solve the above technical problems, the present invention provides the following technical solution: a movable test stand for static testing of unmanned aerial vehicles (UAVs), including a frame, a first support plate fixedly connected to one side of the top surface of the frame, a placement platform fixedly connected to the top surface of the first support plate, and the UAV body placed on the top surface of the placement platform; Both sides of the top surface of the frame are provided with pressure devices. The pressure devices include assembly plates. The top surface of the assembly plates is provided with several load-bearing mechanisms. The load-bearing mechanisms include elastic plates and assembly plates. The elastic plates include several folded parts. The bottom surface of the assembly plate is provided with several positioning mechanisms. Each positioning mechanism includes a storage cover, two fitting blocks, and two guide plates. The two fitting blocks are movably installed inside the storage cover, and the two guide plates are respectively fixedly connected to the outer walls of both sides of the assembly plate. The bottom surface of the storage cover is screwed to a cover plate, and the bottom surface of the cover plate is provided with a driving assembly. The driving assembly includes a pressing plate and a driving plate. The driving plate is movably installed inside the cover plate, and the driving plate is provided with a pushing part facing the inside of the storage cover. The top surface of the assembly plate is provided with a storage component, which includes a positioning sleeve.

[0006] Preferably, the pressure application device further includes a second support plate, which is fixedly connected to the top surface of the frame. A hydraulic actuator is fixedly connected to one side of the top surface of the second support plate, and the output end of the hydraulic actuator is screwed to the bottom surface of the assembly plate. Two second support plates are distributed on both sides of the first support plate. Both sides of the placement platform are screwed with straps for fixing the drone body, and the straps are located on the outside of the drone body.

[0007] Preferably, the assembly plate is located on the top surface of the elastic plate, and both ends of the elastic plate are fixedly connected to the top surface and bottom surface of the assembly plate, respectively, and the bending directions of adjacent folded portions are opposite.

[0008] Preferably, the storage cover is fixedly connected to the bottom surface of the assembly plate, the outer wall of the assembly plate is provided with a plurality of guide grooves adapted to the size of the guide plate, the guide plate is located inside the guide grooves, and a limiting block is fixedly connected to the outer wall of the guide plate, the limiting block being located on the bottom surface of the assembly plate; The guide plate has several fitting grooves facing the outer wall of the assembly plate. The fitting grooves are distributed vertically at equal intervals. The size of the fitting groove is adapted to the size of the fitting block, and the end of the fitting block is engaged inside the fitting groove. The bottom surface of the fitting block adopts an inclined structure design on one side.

[0009] Preferably, a connecting rod is fixedly connected to the end of the fitting block, and a support spring is provided on the connecting rod away from the end of the fitting block. A spring mounting groove adapted to the size of the support spring is opened at the end of the connecting rod, and the support spring is located inside the spring mounting groove. The connecting rod includes a pressure-bearing part, which is located away from the interlocking block, and the pressure-bearing part has a frustum structure design.

[0010] Preferably, the drive assembly further includes two sleeves and a push plate. Both sleeves are fixedly connected to the bottom surface of the cover plate. A rotating shaft is rotatably installed inside the sleeve. A pressure plate is fixedly connected to the outer wall of the rotating shaft, and the end of the pressure plate protrudes outside the assembly plate. The top surface of the push plate is fixedly connected to the outer wall of the positioning sleeve. The bottom surface of the push plate adopts an arc-shaped structure design. The push plate and the pressure plate are relatively perpendicular to each other. The extrusion plate is fixedly connected to the outer wall of the rotating shaft, and the extrusion plate is in contact with the outer wall of the drive plate; The pushing part adopts a V-shaped structure design, and the angle of the inclined surface of the pushing part is adapted to the cone angle of the pressure receiving part. The pressure receiving part is located inside the pushing part. Rubber blocks are fixedly connected to both outer walls of the drive plate. The rubber blocks have deformation cavities for compression inside. The inner walls of the cover plate have slots that fit the size of the rubber blocks on both sides.

[0011] Preferably, a drive shaft is provided on both sides of the bottom surface of the positioning sleeve, the drive shaft is rotatably connected to the assembly plate, a protective pad is fixedly connected to the inner wall of the positioning sleeve, and a storage groove adapted to the size of the drone's wings is opened inside the protective pad, and the wings of the drone's body are located inside the storage groove.

[0012] Compared with the prior art, the beneficial effects of the present invention are: 1. This invention, through the design of folding sections with varying numbers of bends, allows a single hydraulic actuator to work with multiple load mechanisms to achieve gradient load application from the wing root to the wingtip. This reduces the number of hydraulic actuators required, simplifies subsequent maintenance procedures, and the multi-folding structure of the elastic plate, with varying numbers of bends at different positions, increasing from the wing root to the wingtip, ensures that the force required to compress the elastic plate varies at different positions. This allows for precise application of loads to different parts of the wing, resulting in an arc-shaped force distribution on the wing that closely matches the actual lift distribution during flight. This ensures the authenticity and reference value of the test data and solves the problem of low subsequent maintenance efficiency caused by multiple hydraulic actuators.

[0013] 2. This invention also restricts the movement trajectory of the assembly plate and the contraction direction of the elastic plate by designing a guide plate and a guide groove to cooperate, thereby preventing the elastic plate from deviating, ensuring accurate load transfer, and improving test stability. The interlocking block is engaged with the interlocking groove of the guide plate under the action of the support spring. The assembly plate can be positioned in multiple positions by interlocking grooves of different heights. If the wing breaks during the test, it can prevent the elastic plate from releasing its elastic force and causing the broken wing to detach, thus ensuring the safety of personnel near the equipment and further solving the safety problem during the test. Attached Figure Description

[0014] Figure 1 This is a schematic diagram of the main frame structure of the present invention; Figure 2 This is a schematic diagram showing the disassembled structure of the first support plate of the present invention; Figure 3 This is a schematic diagram showing the disassembled structure of the pressure application device of the present invention; Figure 4 This is an enlarged schematic diagram of the assembly plate structure of the present invention; Figure 5 This is a schematic diagram of the assembly plate structure being flipped and disassembled according to the present invention; Figure 6This is a schematic diagram showing the disassembled structure of the positioning mechanism of the present invention; Figure 7 This is a schematic diagram showing the structural breakdown of the drive component of the present invention; Figure 8 This is an enlarged schematic diagram of the rotating shaft structure of the present invention; Figure 9 This is an enlarged schematic diagram of the drive board structure of the present invention; Figure 10 This is a schematic diagram showing the structural breakdown of the load-bearing mechanism of the present invention; Figure 11 This is an enlarged schematic diagram of the elastic plate structure of the present invention; Figure 12 This is a schematic diagram of the guide plate structure flipping according to the present invention.

[0015] The following are the labeling instructions in the diagram: 1. Frame; 11. First support plate; 12. Placement platform; 13. UAV body; 14. Strap; 2. Pressure device; 21. Second support plate; 22. Hydraulic actuator; 23. Assembly plate; 24. Guide groove; 3. Loading mechanism; 31. Elastic plate; 32. Folding part; 33. Assembly plate; 4. Positioning mechanism; 41. Storage cover; 42. Fitting block; 43. Connecting rod; 44. Pressure-bearing part; 45. Support spring; 46. Guide plate; 47. Limiting block; 48. Fitting groove; 49. Cover plate; 5. Drive assembly; 51. Sleeve; 52. Rotating shaft; 53. Pressure plate; 54. Extrusion plate; 55. Drive plate; 56. Rubber clamp; 57. Pushing part; 58. Slot; 59. Pushing plate; 6. Storage assembly; 61. Positioning sleeve; 62. Protective pad; 63. Drive shaft. Detailed Implementation

[0016] like Figures 1 to 12As shown, the present invention relates to a movable test bench for static testing of unmanned aerial vehicles (UAVs), comprising a frame 1, a first support plate 11 fixedly connected to one side of the top surface of the frame 1, a placement platform 12 fixedly connected to the top surface of the first support plate 11, a UAV body 13 placed on the top surface of the placement platform 12, pressure applying devices 2 provided on both sides of the top surface of the frame 1, each pressure applying device 2 including an assembly plate 23, a plurality of load-bearing mechanisms 3 provided on the top surface of the assembly plate 23, each load-bearing mechanism 3 including an elastic plate 31 and an assembly plate 33, the elastic plate 31 including a plurality of folding portions 32, and a plurality of positioning mechanisms 4 provided on the bottom surface of the assembly plate 23. The assembly plate 33 includes a storage cover 41, two fitting blocks 42, and two guide plates 46. The two fitting blocks 42 are movably installed inside the storage cover 41. The two guide plates 46 are fixedly connected to the outer walls of both sides of the assembly plate 33. A cover plate 49 is screwed to the bottom of the storage cover 41. A drive assembly 5 is provided on the bottom of the cover plate 49. The drive assembly 5 includes a pressing plate 54 and a drive plate 55. The drive plate 55 is movably installed inside the cover plate 49, and a pushing part 57 is provided on the drive plate 55 facing inwards towards the inside of the storage cover 41. A storage assembly 6 is provided on the top surface of the assembly plate 33, and the storage assembly 6 includes a positioning sleeve 61. The wing gradient load is applied through the elastic plate 31 of the multi-folded part 32, reducing the amount of hydraulic actuator 22 required, lowering costs, and simplifying maintenance. The design of the guide plates 46 and fitting blocks 42 ensures accurate load transfer while preventing wing breakage and detachment, improving test stability and safety, and conforming to the actual lift distribution of flight, ensuring accurate test data.

[0017] Specifically, the pressure device 2 also includes a second support plate 21, which is fixedly connected to the top surface of the frame 1. A hydraulic actuator 22 is fixedly connected to one side of the top surface of the second support plate 21. The output end of the hydraulic actuator 22 is screwed to the bottom surface of the mounting plate 23. The two second support plates 21 are distributed on both sides of the first support plate 11. Both sides of the placement platform 12 are screwed with straps 14 for fixing the drone body 13, and the straps 14 are located outside the drone body 13. The second support plate 21 provides stable mounting support for the hydraulic actuator 22, ensuring that the hydraulic actuator 22 will not shift due to force during operation. As a power source, the hydraulic actuator 22 can provide stable and adjustable driving force to meet the pressure requirements and adapt to the testing requirements of the UAV body 13. The hydraulic actuator 22 is screwed to the mounting plate 23, which facilitates subsequent disassembly and replacement, reduces maintenance costs, and ensures the vertical movement of the mounting plate 23. The two second support plates 21 are symmetrically distributed, so that the driving force of the hydraulic actuators 22 on both sides of the UAV body 13 wings is balanced. The strap 14 is connected by screws to facilitate adjustment of tightness and can adapt to the size of the UAV body 13. At the same time, the strap 14 is located outside the fuselage, which can fix the UAV without obstructing the wing part and ensure the stability of the fuselage.

[0018] Furthermore, the assembly plate 33 is located on the top surface of the elastic plate 31. Both ends of the elastic plate 31 are fixedly connected to the top and bottom surfaces of the assembly plate 23, respectively. The bending directions of adjacent folding portions 32 are opposite. The assembly plate 33, being on top of the elastic plate 31, can evenly transmit the force of the load mechanism 3 to the upper storage assembly 6, ensuring the stability of the force exerted by the storage assembly 6 on the wing. The fixed connection design at both ends of the elastic plate 31 prevents the elastic plate 31 from detaching from the assembly plate 23 and assembly plate 33 under stress, improving the reliability of the structural connection. The opposite bending directions of adjacent folding portions 32 allow for a more uniform stress distribution on the elastic plate 31 during deformation, extending its service life and improving the symmetry of deformation, ensuring the assembly plate 33 maintains horizontal movement. The number of bends in the folding portions 32 of the elastic plate 31 at different positions on the outer side of the wing varies. The number of bends in the folded portions 32 of the elastic plate 31 at different positions increases from the root of the wing to the tip. The load mechanism 3 near the placement platform 12 is located at the root of the wing, the load mechanism 3 in the middle of the assembly plate 23 is located in the middle of the wing, and the load mechanism 3 away from the placement platform 12 is located at the tip of the wing. Due to the different number of bends in the folded portions 32, different forces can be applied to the elastic plate 31 at different positions to compress it. This allows different loads to be applied to different positions of the wing, so that the wing can present an arc shape during the test, which conforms to the distribution law of lift in real flight and ensures the accuracy of the test data of the wing.

[0019] Furthermore, the storage cover 41 is fixedly connected to the bottom surface of the assembly plate 23. The outer wall of the assembly plate 23 is provided with several guide grooves 24 that are adapted to the size of the guide plate 46. The guide plate 46 is located inside the guide grooves 24. The outer wall of the guide plate 46 is fixedly connected with a limiting block 47, which is located on the bottom surface of the assembly plate 23. The guide plate 46 is provided with several fitting grooves 48 facing the outer wall of the assembly plate 23. The several fitting grooves 48 are distributed vertically at equal intervals. The size of the fitting grooves 48 is adapted to the size of the fitting block 42, and the end of the fitting block 42 is engaged inside the fitting groove 48. One side of the bottom surface of the fitting block 42 adopts an inclined structure design. The storage cover 41 is fixedly connected to the assembly plate 23 to ensure that the storage cover 41 moves synchronously with the assembly plate 23, avoiding relative displacement between the two from affecting the function of the positioning mechanism 4. The guide groove 24 is size-matched with the guide plate 46, which can further improve the accuracy of the movement of the guide plate 46 and reduce shaking. The guide plate 46 is located inside the guide groove 24, which can limit the vertical movement trajectory of the assembly plate 33 and the contraction of the elastic plate 31. The limiting block 47 is located on the bottom surface of the assembly plate 23, which can limit the maximum upward movement distance of the guide plate 46, prevent the guide plate 46 from detaching from the guide groove 24, and improve structural safety. The 48 are equidistantly vertically distributed, which facilitates the locking of the interlocking blocks 42 at different heights. This meets the positioning requirements of the positioning sleeves 61 at different heights when the wing is bent during the experiment. The interlocking grooves 48 and the interlocking blocks 42 are size-matched, ensuring a stable connection after locking and preventing the assembly plate 33 from moving on its own. This prevents the elastic plate 31 from releasing and causing the broken wing to detach if the wing breaks during the test, thus protecting the safety of personnel working near the equipment. The inclined bottom structure of the interlocking blocks 42 facilitates quick disengagement from the interlocking grooves 48 during driving, reducing jamming and improving operational smoothness.

[0020] It is worth noting that a connecting rod 43 is fixedly connected to the end of the fitting block 42. A support spring 45 is provided at the end of the connecting rod 43 away from the fitting block 42. A spring mounting groove adapted to the size of the support spring 45 is opened at the end of the connecting rod 43, and the support spring 45 is located inside the spring mounting groove. The connecting rod 43 includes a pressure-bearing part 44, which is located away from the fitting block 42. The pressure-bearing part 44 has a frustum structure design. The connecting rod 43 is fixedly connected to the fitting block 42, which can accurately transmit the elastic force of the support spring 45 to the fitting block 42, ensuring that the fitting block 42 is stably engaged in the fitting groove 48. The support spring 45 can provide continuous reset elastic force for the fitting block 42. When the driving force of the drive component 5 disappears, the fitting block 42 can automatically spring back to the engaged position without manual adjustment, improving the ease of operation. The spring mounting groove can limit and constrain the support spring 45 to prevent the support spring 45 from shifting or falling off when under force, ensuring the stable function of the support spring 45. The frustum structure design of the pressure part 44 facilitates the precise fit between the push part 57 and the pressure part 44, so that the driving force can be efficiently transmitted to the connecting rod 43. At the same time, the frustum structure can distribute the force and prevent the pressure part 44 from being damaged due to excessive local stress.

[0021] It is worth mentioning that the drive assembly 5 also includes two retaining sleeves 51 and a pusher plate 59. Both retaining sleeves 51 are fixedly connected to the bottom surface of the cover plate 49. A rotating shaft 52 is rotatably mounted inside each retaining sleeve 51. A pressure plate 53 is fixedly connected to the outer wall of the rotating shaft 52, and the end of the pressure plate 53 protrudes outside the assembly plate 23. The top surface of the pusher plate 59 is fixedly connected to the outer wall of the positioning sleeve 61. The bottom surface of the pusher plate 59 adopts an arc-shaped structure design. The pusher plate 59 and the pressure plate 53 are relatively perpendicularly distributed. The pressure plate 54 is fixedly connected to the outer wall of the rotating shaft 52. The extrusion plate 54 is in contact with the outer wall of the drive plate 55. The pushing part 57 adopts a V-shaped structure design. The angle of the inclined surface of the pushing part 57 is adapted to the cone angle of the pressure part 44. The pressure part 44 is located inside the pushing part 57. Rubber blocks 56 are fixedly connected to both outer walls of the drive plate 55. The rubber blocks 56 have deformation cavities for compression inside. The inner walls of the cover plate 49 have slots 58 that are adapted to the size of the rubber blocks 56 on both sides.The sleeve 51 is fixedly connected to the cover plate 49, providing stable rotational support for the rotating shaft 52 and ensuring that the rotating shaft 52 will not deviate during rotation. The rotating shaft 52's rotatable installation design allows for synchronous rotation of the pressure plate 53 and the extrusion plate 54, converting the force of the push plate 59 into the driving force of the extrusion plate 54, resulting in high transmission efficiency. Furthermore, the length of the push plate 59 near the placement table 12 is shorter than that of the push plate 59 located in the middle of the assembly plate 23, and the length of the push plate 59 located in the middle of the assembly plate 23 is shorter than that of the push plate 59 located away from the placement table 12, ensuring that the positioning mechanism 4 can adapt to different positions. The elastic plate 31 has different compression distances, and the end of the pressure plate 53 protrudes outside the assembly plate 23, facilitating contact between the push plate 59 and the pressure plate 53 to apply force. This avoids drive failure due to concealed positioning. The push plate 59 is fixedly connected to the positioning sleeve 61 and can move synchronously with the positioning sleeve 61 to achieve linkage drive, reducing additional drive components. The arc-shaped structure design of the bottom surface of the push plate 59 reduces frictional resistance when in contact with the pressure plate 53, making the pushing process smoother, while preventing sharp edges from scratching the pressure plate 53. The push plate 59 and the pressure plate 53 are relatively perpendicularly distributed to ensure... The force of the push plate 59 acts perpendicularly to the pressure plate 53, improving the efficiency of force transmission. The extrusion plate 54 is fixedly connected to the rotating shaft 52 and can rotate synchronously with the rotating shaft 52, thereby precisely extruding the drive plate 55 and realizing the movement of the drive plate 55. The V-shaped structure design of the push part 57 can wrap around and position the pressure part 44, ensuring that the push part 57 and the pressure part 44 fit tightly and avoid slippage during driving. The angle between the push part 57 and the pressure part 44 is adapted so that the driving force can be evenly transmitted to the pressure part 44, avoiding excessive local force. Therefore, when the push part 57 extrudes the pressure part 44, it can drive the pressure plate 55. The two connecting rods 43 move towards each other. The rubber block 56 is elastic and can be engaged or disengaged from the slot 58 through deformation, which facilitates the fixation of the drive plate 55 after movement. The deformation cavity provides deformation space for the rubber block 56, ensuring that the rubber block 56 can smoothly engage or disengage from the slot 58, improving operational flexibility. Thus, when the pressure device 2 completes the test on the wing, the pushing part 57 simultaneously squeezes the pressure receiving part 44, realizing the retraction of the two interlocking blocks 42 and unlocking the guide plate 46, ensuring that the subsequent process of the hydraulic actuator 22 driving the load mechanism 3 to move down and reset is smooth.

[0022] It is worth noting that drive shafts 63 are provided on both sides of the bottom surface of the positioning sleeve 61. The drive shafts 63 are rotatably connected to the assembly plate 33. A protective pad 62 is fixedly connected to the inner wall of the positioning sleeve 61. The protective pad 62 has a storage slot adapted to the size of the drone body 13's wing, and the wing of the drone body 13 is located inside the storage slot. The drive shaft 63 is rotatably connected to the assembly plate 33, allowing the positioning sleeve 61 to rotate around the drive shaft 63. This facilitates the adjustment of the angle of the positioning sleeve 61 according to the angle of the drone body 13's wing, improving adaptability. The protective pad 62 can directly contact the drone wing, preventing the hard wall of the positioning sleeve 61 from scratching or squeezing the wing, thus improving the protective effect. The storage slot is adapted to the size of the drone wing, which can accurately position and constrain the wing, ensuring that the wing position does not shift when pressure is applied. At the same time, the storage slot can wrap around the wing part, further improving the protective effect. The protective pad 62 is made of polycarbonate material.

[0023] Working Principle: This embodiment provides a movable test stand for static testing of unmanned aerial vehicles (UAVs). In use, the UAV body 13 is placed on the top surface of the placement platform 12. By adjusting the straps 14 on both sides of the placement platform 12 and tightening the screws, the straps 14 are made to fit tightly against the exterior of the UAV body 13, achieving stable fixation and preventing displacement during the test. Then, the wings of the UAV body 13 are precisely embedded into the storage grooves of the protective pads 62 on the inner wall of the positioning sleeve 61. The protective pads 62 prevent direct contact between the wings and the hard wall of the positioning sleeve 61, avoiding scratches or pressure damage. The hydraulic actuators 22 on the second support plates 21 on both sides of the top surface of the frame 1 are activated. The output end of the hydraulic actuators 22 generates an upward driving force, causing the assembly plate 23 to rise vertically. Simultaneously, several load mechanisms 3 on the top surface, positioning mechanisms 4 on the bottom surface, and drive components 5 rise together. The elastic plate 31 in the load mechanism 3 gradually provides load to the wing as the assembly plate 23 rises. The positioning sleeve 61 first pushes the wing upward under the action of continuous lift force. At this time, the elastic plate 31 begins to compress under the wing reaction force transmitted by the assembly plate 33. Since the number of bends of the folded part 32 of the elastic plate 31 corresponding to different load mechanisms 3 positions is different, the force required to compress different elastic plates 31 is different, thereby achieving the application of different loads to different positions of the wing, so that the wing presents an arc shape that conforms to the actual lift distribution law of flight. During the compression process of the elastic plate 31, the assembly plate 33 drives the guide plates 46 on both sides to move vertically along the guide groove 24 of the assembly plate 23. The guide groove 24 restricts the movement trajectory of the guide plate 46 to prevent the elastic plate 31 from deviating. The limiting block 47 prevents the guide plate 46 from falling out of the guide groove 24. At the same time, the fitting block 42 in the positioning mechanism 4 is always engaged in the fitting groove 48 of the guide plate 46 under the elastic force of the support spring 45. Through the engagement of the fitting groove 48 and the fitting block 42 at different heights, the assembly plate 33 is positioned at different heights. If the wing breaks during the test, the engagement of the fitting block 42 and the fitting groove 48 can prevent the elastic plate 31 from releasing its elastic force and causing the broken wing to detach, ensuring the safety of the personnel. When the wing test is completed, the positioning sleeve 61 is compressed and moved downward with the elastic plate 31 and is pushed by the push plate 59 on the outer wall to press the end of the pressure plate 53 in the drive assembly 5. The arc-shaped structure reduces frictional resistance, allowing the pressure plate 53 to rotate around the shaft 52 inside the sleeve 51. The shaft 52 synchronously drives the extrusion plate 54 on the outer wall to rotate. The extrusion plate 54 extrudes the drive plate 55, causing it to move upward along the inner wall of the cover plate 49. The rubber blocks 56 on both sides of the drive plate 55 are compressed through the deformation cavity and enter the slot 58. The V-shaped pushing part 57 at the top of the drive plate 55 moves synchronously and abuts the frustum-shaped pressure part 44 of the connecting rod 43. As the pushing part 57 continues to rise, its inclined surface extrudes the pressure part 44, driving the two connecting rods 43 to move towards each other. The connecting rods 43 drive the end fitting block 42 to retract and disengage from the fitting groove 48 of the guide plate 46, releasing the positioning restriction on the guide plate 46. Thus, after the test is completed, the output end of the hydraulic actuator 22 is controlled to retract.The assembly plate 23 and related components are moved downwards, and the elastic plate 31 gradually returns to its original position under its own elasticity, causing the assembly plate 33 and positioning sleeve 61 to return to their initial positions. The hydraulic actuator 22 continues to retract until the assembly plate 23 returns to its original position. The hydraulic actuator 22 is then turned off, the screws on the strap 14 are loosened, and the UAV body 13 is removed, completing the entire static test process.

[0024] The embodiments disclosed in this invention are preferred embodiments, but are not limited thereto. Those skilled in the art can easily understand the spirit of this invention based on the above embodiments and make different extensions and variations, but as long as they do not depart from the spirit of this invention, they are all within the protection scope of this invention.

Claims

1. A movable test stand for static testing of unmanned aerial vehicles (UAVs), characterized in that, Includes a frame (1), on one side of the top surface of the frame (1) a first support plate (11) is fixedly connected, on the top surface of the first support plate (11) a placement platform (12) is fixedly connected, and on the top surface of the placement platform (12) a drone body (13) is placed. The frame (1) is provided with pressure devices (2) on both sides of the top surface. The pressure device (2) includes an assembly plate (23). The top surface of the assembly plate (23) is provided with several load mechanisms (3). The load mechanism (3) includes an elastic plate (31) and an assembly plate (33). The elastic plate (31) includes several folding parts (32). The bottom surface of the assembly plate (23) is provided with several positioning mechanisms (4). The positioning mechanism (4) includes a storage cover (41), two fitting blocks (42) and two guide plates (46). The two fitting blocks (42) are movably installed inside the storage cover (41), and the two guide plates (46) are respectively fixedly connected to the outer walls on both sides of the assembly plate (33). The bottom surface of the storage cover (41) is screwed to a cover plate (49). The bottom surface of the cover plate (49) is provided with a drive assembly (5). The drive assembly (5) includes a pressing plate (54) and a drive plate (55). The drive plate (55) is movably installed inside the cover plate (49), and the drive plate (55) is provided with a pushing part (57) facing the inside of the storage cover (41). The top surface of the assembly plate (33) is provided with a storage component (6), which includes a positioning sleeve (61).

2. The movable test stand for static testing of unmanned aerial vehicles according to claim 1, characterized in that, The pressure device (2) also includes a second support plate (21), which is fixedly connected to the top surface of the frame (1). A hydraulic actuator (22) is fixedly connected to one side of the top surface of the second support plate (21), and the output end of the hydraulic actuator (22) is screwed to the bottom surface of the assembly plate (23). Two second support plates (21) are distributed on both sides of the first support plate (11). Both sides of the placement platform (12) are screwed with straps (14) for fixing the drone body (13), and the straps (14) are located outside the drone body (13).

3. The movable test stand for static testing of unmanned aerial vehicles according to claim 1, characterized in that, The assembly plate (33) is located on the top surface of the elastic plate (31). The two ends of the elastic plate (31) are fixedly connected to the top surface of the assembly plate (23) and the bottom surface of the assembly plate (33), respectively. The bending directions of adjacent folding parts (32) are opposite.

4. The movable test stand for static testing of unmanned aerial vehicles according to claim 1, characterized in that, The storage cover (41) is fixedly connected to the bottom surface of the assembly plate (23). The outer wall of the assembly plate (23) is provided with a plurality of guide grooves (24) adapted to the size of the guide plate (46). The guide plate (46) is located inside the guide grooves (24). The outer wall of the guide plate (46) is fixedly connected with a limiting block (47). The limiting block (47) is located on the bottom surface of the assembly plate (23). The guide plate (46) has several fitting grooves (48) on the outer wall of the assembly plate (23). The fitting grooves (48) are equidistantly and vertically distributed. The size of the fitting grooves (48) is adapted to the size of the fitting block (42). The end of the fitting block (42) is engaged inside the fitting groove (48). The bottom side of the fitting block (42) adopts an inclined structure design.

5. A movable test stand for static testing of unmanned aerial vehicles according to claim 4, characterized in that, The end of the fitting block (42) is fixedly connected to a connecting rod (43). A support spring (45) is provided at the end of the connecting rod (43) away from the fitting block (42). A spring mounting groove adapted to the size of the support spring (45) is opened at the end of the connecting rod (43), and the support spring (45) is located inside the spring mounting groove. The connecting rod (43) includes a pressure-bearing part (44), which is located away from the interlocking block (42) and has a frustum structure design.

6. A movable test stand for static testing of unmanned aerial vehicles according to claim 5, characterized in that, The drive assembly (5) also includes two sleeves (51) and a push plate (59). The two sleeves (51) are fixedly connected to the bottom surface of the cover plate (49). A rotating shaft (52) is rotatably installed inside the sleeve (51). A pressure plate (53) is fixedly connected to the outer wall of the rotating shaft (52), and the end of the pressure plate (53) protrudes outside the assembly plate (23). The top surface of the push plate (59) is fixedly connected to the outer wall of the positioning sleeve (61). The bottom surface of the push plate (59) adopts an arc-shaped structure design. The push plate (59) and the pressure plate (53) are relatively perpendicularly distributed. The extrusion plate (54) is fixedly connected to the outer wall of the rotating shaft (52), and the extrusion plate (54) is in contact with the outer wall of the drive plate (55); The pushing part (57) adopts a V-shaped structure design. The angle of the inclined surface of the pushing part (57) is adapted to the cone angle of the pressure part (44). The pressure part (44) is located inside the pushing part (57). Rubber blocks (56) are fixedly connected to both outer walls of the drive plate (55). The rubber blocks (56) have a deformation cavity for compression inside. The inner walls of the cover plate (49) have slots (58) that are adapted to the size of the rubber blocks (56).

7. A movable test stand for static testing of unmanned aerial vehicles according to claim 2, characterized in that, The positioning sleeve (61) has a drive shaft (63) on both sides of its bottom surface. The drive shaft (63) is rotatably connected to the assembly plate (33). The inner wall of the positioning sleeve (61) is fixedly connected to a protective pad (62). The protective pad (62) has a storage slot inside that is adapted to the size of the wing of the drone body (13), and the wing of the drone body (13) is inside the storage slot.

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