A skeleton compression test device for unmanned aerial vehicle strength detection

Abstract

The application discloses a framework compression test device for unmanned aerial vehicle strength detection and belongs to the technical field of unmanned aerial vehicle strength detection. The device is characterized in that the sliding seat one end is extruded by the top material seat to extrude the steel ball, the steel ball can roll inside the box body, when one or several sliding seats move towards the inside of the box body, the space inside the box body is reduced, the steel ball extrudes the sliding seat at other positions and pushes it out until the top material assembly is attached to the outer wall of the framework, at this time, the length of the several sliding seats extending out of the box body changes, the top material seat is continuously pressed to deflect in the sliding seat through the hinged seat, the part of the top material seat that is raised contacts the recess on the framework, thus the multiple top material seats can be attached to the irregular surface of the special-shaped framework, the uniformity of the framework stress is ensured, the local pressure is controlled within the tolerance range of the framework material, the local pressure of the framework caused by stress concentration of the clamping point is prevented, and the precision of the compression test and the universality of the device are improved.

Description

TECHNICAL FIELD

[0001] The present application relates to the technical field of unmanned aerial vehicle strength detection, in particular to a framework compression test device for unmanned aerial vehicle strength detection. BACKGROUND

[0002] With the rapid development of unmanned aerial vehicle technology, its application scenarios have expanded from consumer aerial photography to industrial inspection, agricultural plant protection, logistics transportation, emergency rescue and other fields. The flight safety and reliability of unmanned aerial vehicles directly depend on their structural strength, and the framework, as the core support component of the unmanned aerial vehicle, bears the weight of the fuselage, power system, load equipment, etc. and needs to withstand the aerodynamic load, vibration impact and ground force during flight. Therefore, accurate strength detection of the framework of the unmanned aerial vehicle, especially compression performance test, is a key link to ensure the safe operation of the unmanned aerial vehicle.

[0003] Currently, when the framework of the unmanned aerial vehicle is subjected to compression test, the traditional method is to use an axial uniform speed loading method to pressurize the framework. However, due to the asymmetric structure or irregular surface of some special-shaped frameworks, the stress distribution of the asymmetric structure presents multi-point concentration when subjected to pressure. The standardization of the pressure surface of the traditional pressurizing mechanism cannot match the irregular surface of the special-shaped framework, resulting in stress concentration at the clamping point, causing the local pressure of the framework to be too large, and the framework structure is damaged in advance, making it difficult to carry out the test work, and further affecting the compression detection accuracy. SUMMARY

[0004] The present application aims to provide a framework compression test device for unmanned aerial vehicle strength detection to solve the problem of asymmetric structure or irregular surface of some special-shaped frameworks, which leads to multi-point stress concentration when subjected to pressure. The standardization of the pressure surface of the traditional pressurizing mechanism cannot match the irregular surface of the special-shaped framework, resulting in stress concentration at the clamping point, causing the local pressure of the framework to be too large, and the framework structure is damaged in advance, making it difficult to carry out the test work, and further affecting the compression detection accuracy.

[0005] To achieve the above-mentioned purpose, the present application provides the following technical solutions:

[0006] A kind of framework compression test device for unmanned aerial vehicle strength detection, including test support frame, one side of the test support frame is fixedly installed with compression test control box, the compression test control box is equipped with heat dissipation hole, the inside of the test support frame is fixedly connected with compression detection component away from compression test control box side, the end of the compression detection component is fixedly connected with sliding assembly, the side of the sliding assembly away from compression detection component is equipped with several groups of perforation, the number of each group of perforation is two and inside is penetrated by sliding limit component, the side of the limit component away from sliding assembly is rotatably connected with material pushing assembly, the side of the test support frame away from compression detection component is fixed with vertical plate, the side of the vertical plate close to sliding assembly is fixedly connected with mounting seat, the inside of the mounting seat is penetrated by drive assembly, the bottom of the drive assembly is penetrated mounting seat and fixed in the bottom of test support frame, the top and bottom of the outside of the drive assembly is fixedly connected with locking assembly, the position of locking assembly in mounting seat is equipped with limit hole, the locking assembly is penetrated and slides in limit hole.

[0007] As a further scheme of the application, the compression detection component includes an electric hydraulic telescopic rod, one end of the electric hydraulic telescopic rod is fixed to one side of the inner wall of the test support, the other end of the electric hydraulic telescopic rod penetrates a partition plate, the partition plate is fixed in the test support frame, one end of the electric hydraulic telescopic rod penetrating the partition plate is fixed to one side of the sliding assembly, and a pressure sensing component is fixedly installed at the connection between the end of the electric hydraulic telescopic rod and the sliding assembly.

[0008] As a further scheme of the application, the partition plate is fixed with a support rod at each corner, the two ends of the support rod are fixed between the inner wall of the test support frame and the vertical plate, and the top and bottom of the partition plate are respectively penetrated by a limit sliding rod, one end of the two limit sliding rods is fixed to the sliding assembly.

[0009] As a further scheme of the application, the sliding assembly includes a box body, one side of the box body is fixed to the two limit sliding rods and the end of the electric hydraulic telescopic rod, the top and bottom of the box body are respectively fixedly installed with a cover plate by screws, the inside of the box body is filled with a plurality of steel balls, the front and rear sides of the box body are respectively fixed with a protective cover, the support rod penetrates and slides at the edge of the protective cover, the vertical plate is respectively provided with a jack at positions corresponding to the two protective covers, and the perforation is provided on the side of the box body away from the electric hydraulic telescopic rod.

[0010] As a further scheme of the application, the limit component includes a sliding seat, the sliding seat penetrates and slides in the adjacent two perforations, a sliding hole is provided in the sliding seat, three first springs are fixed to one side of the inner wall of the sliding hole, and the other end of the first spring is fixed to one side of the inner wall of the box body close to the perforation.

[0011] As a further scheme of the present application, the top feeding assembly comprises a top feeding base, a hinge base is fixed on one side of the top feeding base close to the sliding base, the hinge base is rotationally connected with one side of the sliding base through a pin shaft, a groove is formed on the side of the sliding base away from the box body, a second spring is fixed on the upper and lower inner walls of the groove respectively, the other ends of the two second springs are fixed on the inner side of the top feeding base, the hinge base is located between the two second springs, and the outer side of the top feeding base is designed as a curved surface and is provided with a plurality of anti-skid strips.

[0012] As a further scheme of the present application, the driving assembly comprises a motor, the motor is fixed on the bottom in the test support frame, a bidirectional screw rod is fixed on the output shaft of the motor, the two ends of the bidirectional screw rod are rotationally connected in the mounting seat through shaft sleeves respectively, and the outer upper and lower parts of the bidirectional screw rod are threadedly connected with sliding plates respectively, the sliding plates are slidingly connected in the inner part of the mounting seat, and the sliding plates are fixed with the end parts of the two locking assemblies.

[0013] As a further scheme of the present application, the locking assembly comprises a horizontal plate, the horizontal plate is slidingly penetrated in a limiting hole, one end of the horizontal plate penetrated in the limiting hole is fixed with the sliding plate, a deflection groove is formed on one side of the bottom of the horizontal plate, a connecting shaft is fixed on the inner wall of the deflection groove, a rotary bearing is sleeved on the connecting shaft, two supporting rods are fixed on the outer part of the rotary bearing, the included angle between the two supporting rods is ninety degrees, a compression roller is installed on the bottom end of the supporting rod, and a anti-falling groove is formed on the outer part of the compression roller.

[0014] As a further scheme of the present application, one side of the rotary bearing is fixedly connected with a partition ring, a torsion spring is fixed on one side of the inner wall of the deflection groove and the partition ring, and the torsion spring is sleeved on the outer part of the connecting shaft.

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

[0016] 1. This invention uses a box body to move the top material assembly to the left and into contact with the frame. When the top material seat presses against the frame, the top material seat, under force, pushes the slide block to move through the perforation via the hinge seat. The perforation limits the slide block, improving its horizontal movement stability. Simultaneously, the end of the slide block located inside the box body presses against the steel ball inside the box body, allowing the steel ball to roll inside the box body. When one or more slide blocks move into the box body, the internal space of the box body shrinks, and the steel ball presses against slide blocks in other positions, causing those slide blocks to be pushed out by the steel ball. The slide blocks then drive the top material assembly to extend until the top material assembly fits against the outer wall of the frame. With the electro-hydraulic extension... The retracting rod continuously applies pressure, causing the top material components at the ends of multiple limiting components to fully contact one side of the skeleton. At this time, the length of several slides extending out of the box will change. As the top material seats are continuously compressed, the protruding parts on the skeleton will squeeze the top or bottom of one side of the top material seats, causing the top material seats to deflect in the slides through the hinge seats, so that the raised parts of the top material seats contact the recesses on the skeleton. This allows multiple top material seats to fit against the irregular surface of the irregular skeleton, ensuring the uniformity of the skeleton's stress, controlling the local pressure within the skeleton material's tolerance range, preventing excessive local pressure on the skeleton due to stress concentration at the clamping points, improving the accuracy of the compression test and the versatility of the device.

[0017] 2. This invention places the drone frame on two locking components below one side of the mounting base, so that the bottom of the frame contacts two adjacent pressure rollers in the two lower locking components, and the top of the frame corresponds to two adjacent pressure rollers in the two upper locking components. Next, the motor is controlled to operate and drive the bidirectional lead screw to rotate. During the rotation of the bidirectional lead screw, its two outer sliding plates can move closer together, and respectively drive the two upper and two lower locking components to move closer together, until the two upper and two lower middle pressure rollers are in complete contact with the top and bottom of the frame. As the two sliding plates continue to move closer, the four middle pressure rollers... When the roller is pressed, it drives the rotary bearing to rotate outside the connecting shaft through the support rod. At the same time, the pressure roller on the other side of the support rod outside the rotary bearing deflects synchronously until the two pressure rollers in the locking assembly are tightly fitted with the top or bottom and the side of the skeleton, respectively. By positioning the four corners of the skeleton at multiple points, the installation stability is improved. When the two slide plates stop moving, the pressure rollers in the four locking assemblies can push the skeleton to the center of the mounting base, so that it corresponds to the position of the multiple top material components in the sliding assembly. This can correct the position of the skeleton and center it without the need for manual adjustment of the skeleton's position, so as to achieve the purpose of rapid pressure testing of the skeleton. Attached Figure Description

[0018] 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.

[0019] Figure 1 This is a three-dimensional structural schematic diagram of the present invention;

[0020] Figure 2 This is a schematic diagram of the connection between the compressive strength testing component and the support rod of the present invention;

[0021] Figure 3 This is a schematic diagram of the structure of the pressure resistance testing component of the present invention;

[0022] Figure 4 This is a schematic diagram of a partial cross-section of the limiting component of the present invention;

[0023] Figure 5 This is a schematic diagram of the top material assembly of the present invention;

[0024] Figure 6 This is a schematic diagram of the connection between the upright plate and the mounting base of the present invention;

[0025] Figure 7 This is a schematic diagram of the structure of the mounting base of the present invention;

[0026] Figure 8 This is a schematic diagram of the locking component of the present invention;

[0027] Figure 9 This is a schematic diagram of the connection between the slide and the perforation in this invention.

[0028] The attached diagram lists the components represented by each number as follows:

[0029] 1. Test support frame; 2. Compression test control box; 3. Compression testing assembly; 301. Electro-hydraulic telescopic rod; 302. Middle partition; 303. Pressure sensing assembly; 304. Limiting slide rod; 4. Support rod; 5. Sliding assembly; 501. Box body; 502. Cover plate; 503. Protective cover; 504. Steel ball; 6. Perforation; 7. Limiting assembly; 701. Slide seat; 702. Sliding hole; 703. First spring; 8. Groove; 9. Ejector assembly; 901. Ejector seat; 902. Hinge seat; 903. Second spring; 904. Anti-slip strip; 10. Vertical plate; 11. Mounting base; 12. Insertion hole; 13. Drive assembly; 131. Motor; 132. Two-way lead screw; 133. Slide plate; 14. Limiting hole; 15. Locking assembly; 151. Horizontal plate; 152. Connecting shaft; 153. Deflection groove; 154. Rotary bearing; 155. Support rod; 156. Pressure roller; 157. Anti-disengagement groove; 158. Spacer ring; 159. Torsion spring; 16. Heat dissipation hole. Detailed Implementation

[0030] The technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of the present invention, and not all embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of the present invention.

[0031] Please see Figures 1-9 The present invention provides a technical solution:

[0032] A frame compression testing device for testing the strength of unmanned aerial vehicles (UAVs) includes a test support frame 1. A compression test control box 2 is fixedly installed on one side of the test support frame 1. The compression test control box 2 has heat dissipation holes 16. A compression detection component 3 is fixedly connected to the side of the test support frame 1 away from the compression test control box 2. A sliding component 5 is fixedly connected to the end of the compression detection component 3. The compression detection component 3 includes an electro-hydraulic telescopic rod 301. One end of the electro-hydraulic telescopic rod 301 is fixed to one side of the inner wall of the test support frame 1. The other end of the electro-hydraulic telescopic rod 301 slides through a partition plate 302, which is fixed inside the test support frame 1. One end of the electro-hydraulic telescopic rod 301 through the partition plate 302 is fixed to one side of the sliding component 5. A pressure sensing component 303 is fixedly installed at the connection between the end of the electro-hydraulic telescopic rod 301 and the sliding component 5 to acquire pressure data.

[0033] The control of the electric hydraulic telescopic rod 301 causes it to move the pressure sensing component 303 and the sliding component 5 to the left. After the sliding component 5 moves, it squeezes the UAV frame. The pressure sensing component 303 monitors the applied pressure in real time, so that the display panel in the pressure test control box 2 can display the test information. At the same time, it is convenient to control the pressure applied by the electric hydraulic telescopic rod 301.

[0034] As a further embodiment of the present invention, support rods 4 are fixed through the four corners of the partition plate 302, and a vertical plate 10 is fixed on the side of the test support frame 1 away from the pressure testing component 3. The two ends of the support rods 4 are fixed between the inner wall of the test support frame 1 and the vertical plate 10, respectively. The top and bottom of the partition plate 302 are respectively slidably slidable through the limit slide rods 304, and one end of the two limit slide rods 304 is fixed to the sliding component 5.

[0035] The sliding assembly 5 includes a box body 501. One side of the box body 501 is fixed to the ends of two limiting slide rods 304 and an electric hydraulic telescopic rod 301. The top and bottom of the box body 501 are respectively fixed with cover plates 502 by screws. The inside of the box body 501 is filled with several steel balls 504. The cover plates 502 can be removed to add steel balls 504.

[0036] The operation of the electric hydraulic telescopic rod 301 causes the box body 501 to move to the left. The box body 501 then drives the two limiting slide rods 304 to slide in the middle partition 302, which serves to limit the box body 501 and improve the stability of the box body 501 driving the multiple top material components 9 to move horizontally.

[0037] Protective covers 503 are fixed on the front and rear sides of the box 501 respectively. The support rod 4 slides through the edge of the protective cover 503. The upright plate 10 has insertion holes 12 corresponding to the positions of the two protective covers 503.

[0038] The box body 501 drives the protective covers 503 on both the front and rear sides to move to the left in sync. Because the protective covers 503 slide outside the support rod 4, the stability of the horizontal movement of the protective covers 503 is improved. When the drone frame is subjected to a pressure test, the protective covers 503 can slide into the two holes 12 in the upright plate 10, so that it can isolate and block the front and rear of the frame. If the frame breaks, the generated debris will fall from the openings at the bottom of the two protective covers 503, preventing the frame from breaking from the front and rear and causing safety hazards. At the same time, it is convenient to collect the debris.

[0039] As a further embodiment of the present invention, a plurality of perforations 6 are provided on the side of the box 501 away from the electric hydraulic telescopic rod 301, and each group of perforations 6 consists of two perforations and a sliding limit component 7 is provided inside, the limit component 7 including a slide block 701.

[0040] Figure 9As shown, a sliding hole 702 is provided in the slide 701. The slide 701 slides through the sliding hole 702 and slides in the through hole 6 opened on the box body 501. Three first springs 703 are fixed in the sliding hole 702 opened on the slide 701. The other end of the first spring 703 is fixed to one side of the box body 501.

[0041] The slide block 701 is limited by the perforation 6 to improve its horizontal movement stability; the slide block 701 is pulled or supported by the force of the first spring 703, so that the slide block 701 can slide in the perforation 6 and return to its original position until all slide blocks 701 are in a flat state, so as to facilitate the next pressure test of the skeleton.

[0042] As a further embodiment of the present invention, the limiting component 7 is rotatably connected to the side away from the sliding component 5, the top component 9 includes a top seat 901, and a hinge seat 902 is fixed on the side of the top seat 901 near the slide 701. The hinge seat 902 is rotatably connected to one side of the slide 701 through a pin. A groove 8 is provided on the side of the slide 701 away from the box 501. Second springs 903 are fixed above and below the inner wall of the groove 8, respectively. The other ends of the two second springs 903 are fixed to the inner side of the top seat 901. The hinge seat 902 is located between the two second springs 903. The outer side of the top seat 901 is designed with an arc surface and is provided with several anti-slip strips 904.

[0043] During the process of the top material seat 901 extruding the skeleton, the protruding part on the skeleton will press the top or bottom of one side of the top material seat 901, causing the top material seat 901 to deflect in the slide 701 through the hinge seat 902, so that the raised part of the top material seat 901 contacts the recessed part on the skeleton. The top material seat 901 can fit with the irregular surface of the irregular skeleton. With the anti-slip strip 904, the top material seat 901 is prevented from slipping off the skeleton.

[0044] When the top material assembly 9 detaches from the frame, the force of the second spring 903 between the slide 701 and the top material seat 901 enables the top material seat 901 to rotate around the middle of one side of the slide 701 via the hinge seat 902 until the top material seat 901 is fully returned to its original position, facilitating the top material seat 901 to perform the next compression on the frame.

[0045] As a further embodiment of the present invention, a mounting base 11 is fixedly connected to the side of the upright plate 10 near the sliding component 5. A drive component 13 is installed through the inside of the mounting base 11. The drive component 13 includes a motor 131, which is fixed to the bottom of the test support frame 1. A bidirectional lead screw 132 is fixed on the output shaft of the motor 131. The two ends of the bidirectional lead screw 132 are rotatably connected to the mounting base 11 through bushings. Slide plates 133 are threadedly connected to the upper and lower parts of the bidirectional lead screw 132. The slide plates 133 are slidably connected inside the mounting base 11 and are fixed to the ends of the two locking components 15.

[0046] A limiting hole 14 is provided in the mounting base 11 at the position corresponding to the locking component 15, and the locking component 15 slides through the limiting hole 14. The locking component 15 includes a horizontal plate 151, which slides through the limiting hole 14, and one end of the horizontal plate 151 through the limiting hole 14 is fixed to the slide plate 133; a deflection groove 153 is provided on one side of the bottom of the horizontal plate 151, and a connecting shaft 152 is fixed to the inner wall of the deflection groove 153. A rotary bearing 154 is sleeved on the connecting shaft 152, and two support rods 155 are fixed to the outside of the rotary bearing 154. The included angle between the two support rods 155 is 90 degrees. A pressure roller 156 is installed at the bottom end of the support rod 155, and an anti-detachment groove 157 is provided on the outside of the pressure roller 156. If the edge of part of the drone frame is narrow, the edge of the frame can be inserted into the anti-detachment groove 157 on the outside of the pressure roller 156 to prevent the frame from slipping off the pressure roller 156.

[0047] During the rotation of the bidirectional lead screw 132, its two outer sliding plates 133 can approach each other, and respectively drive the two upper locking components 15 and the two lower locking components 15 to approach each other until the two upper middle pressure rollers 156 and the two lower middle pressure rollers 156 are in complete contact with the top and bottom of the skeleton, which facilitates clamping and locking the skeleton.

[0048] When the two slide plates 133 continue to approach each other, the four pressure rollers 156 in the middle will be pressed and will drive the rotary bearing 154 to rotate outside the connecting shaft 152 through the support rod 155. At the same time, the pressure roller 156 on the other side of the support rod 155 outside the rotary bearing 154 will deflect synchronously until the two pressure rollers 156 in the locking assembly 15 are tightly fitted with the top or bottom and the side of the frame respectively. By positioning the four corners of the frame at multiple points, the installation stability is improved.

[0049] As a further embodiment of the present invention, a spacer ring 158 is fixedly connected to one side of the rotary bearing 154, and a torsion spring 159 is fixed to one side of the inner wall of the deflection groove 153. The torsion spring 159 is sleeved on the outside of the connecting shaft 152. When the drone frame is removed, the two sliding plates 133 outside the bidirectional lead screw 132 are moved away from each other. With the force of the torsion spring 159, the rotary bearing 154 is driven to rotate outside the connecting shaft 152, so that the rotary bearing 154 can drive the pressure roller 156 back to its original position through the support rod 155, which facilitates the next locking of the frame.

[0050] Working principle of this invention:

[0051] During the compression test on the drone frame, the drone frame is placed on two locking components 15 below one side of the mounting base 11, so that the bottom of the frame contacts the two adjacent pressure rollers 156 of the two lower locking components 15, and the top of the frame corresponds to the two adjacent pressure rollers 156 of the two upper locking components 15. Next, the control motor 131 is activated, driving the bidirectional lead screw 132 to rotate. During the rotation of the bidirectional lead screw 132, its two outer sliding plates 133 can move closer together, respectively driving the two upper and two lower locking components 15 to move closer together, until the two upper and two lower middle pressure rollers 156 are in complete contact with the top and bottom of the frame. As the two sliding plates 133 continue to move closer, the four middle pressure rollers 156... When pressure is applied, the support rod 155 drives the rotary bearing 154 to rotate outside the connecting shaft 152. At the same time, the pressure roller 156 on the other side of the support rod 155 outside the rotary bearing 154 deflects synchronously until the two pressure rollers 156 in the locking assembly 15 are tightly fitted with the top or bottom and the side of the frame, respectively. By positioning the four corners of the frame at multiple points, the installation stability is improved. When the two slide plates 133 no longer move, the pressure rollers 156 in the four locking assemblies 15 can push the frame to the center of the mounting base 11, so that it corresponds to the position of the multiple top material assemblies 9 in the sliding assembly 5, thereby achieving the purpose of centering the frame. If the edge of some UAV frames is narrow, the edge of the frame can be inserted into the anti-detachment groove 157 outside the pressure roller 156 to prevent the frame from slipping off the pressure roller 156.

[0052] After locking the frame, the electric hydraulic telescopic rod 301 is operated to move the pressure sensing component 303 and the box 501 in the sliding component 5 to the left. The box 501 then drives the two limiting slide rods 304 to slide in the partition plate 302, which limits the box 501 and improves the stability of the horizontal movement of the box 501 and the multiple top material components 9. During the leftward movement of the box 501 and the top material components 9, they will come into contact with the frame. When the top material seat 901 in the top material component 9 presses against the frame, the top material seat 901, under force, will push the slide 701 to move in the through hole 6 through the hinge seat 902. The through hole 6 limits the slide 701 and improves its horizontal movement stability. At the same time, the end of the slide 701 located inside the box 501 presses the steel ball 504 in the box 501, so that the steel ball 504 can move within the box. As one or more slides 701 roll inside the box 501, the space inside the box 501 shrinks. The steel ball 504 then presses against other slides 701, causing them to be pushed out. The slides 701 then extend the top material assembly 9 until it fits against the outer wall of the frame. As the electric hydraulic telescopic rod 301 continues to apply pressure, the top material assembly 9 at the ends of multiple limit components 7 comes into complete contact with one side of the frame. At this time, the length of several slides 701 extending out of the box 501 will change. As the top material seat 901 continues to be pressed, the protrusion on the frame will press against the top or bottom of one side of the top material seat 901, causing the top material seat 901 to deflect in the slide 701 through the hinge seat 902, so that the raised part of the top material seat 901 contacts the recess on the frame.

[0053] During this process, the housing 501 will drive the protective covers 503 on both the front and rear sides to move synchronously to the left. Because the protective covers 503 slide outside the support rod 4, the stability of the horizontal movement of the protective covers 503 is improved. When the drone frame is subjected to a pressure test, the protective covers 503 can slide into the two holes 12 in the upright plate 10, so that they can isolate and block the front and rear of the frame. If the frame breaks, the resulting debris will fall from the openings at the bottom of the two protective covers 503, preventing the frame from breaking from the front and rear and causing safety hazards. At the same time, it is convenient to collect the debris. As the electric hydraulic telescopic rod 301 continues to apply pressure, the pressure sensing component 303 monitors the applied pressure in real time, so that the display panel in the pressure test control box 2 can display the test information. After the compression test of the skeleton is completed, the electric hydraulic telescopic rod 301 is retracted to pull the box 501 to the right. The box 501 then drives the sliding component 5 and the top component 9 to move to the right until the top component 9 is disengaged from the skeleton. During this process, the force of the second spring 903 between the slide 701 and the top component 901 allows the top component 901 to rotate around the middle of one side of the slide 701 through the hinge 902 until the top component 901 is fully returned to its original position. Then, the force of the first spring 703 pulls or supports the slide 701 so that the slide 701 can slide in the perforation 6 and return to its original position until all the slides 701 and the top component 901 are in a level state to facilitate the next compression operation on the skeleton.

[0054] When the drone frame is removed from one side of the mounting base 11, the control motor 131 operates to drive the bidirectional lead screw 132 to reverse, causing the two sliding plates 133 outside the bidirectional lead screw 132 to move away from each other, and causing the pressure roller 156 in the locking assembly 15 to gradually move away from the frame. With the help of the torsion spring 159, the rotary bearing 154 rotates outside the connecting shaft 152, so that the rotary bearing 154 can drive the pressure roller 156 back to its original position through the support rod 155. After the frame is removed, it can be clamped again.

Claims

1. A frame compression testing device for strength testing of unmanned aerial vehicles, comprising a test support frame (1), characterized in that: A compression test control box (2) is fixedly installed on one side of the test support frame (1). The compression test control box (2) has heat dissipation holes (16). A compression detection component (3) is fixedly connected to the side of the test support frame (1) away from the compression test control box (2). A sliding component (5) is fixedly connected to the end of the compression detection component (3). Several sets of through holes (6) are opened on the side of the sliding component (5) away from the compression detection component (3). Each set of through holes (6) has two holes and a sliding limit component (7) passes through them. A top material component (9) is rotatably connected to the side of the limit component (7) away from the sliding component (5). A vertical plate (10) is fixed on the side of the test support frame (1) away from the pressure testing component (3). A mounting base (11) is fixedly connected on the side of the vertical plate (10) close to the sliding component (5). A driving component (13) is installed through the inside of the mounting base (11). The bottom end of the driving component (13) passes through the mounting base (11) and is fixed to the bottom inside the test support frame (1). Locking components (15) are fixedly connected to the top and bottom of the outside of the driving component (13). A limiting hole (14) is opened in the mounting base (11) at the position corresponding to the locking component (15). The locking component (15) slides through the limiting hole (14). The pressure resistance testing component (3) includes an electro-hydraulic telescopic rod (301). One end of the electro-hydraulic telescopic rod (301) is fixed to one side of the inner wall of the test support. The other end of the electro-hydraulic telescopic rod (301) slides through a partition plate (302). The partition plate (302) is fixed inside the test support frame (1). One end of the electro-hydraulic telescopic rod (301) that passes through the partition plate (302) is fixed to one side of the sliding component (5). A pressure sensing component (303) is fixedly installed at the connection between the end of the electro-hydraulic telescopic rod (301) and the sliding component (5). Support rods (4) are fixed through the four corners of the partition plate (302). The two ends of the support rods (4) are fixed between the inner wall of the test support frame (1) and the upright plate (10). The top and bottom of the partition plate (302) are respectively connected by sliding limit rods (304). One end of the two limit rods (304) is fixed to the sliding assembly (5). The sliding assembly (5) includes a box body (501), one side of which is fixed to the ends of two limiting slide rods (304) and an electric hydraulic telescopic rod (301). The top and bottom of the box body (501) are respectively fixed with cover plates (502) by screws. The box body (501) is filled with several steel balls (504). Protective covers (503) are fixed on the front and rear sides of the box body (501). The support rod (4) slides through the edge of the protective cover (503). The upright plate (10) is provided with insertion holes (12) corresponding to the positions of the two protective covers (503). The through hole (6) is opened on the side of the box body (501) away from the electric hydraulic telescopic rod (301). The limiting component (7) includes a slide (701), which slides through two adjacent through holes (6). A sliding hole (702) is provided in the slide (701). Three first springs (703) are fixed on one side of the inner wall of the sliding hole (702). The other end of the first spring (703) is fixed on the inner wall of the box (501) near the through hole (6). The top material assembly (9) includes a top material seat (901). A hinge seat (902) is fixed on the side of the top material seat (901) near the slide (701). The hinge seat (902) is rotatably connected to one side of the slide (701) by a pin. A groove (8) is provided on the side of the slide (701) away from the box (501). A second spring (903) is fixed above and below the inner wall of the groove (8). The other end of the two second springs (903) is fixed to the inner side of the top material seat (901). The hinge seat (902) is located between the two second springs (903). The outer side of the top material seat (901) is designed with an arc surface and is provided with several anti-slip strips (904).

2. The frame compression testing device for UAV strength testing according to claim 1, characterized in that: The drive assembly (13) includes a motor (131), which is fixed at the bottom of the test support frame (1). A bidirectional lead screw (132) is fixed on the output shaft of the motor (131). The two ends of the bidirectional lead screw (132) are rotatably connected to the mounting base (11) through bushings. A sliding plate (133) is threaded to the upper and lower parts of the outside of the bidirectional lead screw (132). The sliding plate (133) is slidably connected inside the mounting base (11). The sliding plate (133) is fixed to the ends of two locking assemblies (15).

3. The frame compression testing device for UAV strength testing according to claim 2, characterized in that: The locking assembly (15) includes a horizontal plate (151), which slides through the limiting hole (14) and one end of the horizontal plate (151) through the limiting hole (14) is fixed to the slide plate (133). A deflection groove (153) is provided on one side of the bottom of the horizontal plate (151). A connecting shaft (152) is fixed on the inner wall of the deflection groove (153). A rotary bearing (154) is sleeved on the connecting shaft (152). Two support rods (155) are fixed on the outside of the rotary bearing (154). The included angle between the two support rods (155) is 90 degrees. A pressure roller (156) is installed at the bottom end of the support rod (155). An anti-detachment groove (157) is provided on the outside of the pressure roller (156).

4. The frame compression testing device for UAV strength testing according to claim 3, characterized in that: A spacer ring (158) is fixedly connected to one side of the rotary bearing (154), and a torsion spring (159) is fixed to one side of the inner wall of the deflection groove (153). The torsion spring (159) is sleeved on the outside of the connecting shaft (152).

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