A kind of unmanned aerial vehicle rack support device for unmanned aerial vehicle detection

Abstract

The application relates to the technical field of unmanned aerial vehicle detection, and particularly relates to a kind of unmanned aerial vehicle rack support device for unmanned aerial vehicle detection, which comprises a stable seat, a swing seat, two arc-shaped bases of the swing seat are arranged in a cross shape, the bottom end of the arc-shaped base is protruded downward and forms a flange to contact the top end of the stable seat, the two ends of each arc-shaped base are connected with the stable seat through a spring, a stable frame, the stable frame is fixedly installed on the top of the swing seat, a bearing seat, the bearing seat is installed on the top of the stable frame, a vibrator, the vibrator is suspended in the middle of the bottom end of the bearing seat, a direction regulator and a load tester, the load tester is arranged on a fixed assembly, and the unmanned aerial vehicle rack support device for unmanned aerial vehicle detection is formed by the stable seat, the swing seat, the stable frame, the bearing seat, the vibrator, the direction regulator and the load tester, so that the durability detection effect of vibration test detection, simulation flight detection and carrying capacity detection on the unmanned aerial vehicle can be achieved.

Description

Technical Field

[0001] This invention relates to the field of drone inspection technology, and more specifically to a drone frame support device for drone inspection. Background Technology

[0002] As an important product of current technological development, drones are unmanned aircraft operated by radio remote control equipment and onboard program control devices. Drones are mainly divided into military and civilian applications. In the military field, drones are divided into reconnaissance drones and target drones. In the civilian field, they can be used in many fields such as aerial photography, agriculture, plant protection, mini selfies, express delivery, disaster relief, surveying and mapping, and power line inspection. Due to the inherent value of drones, there are higher requirements for their durability, such as their vibration resistance, wind resistance, and carrying capacity.

[0003] Therefore, in order to develop more durable drones that better meet usage requirements, there are strict testing methods for the drones themselves. This has led to the development of drone frame support devices, which are auxiliary testing equipment that supports the drone frame to test its durability. Most existing drone frame support devices only have a support function and lack testing functions, resulting in relatively simple functions and failing to effectively test the main durability performance of the drone.

[0004] During the search, it was found that Chinese patent publication numbers CN214418574U and CN210653690U, although they disclose a drone frame support device for drone testing, only focus on how to support and deploy the drone, without addressing how to perform durability testing on the drone. Therefore, the inventor proposes a drone frame support device for drone testing to reduce the limitations of existing technologies in terms of drone durability testing. Summary of the Invention

[0005] (a) Technical problems to be solved

[0006] To address the shortcomings of existing technologies, this invention provides a drone frame support device for drone testing that can perform durability tests on drones, thereby solving the problems of the prior art mentioned in the background section.

[0007] (II) Technical Solution

[0008] To achieve the above objectives, the present invention provides the following technical solution: a drone frame support device for drone testing, comprising a stabilizer base, and further comprising:

[0009] The rocker base has two arc-shaped bases arranged in a cross shape, with the bottom end of each arc-shaped base protruding downwards to form a flange that contacts the top end of the stabilizing base. Both ends of each arc-shaped base are connected to the stabilizing base by a spring.

[0010] A stabilizing frame, which is fixedly mounted on top of the swing base, and the stabilizing frame is frustum-shaped;

[0011] A support base is mounted on top of a stabilizer frame, and a fixing component for securing the drone is provided at the top of the support base;

[0012] A vibrator, which is suspended at the bottom center of the support base and is elastically connected to the stabilizer;

[0013] The directional adjuster has four components, and each of the four ends of the rocker seat has an adjustment shaft on its upper side. The directional adjuster is sleeved over the adjustment shaft and longitudinally installed on the top of the stabilizer.

[0014] A load tester, which is mounted on a fixed assembly, is used to test the flight load capacity of the UAV.

[0015] Furthermore, as a preferred embodiment of the present invention, the stabilizer includes:

[0016] The first ring is located on the upper side of the stabilizer and is connected to the bottom end of the support base;

[0017] The second ring is located on the lower side of the stabilizer, and the diameter of the second ring is larger than that of the first ring. The second ring is connected to the top of the rocker seat.

[0018] The number of support rods is at least four, and the multiple support rods are evenly distributed and connected between the first ring and the second ring.

[0019] Furthermore, as a preferred embodiment of the present invention, the vibrator includes:

[0020] A vibratory motor, wherein a variable diameter rod is connected to the upper side of the vibratory motor, and the outer diameter of the variable diameter rod increases sequentially from top to bottom, and a universal ball is connected to the top of the variable diameter rod;

[0021] A spherical frame, wherein the bottom end of the support base is provided with a protruding cover, and the spherical frame is installed at the bottom end of the protruding cover, and the universal ball is rotatably installed on the spherical frame;

[0022] A movable sleeve is fitted over the outside of the variable diameter rod, and the outer side of the movable sleeve is elastically connected to four support rods at corresponding positions among the plurality of support rods by at least four elastic elements.

[0023] Furthermore, as a preferred embodiment of the present invention, the elastic element includes:

[0024] The number of hinge seats one corresponds one-to-one with the number of elastic elements, and the hinge seats one are evenly distributed around the circumference and connected to the outer wall of the movable sleeve, and each hinge seat one is movably connected to a connecting rod one.

[0025] The number of hinge seats two corresponds one-to-one with the number of elastic elements, and the hinge seats two are evenly distributed around the circumference and connected to the inner sidewalls of multiple support rods, and each hinge seat two is movably connected to a connecting rod two.

[0026] The number of springs two corresponds one-to-one with the number of elastic elements. The two ends of spring two are respectively connected between the corresponding connecting rod one and connecting rod two. A pull rope runs through the inside of spring two, and the two ends of the pull rope are also respectively connected to the ends of connecting rod one and connecting rod two.

[0027] Furthermore, as a more preferred technical solution of the present invention, the direction adjuster includes:

[0028] An electric cylinder is fixedly mounted on the top of the stabilizer.

[0029] An adjusting ring, which is circular in shape, is fixedly installed on the top output end of each corresponding electric cylinder, and is concentrically sleeved on the outside of the corresponding adjusting shaft.

[0030] Based on the aforementioned scheme, the bottom of the adjusting shaft is provided with a planar structure, and a flat groove suitable for insertion of the planar structure is provided on the lower side of the inner wall of the adjusting ring.

[0031] Based on the aforementioned solution, the fixing component further includes:

[0032] The telescopic hook structure is configured as four sets, and the four sets of telescopic hook structures are arranged circumferentially on the support base for hooking the four rods on the UAV frame respectively. Each set of telescopic hook structures is arranged in opposite directions and in an alternating manner.

[0033] Furthermore, each telescopic hook structure also includes:

[0034] The hook body consists of a hook portion and a rod portion, with the rod portion passing through the support seat and extending to the lower side of the bottom end of the support seat. The support seat has an adjustment cavity on the outer side of the rod portion, and the inner diameter of the adjustment cavity is larger than the outer diameter of the rod portion.

[0035] The inner circumference of the adjustment cavity is provided with two upper annular grooves and two lower annular grooves. The arc lengths of the two upper annular grooves and the two lower annular grooves are the same and each is one-quarter of the inner diameter of the adjustment cavity.

[0036] Furthermore, each pair of adjacent upper annular slide grooves and lower annular slide grooves share a longitudinal groove, which is longitudinally opened on the inner wall of the adjustment cavity;

[0037] An adjusting tube is fixedly sleeved on the outside of the rod, and the adjusting tube and the adjusting cavity are slidably fitted together. A guide shaft is provided on the upper side of the outer wall of the adjusting tube.

[0038] The guide shaft is located inside the slide groove and can be slidably connected to the upper annular groove and the lower annular groove.

[0039] A guide rod is provided at the entrance of the lower annular slide groove, and a torsion spring is provided on the guide rod to press against the slide groove, so as to prevent the guide shaft from re-entering the upper annular slide groove when it rises, so that the guide shaft can smoothly slide into the lower annular slide groove.

[0040] The gear is fixedly fitted on the lower side of each of the rods, and the two gears between two adjacent rods are meshed together.

[0041] A connecting plate is provided on the lower side of each telescopic hook structure, and two corresponding rods are rotatably connected to the connecting plate by a ruler spring. A spring three is also sleeved on the rod, and the top end of the spring three is rotatably connected to the bottom end of the gear. The top end of the spring three is fixedly connected to the top end of the connecting plate.

[0042] Furthermore, based on the aforementioned solution, the load testing device further includes:

[0043] A pressure sensor is mounted between the connecting plate and each of the three springs.

[0044] (III) Beneficial Effects

[0045] Compared with the prior art, the present invention provides a drone frame support device for drone inspection, which has the following advantages:

[0046] 1. In this invention, a drone frame support device for drone testing is composed of a stabilizing seat, a swinging seat, a stabilizing frame, a bearing seat, a vibrator, a direction adjuster, and a load tester. This device achieves the effect of conducting vibration testing, simulated flight testing, and durability testing of drones, as well as testing their carrying capacity. Compared with existing drone testing support devices, this device improves the practicality of the support device.

[0047] 2. In this invention, by setting up a swing seat and using a vibrator, a comprehensive and multi-dimensional vibration test can be performed on the drone after it has been stabilized. This allows for a more comprehensive detection of the drone's vibration resistance. By setting different vibration times, the degree of damage to the drone can be observed during different vibration times. Each test uses a new drone from the same batch to obtain vibration test capability data for the drone.

[0048] 3. In this invention, the design of the direction adjuster can change the operating angle of the drone. Thus, based on the different flight modes and angles of the drone under strong winds, the degree of damage to the drone can be observed to test the wind resistance and flight durability of the drone. The operating intensity of the drone can be tested based on the wind force of the strong wind. (This application is an auxiliary support for strong wind testing. Strong wind turbines are not shown in the accompanying drawings of this application.)

[0049] 4. In this invention, the load tester is used to test the load weight of the drone. It is possible to observe the degree of damage to the drone itself when the weight increases, that is, when the lift of the drone increases. This allows for the simulation and detection of the maximum load-bearing weight when the drone is not damaged, and the durability test results when it carries items are obtained. Attached Figure Description

[0050] Figure 1 This is a schematic diagram of the structure of the UAV mounted on the support device according to this application;

[0051] Figure 2 This is an exploded view of the support device of this application;

[0052] Figure 3 This is a partial structural diagram showing the connection between the rocker base, electric cylinder, and adjusting ring in this application;

[0053] Figure 4 This is an exploded structural diagram showing the connection between the spherical frame, variable diameter rod, universal ball, and vibration motor in this application.

[0054] Figure 5 This is a schematic diagram of the connection between the spherical frame, the variable diameter rod, the universal ball, and the vibration motor in this application.

[0055] Figure 6 This is an exploded structural diagram of the bearing base, stabilizer frame, and fixing components of this application;

[0056] Figure 7 This is a schematic diagram of the mating structure of a set of telescopic hook structures in this application;

[0057] Figure 8 This is a partial cross-sectional view of the connecting plate and the rotator in this application;

[0058] Figure 9This is a schematic diagram of the layout structure of the support and hook body in this application;

[0059] Figure 10 This is a schematic diagram simulating the planar movement of the guide shaft within the upper and lower annular grooves of this application.

[0060] In the diagram: 1. Stabilizer; 2. Swing mount; 3. Fixing assembly; 4. Bearing seat; 5. Stabilizer frame; 6. Vibrator; 7. Direction adjuster; 8. Load tester; 9. Elastic element; 201. Arc-shaped base; 202. Spring 1; 301. Hook; 302. Adjusting tube; 303. Guide rod; 304. Gear; 305. Connecting plate; 306. Upper annular groove; 307. Lower annular groove; 308. Longitudinal groove; 309. Guide shaft; 310. Torsion spring; 311. Spring 3; 312. Rotator; 5 01. First ring; 502. Second ring; 503. Support rod; 601. Vibration motor; 602. Movable sleeve; 603. Variable diameter rod; 604. Universal ball; 605. Spherical frame; 606. Protrusion cover; 701. Electric cylinder; 702. Adjusting ring; 703. Planar structure; 704. Flat groove; 801. Pressure sensor; 901. Hinge seat one; 902. Hinge seat two; 903. Spring two; 904. Pull rope; 3121. Rotating rod; 3122. Rotating cap; 3123. Locking screw. Detailed Implementation

[0061] 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.

[0062] For examples, please refer to Figures 1 to 10 A drone frame support device for drone inspection includes a stabilizer 1, and further includes, in addition to, a stabilizer 1.

[0063] The swing seat 2 has two arc-shaped bases 201 arranged in a cross shape. The bottom end of the arc-shaped base 201 protrudes downward and forms a flange that contacts the top end of the stabilizer 1. Both ends of each arc-shaped base 201 are connected to the stabilizer 1 by a spring 202. The swing seat 2 is designed for vibration testing of UAVs. Its cross-shaped structure facilitates directional adjustment to simulate the angle during flight, allowing for better wind force testing.

[0064] In addition: a stabilizer 5, which is fixedly installed on the top of the swing seat 2, and the stabilizer 5 is frustum-shaped. The purpose of designing the stabilizer 5 as a frustum-shaped stabilizer is to provide better support and higher stability, and at the same time, it is convenient to carry out vibration testing in conjunction with the swing seat 2; a support seat 4, which is installed on the top of the stabilizer 5, and the top of the support seat 4 is provided with a fixing component 3 for fixing the UAV; a vibrator 6, which is suspended in the middle of the bottom end of the support seat 4, and the vibrator 6 is elastically connected to the stabilizer 5; four direction adjusters 7, and each of the four ends of the swing seat 2 is provided with an adjustment shaft. The direction adjusters 7 are sleeved on the outside of the adjustment shaft and are longitudinally installed on the top of the stabilizer 1; and a load tester 8, which is arranged on the fixing component 3 and is used to test the flight load capacity of the UAV.

[0065] Please see Figure 1 and Figure 2 In this preferred embodiment, the stabilizer 5 includes a first ring 501, a second ring 502, and support rods 503. The first ring 501 is located on the upper side of the stabilizer 5 and is connected to the bottom end of the bearing seat 4. The second ring 502 is located on the lower side of the stabilizer 5, and the diameter of the second ring 502 is larger than the diameter of the first ring 501. The second ring 502 is connected to the top end of the rocker seat 2. The number of support rods 503 is at least four, and multiple support rods 503 are evenly distributed between the first ring 501 and the second ring 502. Through this design, the stabilizer 5 is stable and lightweight, making it easy to handle. At the same time, the first ring 501 is smaller than the second ring 502, providing more stable support and making it less prone to tipping over during vibration testing.

[0066] Additionally, the vibrator 6 includes a vibration motor 601 and a movable sleeve 602. A variable diameter rod 603 is connected to the upper side of the vibration motor 601, and the outer diameter of the variable diameter rod 603 increases sequentially from top to bottom. A universal ball joint 604 is connected to the top of the variable diameter rod 603, and a spherical frame 605 is rotatably fitted around the universal ball joint 604. A protrusion cover 606 is provided at the bottom end of the bearing seat 4, and the spherical frame 605 is installed at the bottom end of the protrusion cover 606. The movable sleeve 602 is fitted around the outside of the variable diameter rod 603, and the outer side of the movable sleeve 602 is elastically connected to four corresponding support rods 503 via at least four elastic elements 9. Through the vibration of the vibration motor 601, combined with the cooperation of the universal ball joint 604 and the spherical frame 605, it can transmit vibration in multiple angles and directions. The movable sleeve 602 is rotatably fitted around the variable diameter rod 603. On rod 603, the movable sleeve 602 can move longitudinally under vibration, thereby improving the vibration coverage of vibrator 6. It is connected to stabilizer 5 through elastic element 9, and the vibration effect of vibration motor 601 is transmitted to stabilizer 5. Under the action of swing seat 2, stabilizer 5 realizes the shaking of support seat 4, thereby realizing vibration testing of UAV fixed on support seat 4. Spring 202 is set on the lower side of swing seat 2, which not only enhances the connection between swing seat 2 and stabilizer 1, but also when swing seat 2 vibrates, one side of spring 202 is compressed and the opposite side of spring 202 is stretched. The compressed spring 202 generates elastic force and the stretched spring 202 generates tension, which improves the reciprocating swinging action of swing seat 2, thereby improving the vibration effect of UAV vibration testing.

[0067] Please see Figure 4 and Figure 5 In a further preferred embodiment of the present invention, the elastic element 9 comprises:

[0068] The number of hinge seats 901 corresponds one-to-one with the number of elastic elements 9, and the hinge seats 901 are evenly distributed around the circumference and connected to the outer wall of the movable sleeve 602, and each hinge seat 901 is movably connected to a connecting rod.

[0069] The number of hinge seats 902 corresponds one-to-one with the number of elastic elements 9, and the hinge seats 902 are evenly distributed around the circumference and connected to the inner sidewalls of the multiple support rods 503, and each hinge seat 902 is movably connected to a connecting rod 2.

[0070] Spring 2 903, the number of spring 2 903 also corresponds one-to-one with the number of elastic elements 9, and the two ends of spring 2 903 are respectively connected between the corresponding connecting rod 1 and connecting rod 2, and a pull rope 904 passes through the inside of spring 2 903, and the two ends of pull rope 904 are also respectively connected to the ends of connecting rod 1 and connecting rod 2.

[0071] To better achieve vibration testing of UAVs, hinge seat 1 901 and hinge seat 2 902 are set up, allowing connecting rod 1 and connecting rod 2 to be movably connected to them respectively. The movable connection described in this application is an axial rotation connection, but it can also be a spherical universal rotation connection, providing different vibration effects. The spherical universal rotation connection structure involves replacing the shaft used for the axial connection with a ball, connecting the ball to one end of connecting rod 1 or connecting rod 2, and converting the shaft holes on hinge seat 1 901 and hinge seat 2 902, which cooperate with the axial rotation, into ball grooves adapted to the ball's rotation, achieving multi-directional universal rotation. This application takes an axial rotation connection as an example, using spring 2 90... 3. The vibration of connecting rod 1 is transmitted to spring 2 903. With the reciprocating action of compression and extension of spring 2 903, the vibration is transmitted to connecting rod 2 and simultaneously to the stabilizer 5. The design of this vibrator 6 is that each connection part is a movable connection. With the kinetic energy transmission of spring 1 202 and spring 2 903, the stabilizer 5 can be swayed in multiple angles and directions. Since the bottom of the swing seat 2 and the stabilizer 1 are only in contact, the structure above the swing seat 2 and the stabilizer 5 will also move in the longitudinal direction during the vibration of the vibrator 6. With the help of spring 2 903, the reciprocating vibration effect in the longitudinal direction is achieved, thereby achieving the purpose of simulating all-round vibration testing.

[0072] In addition, the design of the variable diameter rod 603 gradually thickening from top to bottom is intended to enhance the sway range between the universal ball 604 and the ball frame 605 by making the upper side of the variable diameter rod 603 thinner, thereby improving the vibration effect. The design of the lower side of the variable diameter rod 603 thicker is intended to improve the connection stability between the vibration motor 601 and the variable diameter rod 603, prevent the problem of breakage during vibration, and improve the service life.

[0073] Furthermore, the use of the pull rope 904 is to improve the connection between link one and link two. The length of the pull rope 904 is longer than the design of the spring, so it will not limit the range of spring extension and contraction. While ensuring vibration test detection, it improves the reliability of the structure and avoids the danger of vibration motor 601 tilting due to the disconnection between spring two 903 and link one or link two.

[0074] Please see Figure 1 , Figure 2 and Figure 3When it is necessary to conduct wind power tests on the drone, a powerful fan is first set up on the front side of the drone. In addition, based on the aforementioned solution, the preferred embodiment of the present invention is that the direction adjuster 7 includes an electric cylinder 701 and an adjusting ring 702. The electric cylinder 701 is fixedly installed on the top of the stabilizer 1. The adjusting ring 702 is circular and is fixedly installed on the top output end of each corresponding electric cylinder 701. The adjusting ring 702 is concentrically sleeved on the outside of the corresponding adjusting shaft.

[0075] The ring design, with the ring sleeved on the outside of the adjustment shaft, ensures that the adjustment shaft will sway at different positions along with the swing seat 2 during vibration testing of the drone. The ring's purpose is to prevent interference with the swing range of the swing seat 2. Simultaneously, in conjunction with the electric cylinder 701, when wind testing is conducted, the corresponding electric cylinder 701 is activated to raise whichever side of the drone needs to be raised. This causes the lower inner wall of the ring to contact the bottom of the adjustment shaft, pushing it upwards. The shape of the swing seat 2 causes it to tilt around its bottom area, thus tilting the drone fixed to the support seat 4. By raising the drone at four positions, the system simulates its ability to take off, land, and turn in strong winds. By observing the degree of damage and changes in the drone's wings, the system assesses the drone's flight durability under strong winds.

[0076] In addition, to better improve the ring's ability to support the adjustment shaft, the bottom of the adjustment shaft is provided with a planar structure 703, and a flat groove 704 suitable for the planar structure 703 to be inserted is provided on the lower side of the inner wall of the adjustment ring 702. By designing the planar structure 703 and the flat groove 704, the point contact when the ring and the adjustment shaft are in contact is transformed into surface contact or line contact, resulting in a larger contact range and stronger stability. Moreover, part of the planar structure 703 is embedded in the flat groove 704 (see figure), which prevents the adjustment shaft from shifting when it is lifted, thus avoiding affecting the accuracy of the UAV's simulated flight.

[0077] Based on the aforementioned solution, in order to better position the drone on the support 4, the fixing component 3 includes a telescopic hook structure. The telescopic hook structure is configured as four sets, and the four sets of telescopic hook structures are arranged circumferentially on the support 4. They are used to hook the four rods on the drone frame respectively. Each set of telescopic hook structures is arranged in opposite directions and alternately. The design of the telescopic hook structure is based on the linkage mechanism on the lower side of the drone frame, which is used to hook each corresponding position, thereby achieving the purpose of stable fixation of the drone frame on the support 4. Some drone frames may only have two linkage mechanisms on the lower side, but this telescopic hook structure can also be used. It should be noted that the research and development of drones is currently a key focus of development, and the investment in drone research and development is also substantial. Therefore, the durability testing of drones is also of paramount importance. Each type of drone will have its own suitable drone testing support device. Therefore, it is reasonable to match one type of drone with one testing support device. Therefore, this application does not need to consider whether it is suitable for testing multiple types of drones.

[0078] Please see Figure 6 and Figure 7 Each telescopic hook structure further includes a hook body 301, an adjusting tube 302, a guide rod 303, a gear 304, and a connecting plate 305. The hook body 301 consists of a hook portion and a rod portion, with the rod portion passing through the support seat 4 and extending to the lower side of the bottom end of the support seat 4. The support seat 4 has an adjusting cavity on the outer side of the rod portion, the inner diameter of the adjusting cavity being larger than the outer diameter of the rod portion. The inner circumferential wall of the adjusting cavity is provided with two upper annular grooves 306 and two lower annular grooves 307. The arc lengths of the 07 are the same and are all one-quarter of the inner diameter of the adjustment cavity. Each pair of adjacent upper annular grooves 306 and lower annular grooves 307 share a longitudinal groove 308. The longitudinal groove 308 is longitudinally opened on the inner wall of the adjustment cavity. The adjustment tube 302 is fixedly sleeved on the outside of the rod and slides with the adjustment cavity. A guide shaft 309 is provided on the upper side of the outer wall of the adjustment tube 302. The guide shaft 309 is located inside the groove and can slide with the upper annular groove and the lower annular groove.

[0079] The guide rod 303 is located at the entrance of the lower annular groove 307, and a torsion spring 310 is provided on the guide rod 303 to press it against the groove, preventing the guide shaft 309 from re-entering the upper annular groove 306 when it rises, so that the guide shaft 309 can smoothly slide into the lower annular groove 307. A gear 304 is fixedly fitted on the lower side of each rod, and the two gears 304 between two adjacent rods are meshed. The connecting plate 305 is located on the lower side of each telescopic hook structure. Furthermore, the two corresponding rods are rotatably connected to the connecting plate 305 via a spring, and a spring 311 is also sleeved on the rod. The top end of the spring 311 is rotatably connected to the bottom end of the gear 304. A rotating ring is fixedly connected to the upper side of the spring 311, and multiple balls are rolled on the rotating ring. The rolling contact between the balls and the bottom end of the gear 304 reduces the rotational friction between the spring and the gear 304 and improves the rotational effect. The top end of the spring 311 is fixedly connected to the top end of the connecting plate 305.

[0080] Once the drone is positioned on the support frame, four interconnected connecting plates 305 are manually pushed. These plates 305 cause two rods and corresponding adjusting tubes 302 to move upwards. At this time, spring 311 extends, and the guide shaft 309 on the adjusting tube 302 moves upwards along the longitudinal groove 308. When the guide shaft 309 encounters the lower annular groove 307, it rotates along the lower annular groove 307 under the action of a ruler spring (a known component, which can be understood by referring to a measuring tape). Since each telescopic hook structure includes two hook bodies 301, that is, two... The two rods, engaged by two identical gears 304 and simultaneously connected to the same connecting plate 305, cause one rod to rotate, while the other rotates in the opposite direction. This allows the hooks on the two hook bodies 301 to rotate after moving upwards. Once the hook bodies 301 have rotated a certain degree, releasing the hand causes the two hook bodies 301 to move downwards along the longitudinal groove 308 to the bottom under the action of the spring 311. Then, as needed, the connecting plate 305 is pushed again, causing the guide shaft 309 to move upwards along the longitudinal groove 308. At this point, due to the action of the spring, the rods will not reverse direction, and the guide shaft will continue to move upwards. The guide shaft 309 will move along the longitudinal groove 308 to the inside of the upper annular groove 306. Under the action of the spring, the guide shaft 309 slides along the upper annular groove 306 to the top of the next longitudinal groove 308. At this time, the hook body 301 rotates again. When the hand is released, the hook body 301 moves down along the longitudinal groove 308 again under the tension of the spring 311. When moving down, it encounters the guide rod 303 with the torsion spring 310. The guide rod 303 rotates to the entrance of the next lower annular groove 307. The guide shaft 309 moves down along the longitudinal groove 308 to the bottom, completing another rotation operation of the hook body 301. When the connecting plate 305 is pushed again, the guide rod 303 blocks the longitudinal groove 308 under the action of the torsion spring 310. When the guide shaft 309 reaches the entrance of the next lower annular groove 307, it will not continue to move upward under the action of the guide rod 303. Instead, it will slide into the lower annular groove 307 again under the action of the spring and drive the hook body 301 to rotate. Then, under the action of the spring 311, it will move to the bottom of the longitudinal groove 308. By pushing the connecting plate 305 each time, the above actions can be repeated to realize the angle change of the hook body 301 after lifting, thereby realizing the hooking and releasing of the UAV frame.

[0081] It should be noted that spring 311 has a large elasticity and can only be compressed when human intervention is involved. Without human intervention, the elastic force of spring 311 can effectively hook the stationary drone onto the carrier frame. This requirement can be achieved by selecting spring 311. In addition, regardless of whether it is the upper annular groove 306 or the lower annular groove 307, when the guide shaft 309 reaches the position of the lower annular groove 307, its hook can rise to the height of detaching from the drone frame without affecting the rotation of the hook body 301. Furthermore, the top of the carrier frame is pre-set with a groove for each time the hook body 301 descends to the lowest point of the longitudinal groove 308, ensuring that the top surface of the carrier frame is flat after each descent of the hook body 301, which facilitates the positioning of the drone that lands on the carrier frame.

[0082] Additionally, please see Figure 8 A circular groove concentric with the rod body is provided on the lower side of the connecting plate 305. A rotator 312 is installed inside the circular groove, rotatably connected to the groove. A rotating rod 3121 extends from the rotator 312, with one end connected to the middle of the ruler spring. Due to continuous operation, the ruler spring will release, reducing the rotational force on the rod. Therefore, the ruler spring can be periodically rotated using the rotator 312, a process commonly known as "tightening," to ensure the ruler spring retains its force. The outer side of 12 is provided with a rotating cap 3122, and a locking screw 3123 is screwed onto the outer circle of the rotating cap 3122. Multiple locking screw holes are opened on the circumference of the outer wall of the circular groove. When the ruler spring is tightened, the locking screw 3123 is loosened to separate it from the locking screw hole. Then the rotator 312 is rotated. After tightening is completed, the locking screw 3123 is screwed into the corresponding locking screw hole, thereby limiting the position of the rotator 312 and ensuring that the ruler spring does not loosen in the reverse direction after tightening.

[0083] In order to better test the carrying capacity of the drone, a load tester 8 is added to the fixed component 3. The load tester 8 includes a pressure sensor 801, which is installed between the connecting plate 305 and each spring 311.

[0084] When conducting a payload capacity test, the stabilizer 1 must first be fixed in the test position. A through-hole is provided in the middle of the swing seat 2, and a screw hole is provided at the top center of the stabilizer 1. A screw rod passes through the screw hole, and the lower side of the screw rod is screwed into the screw hole to lock the swing seat 2, ensuring the stability of the payload capacity test. Multiple pressure sensors 801 are connected to a numerical display screen. During the test, the drone is turned on and placed in a takeoff state. As the drone ascends, the hook 301 is pulled upwards, compressing the spring 311. When the spring 311 is compressed to a certain extent and no longer compressed, the pressure value on the numerical display screen is recorded. The sum of the pressure values ​​of multiple springs 311 is the payload weight carried by the drone, thus calculating the drone's payload capacity.

[0085] It should also be noted that the compression distance of spring 311 will not exceed the distance from the guide shaft 309 to the lower annular slide groove 307 within the longitudinal groove 308. This device has undergone multiple data calculations before manufacturing to ensure that the hook 301 rotates during the test of the UAV's carrying capacity.

[0086] Although embodiments of the 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 invention, the scope of which is defined by the appended claims and their equivalents.

Claims

1. A UAV frame support device for UAV testing, comprising a stabilizer (1), characterized in that, Also includes: The rocking seat (2) has two arc-shaped bases (201) arranged in a cross shape, and the bottom end of the arc-shaped base (201) protrudes downward and forms a flange that contacts the top end of the stable seat (1). Both ends of each arc-shaped base (201) are connected to the stable seat (1) by a spring (202). A stabilizer (5) is fixedly installed on the top of the rocker seat (2), and the stabilizer (5) is frustum-shaped; The support (4) is mounted on top of the stabilizer (5), and the top of the support (4) is provided with a fixing component (3) for fixing the UAV; Vibrator (6), which is suspended at the bottom center of the support (4) and is elastically connected to the stabilizer (5); The direction adjuster (7) has four components, and each of the four ends of the rocker seat (2) is provided with an adjustment shaft. The direction adjuster (7) is sleeved on the outside of the adjustment shaft and is longitudinally installed on the top of the stabilizer (1). A load tester (8) is arranged on a fixed assembly (3) for testing the flight load capacity of the UAV.

2. The UAV frame support device for UAV testing according to claim 1, characterized in that, The stabilizer (5) includes: The first ring (501) is located on the upper side of the stabilizer (5) and is connected to the bottom end of the support (4); The second ring (502) is located on the lower side of the stabilizer (5), and the diameter of the second ring (502) is larger than the diameter of the first ring (501). The second ring (502) is connected to the top of the rocker seat (2). Support rods (503), the number of which is at least four, and the plurality of support rods (503) are evenly distributed and connected between the first ring (501) and the second ring (502).

3. The UAV frame support device for UAV testing according to claim 2, characterized in that, The vibrator (6) includes: A vibration motor (601) is connected to a variable diameter rod (603) on its upper side. The outer diameter of the variable diameter rod (603) increases from top to bottom. A universal ball (604) is connected to the top of the variable diameter rod (603). The ball frame (605) has a raised cover (606) at the bottom end of the support base (4), and the ball frame (605) is installed at the bottom end of the raised cover (606). The universal ball (604) is rotatably installed on the ball frame (605). The movable sleeve (602) is sleeved on the outside of the variable diameter rod (603), and the outside of the movable sleeve (602) is elastically connected to four support rods (503) at corresponding positions in the plurality of support rods (503) by at least four elastic elements (9).

4. A drone frame support device for drone testing according to claim 3, characterized in that, The elastic element (9) includes: The number of hinge seats (901) corresponds one-to-one with the number of elastic elements (9), and the hinge seats (901) are evenly distributed around the outer wall of the movable sleeve (602), and each hinge seat (901) is movably connected to a connecting rod. The number of hinge seats (902) corresponds one-to-one with the number of elastic elements (9), and the hinge seats (902) are evenly distributed around the inner sidewalls of multiple support rods (503), and each hinge seat (902) is movably connected to a connecting rod (2). Spring 2 (903), the number of spring 2 (903) also corresponds one-to-one with the number of elastic elements (9), and the two ends of spring 2 (903) are respectively connected between the corresponding connecting rod 1 and connecting rod 2, and a pull rope (904) runs through the inside of spring 2 (903), and the two ends of the pull rope (904) are also respectively connected to the ends of connecting rod 1 and connecting rod 2.

5. A drone frame support device for drone testing according to claim 4, characterized in that, The direction adjuster (7) includes: An electric cylinder (701) is fixedly mounted on the top of the stabilizer (1); An adjusting ring (702) is circular in shape and is fixedly installed on the top output end of each corresponding electric cylinder (701), and the adjusting ring (702) is concentrically sleeved on the outside of the corresponding adjusting shaft.

6. A drone frame support device for drone testing according to claim 5, characterized in that, The bottom of the adjusting shaft is provided with a planar structure (703), and a flat groove (704) suitable for insertion of the planar structure (703) is provided on the lower side of the inner wall of the adjusting ring (702).

7. A drone frame support device for drone testing according to claim 6, characterized in that, The fixing component (3) includes: The telescopic hook structure is configured as four groups, and the four groups of telescopic hook structures are arranged circumferentially on the bearing seat (4) for hooking the four rods on the UAV frame respectively. Each group of telescopic hook structures is arranged oppositely and alternately. Each telescopic hook structure also includes: The hook body (301) is composed of a hook part and a rod part, and the rod part passes through the bearing seat (4) and extends to the lower side of the bottom end of the bearing seat (4). The bearing seat (4) has an adjustment cavity on the outside of the rod part, and the inner diameter of the adjustment cavity is larger than the outer diameter of the rod part. The inner circumference of the adjustment cavity is provided with two upper annular grooves (306) and two lower annular grooves (307). The arc lengths of the two upper annular grooves (306) and the two lower annular grooves (307) are the same and are all one-quarter of the inner diameter of the adjustment cavity. Furthermore, each pair of adjacent upper annular slide grooves (306) and lower annular slide grooves (307) share a longitudinal groove (308), which is longitudinally opened on the inner wall of the adjustment cavity; An adjusting tube (302) is fixedly sleeved on the outside of the rod, and the adjusting tube (302) and the adjusting cavity are slidably fitted together. A guide shaft (309) is provided on the upper side of the outer wall of the adjusting tube (302). The guide shaft (309) is located inside the slide groove and can be slidably connected to the upper annular slide groove and the lower annular slide groove. A guide rod (303) is provided at the entrance of the lower annular slide groove (307), and a torsion spring (310) is provided on the guide rod (303) to press against the slide groove, so as to prevent the guide shaft (309) from entering the upper annular slide groove (306) again when it rises, so that the guide shaft (309) can slide smoothly into the lower annular slide groove (307); Gears (304), each of the lower sides of the rod is fixedly fitted with a gear (304), and two gears (304) between two adjacent rods are meshed and connected; A connecting plate (305) is provided on the lower side of each telescopic hook structure, and two corresponding rods are rotatably connected to the connecting plate (305) by means of a ruler spring. A spring three (311) is also sleeved on the rod. The top end of the spring three (311) is rotatably connected to the bottom end of the gear (304), and the top end of the spring three (311) is fixedly connected to the top end of the connecting plate (305).

8. A drone frame support device for drone testing according to claim 7, characterized in that, The load testing device (8) includes: A pressure sensor (801) is mounted between the connecting plate (305) and each spring three (311).

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