Unmanned aerial vehicle testing device and control method

Abstract

The invention discloses an unmanned aerial vehicle testing device and a control method, and relates to the technical field of unmanned aerial vehicle testing, and the unmanned aerial vehicle testing device comprises a base, a steering member and a flexible connecting member. The steering part is mounted on the upper side of the base and used for mounting the unmanned aerial vehicle and enabling the unmanned aerial vehicle to move relative to the base; the two ends of the flexible connecting piece are connected with the steering piece and the base. The base is arranged to fix the unmanned aerial vehicle, the steering part is arranged on the base, the unmanned aerial vehicle can be installed on the base, and the unmanned aerial vehicle can move relative to the base through the steering part; meanwhile, the unmanned aerial vehicle is further provided with the flexible connecting piece, the two ends of the flexible connecting piece are connected with the steering piece and the base correspondingly, when the steering piece and the unmanned aerial vehicle are out of control, rapid spinning or breakage and loosening are caused, the flexible connecting piece can pull and limit movement of the unmanned aerial vehicle and the steering piece, and property loss and personal injury caused by out-of-control of the steering piece and the unmanned aerial vehicle are avoided.

Description

Technical Field

[0001] This invention relates to the field of unmanned aerial vehicle (UAV) testing technology, and in particular to a UAV testing device and control method. Background Technology

[0002] Currently, the production process of drones is mainly controlled by individual companies, and there is a lack of robust testing data to support the stability, durability, and consistency of the products. Products need to be launched to the market quickly, making them susceptible to insufficient testing and batch-to-batch variations in incoming materials, leading to quality fluctuations in the final product.

[0003] Commonly, testers repeatedly fly drones in the field for endurance testing. However, they are constrained by charging time, generator noise pollution, long application cycles for suitable airspace, and harsh weather conditions such as wind, rain, high temperatures, and sun exposure. This results in high labor intensity, low efficiency, and testers usually lack effective safety protection.

[0004] Some companies also use crane-based air-lift testing to verify the stability of flight control in the early stages, in order to avoid significant losses caused by crashes and delays in testing progress. Replacing batteries is laborious, renting crane vehicles is troublesome, and it requires open outdoor spaces. In bad weather such as wind and rain, the testing costs are high and the work efficiency is low.

[0005] A few companies have also adopted indoor test benches. However, such indoor test benches often require high-intensity durability testing with drones, which can easily lead to damage to the drones or loss of control due to device breakage, posing a safety hazard. Summary of the Invention

[0006] The main objective of this invention is to propose a drone testing device and control method, which aims to reduce the risk of loss of control during drone testing and improve the safety and stability of drone testing.

[0007] To achieve the above objectives, the present invention proposes a drone testing device, comprising a base, a steering component, and a flexible connector; the steering component is mounted on the upper side of the base and is used to mount the drone, enabling the drone to move relative to the base; the two ends of the flexible connector are connected to the steering component and the base.

[0008] In one embodiment, the steering component includes a universal joint and a mounting base; the universal joint is mounted on a base; the mounting base is connected to the universal joint, the mounting base is used to mount the drone and is movable relative to the base via the universal joint, and the two ends of the flexible connector are connected to the mounting base and the base.

[0009] In one embodiment, the universal joint includes a limiting plate and a universal ball. The limiting plate has a locking hole in the middle. There are two limiting plates, which are spaced apart and connected to each other by a connecting rod. The universal ball is locked between the two limiting plates and has a connecting part. The connecting part passes through the locking hole of one of the limiting plates and is connected to one of the base and the mounting base. The other of the base and the mounting base is connected to the other of the two limiting plates.

[0010] In one embodiment, the universal joint includes a pin, one of which has a first insertion hole on a limiting plate that engages with the pin, and one of the base and the mounting base has a second insertion hole that engages with the pin. The pin can pass through the second insertion hole and be inserted into the first insertion hole to limit the universal joint and the mounting base.

[0011] In one embodiment, the mounting base includes a connecting platform and a mounting bracket; the connecting platform is connected to a universal joint, and the two ends of a flexible connector are connected to the connecting platform and the base; the mounting bracket is mounted on the connecting platform and is bolted to the UAV through threaded holes.

[0012] In one embodiment, the mounting bracket has multiple threaded holes, at least some of which are spaced apart in the vertical direction, and the threaded holes at different heights can form different mounting combinations.

[0013] In one embodiment, a connecting arm is provided on the mounting bracket, and a retaining ring is detachably installed on the connecting arm for the main beam of the UAV to pass through for limiting. The connecting arm is bolted to the UAV through the threaded hole.

[0014] In one embodiment, multiple connecting arms are provided, and temporary support plates are installed between the multiple connecting arms to provide auxiliary support for the drone.

[0015] In one embodiment, multiple flexible connectors are provided, and the multiple flexible connectors are arranged around the periphery of the steering component.

[0016] In one embodiment, the base includes a counterweight platform and a support frame; the counterweight platform is used to place counterweight blocks; the support frame is installed on the counterweight platform, the support frame is connected to the steering component, and a flexible connector connects the steering component and the support frame.

[0017] The present invention also proposes a drone test control method based on a drone test device, which includes a base, a steering component, and a flexible connector; the steering component is installed on the upper side of the base and is used to mount the drone and enable the drone to move relative to the base; the two ends of the flexible connector are connected to the steering component and the base.

[0018] The control method includes the following steps: After the drone is installed on the steering component of the drone testing device, a test start command is obtained to control the drone to start. After the drone is started, control the drone to conduct a single test. In the single test, control the drone to enter multiple flight modes in sequence according to the preset time relationship, and execute the corresponding preset duration in each flight mode. After a single test is completed, control the drone to repeat the steps of the single test until the total time meets the preset test time. The operating parameters of the drone during the testing process are obtained so that testers can evaluate the aging process in conjunction with the mechanical loosening.

[0019] In one embodiment, the multiple flight modes include adjusting the flight attitude of the UAV to a first flight attitude and a second flight attitude, wherein the first flight attitude is a hovering attitude in which the multiple wings of the UAV are on the same horizontal plane, and the second flight attitude is a flight attitude in which the UAV is tilted relative to the horizontal plane.

[0020] In one embodiment, the operating parameters include at least one of the following: UAV control parameters, UAV flight attitude parameters, UAV temperature parameters, ambient temperature parameters, and ambient humidity parameters.

[0021] The technical solution of this invention employs a base for mounting and securing a drone. The base is equipped with a steering component, enabling the drone to be mounted on it and to move relative to the base to achieve different flight attitudes. Simultaneously, the invention also includes a flexible connector, with both ends connected to the steering component and the base respectively. This connector allows for tension on both the steering component and the base. When the steering component and the drone are operating normally, the flexible connector can bend and swing in coordination with the steering component, avoiding interference with normal operation. If the steering component and the drone become uncontrollable, causing rapid spinning or breakage, the flexible connector can pull and restrict the movement of the drone and the steering component, preventing property damage and personal injury caused by loss of control. Attached Figure Description

[0022] To more clearly illustrate the technical solutions in the embodiments of the present invention or the prior art, the drawings used in the description of the embodiments or the prior art 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 the structures shown in these drawings without creative effort.

[0023] Figure 1 This is a front view schematic diagram of an embodiment of the UAV testing device (loaded with a UAV) provided by the present invention; Figure 2 for Figure 1 A three-dimensional structural diagram of the drone testing device in the diagram; Figure 3 for Figure 2 A three-dimensional structural diagram of the rotating component; Figure 4 for Figure 1 3D exploded view of the test device for unmanned aerial vehicles (UAVs); Figure 5 This is a schematic diagram of the hardware operating environment device involved in the embodiments of the present invention; Figure 6 This is a flowchart illustrating the UAV test control method of the present invention.

[0024] Explanation of icon numbers: 100. Base; 110. Counterweight platform; 120. Support frame; 200. Steering component; 210. Universal joint; 211. Limiting plate; 2111. Locking hole; 2112. First insertion hole; 212. Universal ball; 2121. Connecting part; 220. Mounting base; 221. Connecting platform; 2211. Second insertion hole; 222. Mounting bracket; 2221. Connecting arm; 2222. Clamping ring; 2223. Temporary support plate; 300. Flexible connectors; 400. Bolt; 1001. Processor; 1002. Communication bus; 1003. User interface; 1004. Network interface; 1005. Memory.

[0025] The realization of the objective, functional features and advantages of the present invention will be further explained in conjunction with the embodiments and with reference to the accompanying drawings. Detailed Implementation

[0026] 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 a part of the embodiments of the present invention, and not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those of ordinary skill in the art without creative effort are within the scope of protection of the present invention.

[0027] It should be noted that if the embodiments of the present invention involve directional indicators (such as up, down, left, right, front, back, etc.), the directional indicators are only used to explain the relative positional relationship and movement of the components in a specific posture. If the specific posture changes, the directional indicators will also change accordingly.

[0028] Furthermore, if the embodiments of this invention involve descriptions such as "first" or "second," these descriptions are for descriptive purposes only and should not be construed as indicating or implying their relative importance or implicitly specifying the number of technical features indicated. Thus, a feature defined with "first" or "second" may explicitly or implicitly include at least one of those features. Additionally, the use of "and / or" or "and / or" throughout the text includes three parallel solutions. For example, "A and / or B" includes solution A, solution B, or a solution where both A and B are satisfied simultaneously. Furthermore, the technical solutions of the various embodiments can be combined with each other, but this must be based on the ability of those skilled in the art to implement them. When the combination of technical solutions is contradictory or impossible to implement, it should be considered that such a combination of technical solutions does not exist and is not within the scope of protection claimed by this invention.

[0029] Currently, the production process of drones is mainly controlled by individual companies, and there is a lack of robust testing data to support the stability, durability, and consistency of the products. Products need to be launched to the market quickly, making them susceptible to insufficient testing and batch-to-batch variations in incoming materials, leading to quality fluctuations in the final product.

[0030] Commonly, testers repeatedly fly drones in the field for endurance testing. However, they are constrained by charging time, generator noise pollution, long application cycles for suitable airspace, and harsh weather conditions such as wind, rain, high temperatures, and sun exposure. This results in high labor intensity, low efficiency, and testers usually lack effective safety protection.

[0031] Some companies also use crane-based air-lift testing to verify the stability of flight control in the early stages, in order to avoid significant losses caused by crashes and delays in testing progress. Replacing batteries is laborious, renting crane vehicles is troublesome, and it requires open outdoor spaces. In bad weather such as wind and rain, the testing costs are high and the work efficiency is low.

[0032] A few companies have also adopted indoor test benches. However, such indoor test benches often require high-intensity durability testing with drones, which can easily lead to damage to the drones or loss of control due to device breakage, posing a safety hazard.

[0033] Based on this, the present invention proposes a drone testing device.

[0034] See appendix Figure 1 and attached Figure 2 In one embodiment of the present invention, the drone testing device includes a base 100, a steering member 200, and a flexible connector 300; the steering member 200 is mounted on the upper side of the base 100 and is used to mount the drone and enable the drone to move relative to the base 100; both ends of the flexible connector 300 are connected to the steering member 200 and the base 100.

[0035] In this embodiment of the invention, a base 100 is provided for mounting and fixing the drone. A steering component 200 is provided on the base 100, which allows the drone to be mounted on the base 100 and to move relative to the base 100 via the steering component 200, thereby achieving different flight attitudes. Simultaneously, this embodiment also provides a flexible connector 300, with both ends of the flexible connector 300 connected to the steering component 200 and the base 100 respectively. This connector can pull on the steering component 200 and the base 100. When the steering component 200 and the drone are operating normally, the flexible connector 300 can bend and swing in coordination with the steering component 200 to avoid interfering with normal operation. When the steering component 200 and the drone become uncontrollable, resulting in rapid spinning or breakage, the flexible connector 300 can pull and restrict the movement of the drone and the steering component 200, preventing property damage and personal injury caused by the loss of control of the steering component 200 and the drone.

[0036] It should be noted that the flexible connector 300 in this embodiment can be set as a flexible structure with any strength that meets the test requirements, such as steel cable, high-strength nylon rope or elastic fiber bundle, etc. In this embodiment, the flexible connector 300 is set as a chain structure. The chain structure takes into account both strength and flexibility, and is not prone to breakage or excessive stretching failure. It also has good fatigue resistance under high frequency oscillation.

[0037] The steering component 200 can match various operating attitudes of the UAV. In the technical solution of the present invention, the specific structural form of the steering component 200 is not limited. It can be a mechanical structure that can realize multi-axis rotation, such as through hinge combination or other movable connection method, as long as it can meet the attitude adjustment of the UAV such as pitch, yaw, roll during the test.

[0038] See appendix Figure 3 In one embodiment, the steering component 200 includes a universal joint 210 and a mounting base 220; the universal joint 210 is mounted on the base 100; the mounting base 220 is connected to the universal joint 210, the mounting base 220 is used to mount the drone, and can move relative to the base 100 through the universal joint 210; both ends of the flexible connector 300 are connected to the mounting base 220 and the base 100.

[0039] In an embodiment of the present invention, the steering component 200 is configured as a structure consisting of a universal joint 210 and a mounting base 220. The universal joint 210 is mounted on the base 100, and the drone is mounted through the mounting base 220 connected to the universal joint 210, so that the drone mounted on the mounting base 220 can rotate or tilt relative to the base 100 through the universal joint 210, so as to ensure that the drone can make smooth attitude adjustments during testing.

[0040] It should be noted that the universal joint 210 in this embodiment can be a cross shaft structure composed of multiple hinge axes, or it can be a ball joint structure with a ball component, or other universal joint 210 structures that meet the test requirements in terms of strength and flexibility.

[0041] In one embodiment, the universal joint 210 includes a limiting plate 211 and a universal ball 212. The limiting plate 211 has a locking hole 2111 in the middle. There are two limiting plates 211, which are spaced apart and connected to each other by a connecting rod. The universal ball 212 is locked between the two limiting plates 211. The universal ball 212 has a connecting part 2121, which passes through the locking hole 2111 of one of the limiting plates 211 and is connected to one of the base 100 and the mounting base 220. The other of the base 100 and the mounting base 220 is connected to the other of the two limiting plates 211.

[0042] See appendix Figure 3 and attached Figure 4 In an embodiment of the present invention, the universal joint 210 includes a limiting plate 211 and a universal ball 212. Two limiting plates 211 are provided, and a locking hole 2111 is provided in the middle of the limiting plate 211, so that the limiting plate 211 can lock the universal ball 212 between the two limiting plates 211 through the locking hole 2111, thereby ensuring that the universal ball 212 can rotate between the two limiting plates 211. This allows the drone and the mounting base 220 to rotate and tilt relative to the base 100. Compared with the general universal joint 210 structure, it has stronger rotation and tilt flexibility, and the maximum tilt angle of the mounting base 220 and the drone can be adjusted according to the size of the locking hole 2111 and the spacing of the limiting plates 211.

[0043] It should be noted that the omnidirectional ball 212 in this embodiment has a connecting part 2121, which can be configured to pass through the locking hole 2111 of the limiting plate 211 near the base 100 and connect to the base 100, while the limiting plate 211 near the mounting base 220 is connected to the mounting base 220, so that the limiting plate 211 and the mounting base 220 can rotate and tilt relative to the base 100; or the connecting part 2121 can pass through the locking hole 2111 of the limiting plate 211 near the mounting base 220 and connect to the mounting base 220, while the limiting plate 211 near the base 100 is connected to the base 100, so that the mounting base 220 can rotate and tilt relative to the limiting plate 211 and the base 100. Both connection methods can realize the rotation and tilting movement of the drone and the mounting base 220 relative to the base 100. Specifically, this embodiment will be described using the connection between the connecting part 2121 and the mounting base 220 as an example.

[0044] When the drone is installed on the mounting base 220, it is easy for the steering component 200 to tilt due to rotation, making it difficult to install properly. In some extreme cases, this may damage the drone or even cause personal injury. Therefore, when installing the drone, the mounting base 220 and the steering component 200 can be fixed to reduce the occurrence of the above situations.

[0045] In some embodiments, a structure is adopted that can lock the mounting base 220 and the steering component 200 to maintain the stability of the installation. When testing, the lock is released so that the mounting base 220 and the steering component 200 can move normally.

[0046] Specifically, the universal joint 210 includes a pin 400, one of which, the limiting plate 211, has a first insertion hole 2112 that mates with the pin 400. One of the base 100 and the mounting base 220 has a second insertion hole 2211 that mates with the pin 400. The pin 400 can pass through the second insertion hole 2211 and be inserted into the first insertion hole 2112 to limit the universal joint 210 and the mounting base 220.

[0047] In an embodiment of the present invention, a first insertion hole 2112 is provided on one of the limiting plates 211, and a second insertion hole 2211 is provided on one of the base 100 and the mounting base 220. The pin 400 can pass through the first insertion hole 2112 and the second insertion hole 2211 to lock the universal ball 212 and prevent the universal ball 212 from rotating, so as to facilitate the installation of the UAV on the mounting base 220. Specifically, in this embodiment, after the pin 400 is inserted into the first insertion hole 2112 and the second insertion hole 2211, the mounting base 220 can be set horizontally, further improving the convenience and reliability of installation.

[0048] It should be noted that the connecting part 2121 can be connected to the base 100, and a second socket 2211 can be provided on the base 100; alternatively, the connecting part 2121 can be connected to the mounting base 220, and a second socket 2211 can be provided on the mounting base 220. Both configurations allow for locking of the universal ball 212 through the connecting part 2121 and the connected mounting base 220 or base 100. Specifically, in this embodiment, the example of the connecting part 2121 being connected to the mounting base 220, and the mounting base 220 having a second socket 2211, will be used for explanation.

[0049] It should be understood that the mounting base 220 in the embodiments of the present invention is used to mount the drone. The mounting base 220 can be set as any structure that can reliably mount the drone, such as a flat plate structure, a frame structure or a snap-fit ​​structure, as long as it can stably support the drone and adapt to various attitude changes during its testing process.

[0050] In one embodiment, the mounting base 220 includes a connecting platform 221 and a mounting bracket 222; the connecting platform 221 is connected to the universal joint 210, and the two ends of the flexible connector 300 are connected to the connecting platform 221 and the base 100; the mounting bracket 222 is mounted on the connecting platform 221, and the mounting bracket 222 is bolted to the UAV through a threaded hole.

[0051] In an embodiment of the present invention, the mounting base 220 includes a connecting platform 221 and a mounting bracket 222. The mounting bracket 222 is provided with a threaded hole, which can be bolted to the drone to mount the drone on the connecting platform 221 via the mounting bracket 222, and the connecting platform 221 is connected to the universal joint 210, so that the mounting bracket 222 and the drone can move relative to the base 100.

[0052] It should be noted that the number of threaded holes in this embodiment can be set arbitrarily, such as 8, 16 or more or fewer, while meeting the installation strength requirements. They can also be arranged according to a certain pattern to improve the convenience and flexibility of installation.

[0053] In one embodiment, the mounting bracket 222 has multiple threaded holes, at least some of which are spaced apart in the vertical direction, and the threaded holes at different heights can form different mounting combinations.

[0054] In embodiments of the present invention, multiple threaded holes are provided, and the threaded holes are spaced apart in the vertical direction, so that the UAV can be installed on the threaded holes at different heights with different installation combinations. That is, the installation height and position of the UAV can be adjusted and changed through multiple threaded holes, thereby improving the flexibility of UAV installation.

[0055] In one embodiment, a connecting arm 2221 is provided on the mounting bracket 222, and a retaining ring 2222 is detachably installed on the connecting arm 2221 for the main beam of the UAV to be limited and inserted. The connecting arm 2221 is bolted to the UAV through a threaded hole.

[0056] It should be noted that the retaining ring 2222 in this embodiment can also be adapted and limited to the main beams in other parts of the drone fuselage, such as the main beams on the front and rear sides of the fuselage, or other beam structures with supporting functions. Specifically, in this embodiment, the inner diameter of the retaining ring 2222 is adapted to the outer diameter of the main beams on the left and right sides (frame) of the drone fuselage as an example.

[0057] In an embodiment of the present invention, a connecting arm 2221 is provided, and a detachable retaining ring 2222 is provided on the connecting arm 2221. The inner diameter of the retaining ring 2222 is adapted to the outer diameter of the main beams (framework) on the left and right sides of the drone body, so that the main beams (framework) are securely encircled and limited. In conjunction with the threaded hole and bolt connection with the drone, the installation and fixing effect of the drone can be improved.

[0058] In one embodiment, multiple connecting arms 2221 are provided, and temporary support plates 2223 are installed between the multiple connecting arms 2221 to provide auxiliary support for the drone.

[0059] In an embodiment of the present invention, a temporary support plate 2223 is installed on the connecting arm 2221, which can provide temporary support when the drone is initially assembled or disassembled, eliminating the need for multiple operators to manually maintain the drone's horizontal support during installation, thus improving installation efficiency.

[0060] In one embodiment, a plurality of flexible connectors 300 are provided, and the plurality of flexible connectors 300 are arranged around the periphery of the steering member 200.

[0061] In the embodiments of the present invention, multiple flexible connectors 300 are evenly distributed in a ring around the steering component 200, which improves the stability of the overall structure and effectively distributes the tensile force borne by a single connector, thereby enhancing the reliability of pulling and limiting in case of loss of control.

[0062] It is understood that the flexible connector 300 in this embodiment is described with 4 units as an example, but it can also be set to more or fewer units, such as 3 or 8 units, provided that the strength requirements are met, and set to be evenly distributed in a ring around the steering component 200 to improve the reliability of the traction limit.

[0063] It should be noted that the base 100 in this embodiment is used to support and fix the drone. It can be set as a flat plate, a frame or other stable structure, and connected to the ground or wall or other working surface by means of bolts, welding or embedded snaps, as long as it can provide sufficient support and stability to ensure that the drone will not overturn or shift during the test.

[0064] Specifically, the base 100 includes a counterweight platform 110 and a support frame 120; the counterweight platform 110 is used to place the counterweight; the support frame 120 is installed on the counterweight platform 110, the support frame 120 is connected to the steering component 200, and the flexible connector 300 is connected to the steering component 200 and the support frame 120.

[0065] In an embodiment of the present invention, the counterweight platform 110 is provided to hold counterweight blocks, preventing the movement of the drone from causing the base 100 to shake or even tip over, thereby further improving safety.

[0066] It should be noted that the executing entity in this embodiment can be a computing service device with data processing, network communication, and program execution functions, such as a tablet computer, personal computer, or mobile phone; or a drone test and control terminal capable of performing the above functions, specifically, such as... Figure 5 As shown, the UAV test control terminal may include: a processor 1001, such as a central processing unit (CPU), a communication bus 1002, a user interface 1003, a network interface 1004, and a memory 1005. The communication bus 1002 is used to enable communication between these components. The user interface 1003 may include a display screen and an input unit such as a keyboard; optionally, the user interface 1003 may also include a standard wired interface or a wireless interface. The network interface 1004 may optionally include a standard wired interface or a wireless interface (such as a Wi-Fi interface). The memory 1005 may be a high-speed random access memory (RAM) or a stable non-volatile memory (NVM), such as a disk drive. Optionally, the memory 1005 may also be a storage device independent of the aforementioned processor 1001.

[0067] Those skilled in the art will understand that Figure 5 The structure shown does not constitute a limitation on the test control terminal for unmanned aerial vehicles (UAVs) and may include more or fewer components than shown, or combine certain components, or have different component arrangements.

[0068] like Figure 5 As shown, the memory 1005, as a storage medium, may include an operating system, a data storage module, a network communication module, a user interface module, and a UAV-based test control program. Figure 5 In the UAV test control terminal shown, the network interface 1004 is mainly used for data communication with the network server; the user interface 1003 is mainly used for data interaction with the user; the processor 1001 and memory 1005 in the UAV test control terminal of the present invention can be set in the UAV test control terminal, and the UAV test control terminal calls the UAV test control program stored in the memory 1005 through the processor 1001 and executes the UAV test control method provided in the embodiment of the present invention.

[0069] See appendix Figure 6This invention also proposes a drone testing and control method based on a drone testing device. The specific structure of the drone testing device is as described in the above embodiments. Since this drone testing and control method adopts all the technical solutions of all the above embodiments, it has at least all the beneficial effects brought about by the technical solutions of the above embodiments, which will not be elaborated here. The control method includes the following steps: S10. After installing the drone on the steering component of the drone testing device, obtain the test start command to control the drone to start. It should be noted that the test start command can be a control command output by the host computer, used to start the drone for testing after the drone is installed on the drone testing device; It is understood that in this embodiment, the drone testing device can be set up in the laboratory, so that the test is not affected by external weather changes, and can be connected to the drone through a programmable power supply to replace the traditional battery power supply, providing continuous power without the need to replace batteries or charge, thereby improving testing efficiency. S20. After the drone is started, control the drone to perform a single test. In the single test, control the drone to enter multiple flight modes in sequence according to the preset time relationship, and execute the corresponding preset duration in each flight mode. It should be noted that the preset timing relationship and preset duration are set according to the test requirements, and may include modes such as hovering, climbing, translation and swinging, and specific power and angle parameters can be set. Understandably, the switching between various flight modes is monitored and recorded in real time by the host computer, which dynamically calibrates the drone's attitude and operational data and uses video monitoring to ensure that testers can stop the test process at any time if they observe any abnormalities. If problems such as crashes or fires occur during the test, key frame videos are edited, logs are uploaded, and the aircraft is repaired. If any abnormality is found in the video during the test, the testers can click the stop button at any time to stop the automated program, then go to the aging chamber door to disconnect the power, open the door, and enter to handle the situation, ensuring that the test process is safe and controllable. S30. After a single test is completed, control the drone to repeat the steps of the single test until the total time meets the preset test time. It should be noted that the above-mentioned single test can include multiple different flight modes, and each test will be executed according to a preset timing sequence for a preset duration. The number of repetitions and the interval between each repetition can be configured according to on-site needs to meet the requirements of continuity and durability in different test scenarios. By repeating the test a corresponding number of times, the preset test duration is achieved, ensuring the accuracy and reliability of the test. Understandably, the preset test duration can be set according to the requirements of the test task and determined in conjunction with the working shift duration of the operators; S40. Obtain the operating parameters of the drone during the test process, so that the testers can conduct an aging evaluation in conjunction with the mechanical loosening situation; It should be noted that after the drone repeats a single test until the total time meets the preset test duration, the tester can confirm the drone's mechanical loosening through video or direct observation, and judge the drone's aging degree in combination with the operating parameters.

[0070] In one embodiment, the multiple flight modes include adjusting the flight attitude of the UAV to a first flight attitude and a second flight attitude, wherein the first flight attitude is a hovering attitude in which the multiple wings of the UAV are on the same horizontal plane, and the second flight attitude is a flight attitude in which the UAV is tilted relative to the horizontal plane.

[0071] It should be noted that the first flight attitude is the stationary attitude of the UAV hovering on the UAV testing device, used for data acquisition under baseline conditions; the second flight attitude is the flight attitude of the UAV on the UAV testing device, which involves pitching or rolling, or a combination of pitching and rolling, or alternating between them; the first and second flight attitudes can be alternated or either flight attitude can be performed continuously to comprehensively cover the flight states that the UAV may encounter in actual operation. Specifically, in this embodiment, a single test is described using the alternation of the first and second flight attitudes as an example. A single test may include: controlling the UAV to enter the first flight attitude and enter a hovering and returning state to await instructions; controlling the UAV to maintain a pitch angle of 10 degrees for 60 seconds; then controlling the UAV to maintain a roll angle of 5 degrees for 5 seconds; then switching back to the first flight attitude and hovering for 10 seconds to complete the single test.

[0072] In one embodiment, the operating parameters include at least one of the following: UAV control parameters, UAV flight attitude parameters, UAV temperature parameters, ambient temperature parameters, and ambient humidity parameters; It should be understood that the operating parameters in this embodiment may include any one or more of the following: UAV control parameters, UAV flight attitude parameters, UAV temperature parameters, ambient temperature parameters, and ambient humidity parameters, to determine and record the aging of the UAV. Specifically, this embodiment uses an example where the operating parameters include all of the above parameters. The UAV control parameters may include UAV voltage control parameters, UAV PWM (Pulse Width Modulation) throttle control parameters, and UAV flight attitude control parameters; the UAV flight attitude parameters may include the values ​​of the UAV pitch angle and roll angle, and, together with the UAV temperature parameters after the test, provide a reference for UAV aging analysis; simultaneously, the operating parameters may also include ambient temperature and humidity parameters to assess the impact of external conditions on the aging of UAV materials.

[0073] Understandably, in this embodiment, the voltage parameters of the drone during testing can be adjusted before inputting the test start command to test the product's power consumption. Alternatively, the PWM throttle control parameters of the drone during testing can be adjusted so that the PWM throttle value gradually increases during the test, or set to a fixed value to simulate the changing operating states of the aircraft during actual operation, such as no load, half load, and full load, or the operating state under a specific load. Specifically, in this embodiment of the invention, the preset test duration of the drone can be set to two hours, the drone voltage can be set to 60 volts, and the PWM throttle value can be set to a fixed 400. Under the ambient temperature and humidity conditions of the laboratory, the host computer and the drone receive the test start command and enter a single test process, repeating the single test until the total duration reaches two hours.

[0074] It should be noted that the operating parameters in the embodiments of the present invention are not limited to the parameters mentioned above, and may also include more parameters that can be used to improve the comprehensiveness of the aging test evaluation of the UAV. In one embodiment, the operating parameters may include the PWM throttle control parameters, speed values, temperature values, fault information and current values ​​of each ESC of the UAV, the actual running time of the UAV, the frame vibration coefficient and the rotating radar status information, as well as the real-time status monitoring parameters of the CPU, frame and each ESC used by the UAV, and can be combined with the above information and the mechanical loosening and temperature conditions directly observed by the test personnel, so that the operator can more comprehensively evaluate the aging degree and fault conditions of the UAV during the test.

[0075] The above description is only a preferred embodiment of the present invention and does not limit the patent scope of the present invention. All equivalent structural transformations made under the concept of the present invention using the contents of the present invention specification and drawings, or direct / indirect applications in other related technical fields, are included within the patent protection scope of the present invention.

Claims

1. A drone testing device, characterized in that, include: Base; A steering component, mounted on the upper side of the base, is used to mount the drone and enable the drone to move relative to the base; as well as, A flexible connector, the two ends of which are connected to the steering component and the base.

2. The UAV testing device as described in claim 1, characterized in that, The steering component includes: Universal joint, mounted on the base; and The mounting base is connected to the universal joint, the mounting base is used to mount the drone and can move relative to the base via the universal joint, and the two ends of the flexible connector are connected to the mounting base and the base.

3. The UAV testing device as described in claim 2, characterized in that, The universal joint includes: A limiting plate, having a locking hole in the middle, comprises two such limiting plates, which are spaced apart and connected to each other by a connecting rod; and... A swivel ball is positioned between the two limiting plates. The swivel ball has a connecting portion that passes through a locking hole in one of the limiting plates and is connected to one of the base and the mounting base. The other of the base and the mounting base is connected to the other of the two limiting plates.

4. The UAV testing device as described in claim 3, characterized in that, The universal joint includes a pin, and one of the limiting plates has a first insertion hole that mates with the pin. One of the base and the mounting base has a second insertion hole that mates with the pin. The pin can pass through the second insertion hole and be inserted into the first insertion hole to limit the universal joint and the mounting base.

5. The UAV testing device as described in claim 2, characterized in that, The mounting base includes: A connecting platform, which is connected to the universal joint, and the two ends of the flexible connector are connected to the connecting platform and the base; and, The mounting bracket is installed on the connecting platform and is bolted to the UAV via threaded holes.

6. The UAV testing apparatus as described in claim 5, characterized in that, The mounting bracket has multiple threaded holes, at least partially spaced vertically, allowing the threaded holes at different heights to form different mounting combinations; and / or, The mounting bracket includes a connecting arm, on which a retaining ring is detachably mounted for the main beam of the UAV to pass through. The connecting arm is bolted to the UAV through the threaded hole.

7. The UAV testing apparatus as described in claim 6, characterized in that, The connecting arms are provided in multiple ways, and temporary support plates are installed between the multiple connecting arms to provide auxiliary support for the drone.

8. The UAV testing apparatus as described in claim 1, characterized in that, The base includes: A counterweight platform for holding counterweights; and, A support frame is installed on the counterweight platform, the support frame is connected to the steering component, and the flexible connector is connected between the steering component and the support frame.

9. A method for testing and controlling an unmanned aerial vehicle (UAV), characterized in that, Based on the UAV testing apparatus as described in any one of claims 1-8, the control method includes the following steps: After the drone is installed on the steering component of the drone testing device, a test start command is obtained to control the drone to start. After the drone is started, the drone is controlled to perform a single test. In the single test, the drone is controlled to enter multiple flight modes in sequence according to a preset time relationship, and to perform the corresponding preset duration in each flight mode. After a single test is completed, control the drone to repeat the steps of the single test until the total time meets the preset test time. The operating parameters of the drone during the testing process are obtained so that testers can evaluate the aging process in conjunction with the mechanical loosening.

10. The UAV test control method as described in claim 9, characterized in that, The multiple flight modes include adjusting the drone's flight attitude to a first flight attitude and a second flight attitude, wherein the first flight attitude is a hovering attitude in which multiple wings of the drone are on the same horizontal plane, and the second flight attitude is a flight attitude in which the drone is tilted relative to the horizontal plane; and / or, The operating parameters include at least one of the following: UAV control parameters, UAV flight attitude parameters, UAV temperature parameters, ambient temperature parameters, and ambient humidity parameters.

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