Aeromagnetic testing device for unmanned aerial vehicle

Abstract

The utility model relates to an unmanned aerial vehicle aeromagnetic testing device comprising a pedestal, the pedestal is fixedly connected with a first installation seat, the first installation seat is internally provided with a first universal ball, the outside of the first universal ball is fixedly connected with a support frame, the support frame is fixedly connected with a guide rod, and the guide rod is fixedly connected with a second universal ball. The bottom of the unmanned aerial vehicle is connected with a support, a guide rod is arranged on the support, a lifting plate is slidably connected to the outer portion of the guide rod in a penetrating mode, a traction assembly is arranged on the outer portion of the lifting plate, and a force measuring assembly is further arranged on the outer portion of the supporting frame. The support at the bottom of the unmanned aerial vehicle is connected with the traction assembly, and then the unmanned aerial vehicle is started to fly and drives the lifting plate to move upwards; according to the unmanned aerial vehicle, the lifting plate abuts against the force measuring assembly so that force can be measured, meanwhile, through the arrangement of the first universal ball, steering of the supporting frame can be achieved when the unmanned aerial vehicle flies in a steering or inclined mode, and tension testing can also be achieved when the unmanned aerial vehicle flies at other inclined angles.

Description

Technical Field

[0001] The utility model relates to the technical field of unmanned aerial vehicle testing equipment, in particular to an unmanned aerial vehicle aeromagnetic testing device. Background Art

[0002] The aerial magnetic measurement system is an equipment system that installs magnetic measurement equipment on an airplane or other aircraft, and uses magnetic probes to measure the gradient of the geomagnetic field to conduct prospecting and other geomagnetic-related operations. The operation of the magnetic measurement system can be used to understand the local ore distribution and geological structure, and provide a reference for solving related problems in hydrology, environment and archaeology. Since the drone has a heavy load, it is necessary to perform a tension test on the drone.

[0003] After searching, a Chinese patent with announcement number: CN 219154752 U discloses a tensile test device for testing unmanned aerial vehicles, which relates to the technical field of tensile test of unmanned aerial vehicles. The tensile test device for testing unmanned aerial vehicles aims to solve the technical problem that it is inconvenient to adjust and place the unmanned aerial vehicles according to the different sizes under the existing technology; the tensile test device includes a workbench; a fixed shaft is fixedly installed on the upper end of the workbench, a table plate is fixedly installed on the upper end of the fixed shaft, a support plate is arranged on the upper end of the table plate, a limit position assembly is arranged on the bottom end of the support plate, an adjustment assembly is arranged on the inner side of the support plate, a mounting plate is arranged on the upper end of the adjustment assembly, a hook is fixedly installed on the upper end of the mounting plate, and a measuring assembly is arranged on the bottom end of the support plate.

[0004] When this patent is actually used, there are the following defects: the drone in this patent can only fly vertically upwards to perform tension testing, but cannot perform tension testing when the drone is tilting or turning during flight. Utility Model Content

[0005] Aiming at the technical problem that the UAV in the patent mentioned in the background technology can only perform tension test when flying vertically upwards, but cannot perform tension test when the UAV is tilted or turned during flight, the utility model provides a UAV aeromagnetic test device.

[0006] The technical solution adopted by the utility model is: a test device for unmanned aerial vehicle aeromagnetics, including a base, a first mounting seat fixedly connected to the base, a first universal ball installed in the first mounting seat, the outside of the first universal ball fixedly connected to a support frame, the support frame fixedly connected to a guide rod, the outside of the guide rod is slidably connected to a lifting plate, the outside of the lifting plate is provided with a hanging assembly, and the outside of the support frame is also provided with a force measuring assembly.

[0007] In one of the embodiments, a spring is fixedly connected to the outside of the support frame, and a section of the spring is fixedly connected to the lifting plate.

[0008] In one of the embodiments, the force measuring assembly includes a rotating plate rotatably connected to both sides of the support frame, a side plate fixedly connected to both sides of the support frame, and a force measuring sensor fixedly connected to the outside of the side plate.

[0009] In one embodiment, hinged plates are fixedly connected to the four sides of the support frame, and a pin is rotatably connected to the outside of the hinged plate, and the pin is fixedly connected to the rotating plate.

[0010] In one embodiment, the lifting plate is fixedly connected to a second mounting seat on the outside, a second universal ball is rotatably connected to the second mounting seat, the second universal ball is fixedly connected to a first support rod on the outside, the first support rod is fixedly connected to a third mounting seat on the outside, and a third universal ball is installed in the third mounting seat.

[0011] In one embodiment, the hanging assembly includes a second support rod fixedly connected to a third universal ball and hooks arranged on both sides of the second support rod, and the outer sides of the second support rod are rotatably connected to fourth universal balls, and the fourth universal ball is fixedly connected to the hooks.

[0012] In one of the embodiments, the outside of the hook is fixedly connected to a limiting rope, one end of the limiting rope is fixedly connected to a threaded cap, and the outside of the hook is provided with a threaded groove.

[0013] The beneficial effect of the utility model is as follows: compared with the prior art, in the utility model, the bracket at the bottom of the UAV is connected to the hanging component, and then the UAV is started to fly, the UAV drives the lifting plate to move upward, and the lifting plate is used to resist the force measuring component to perform force measurement, and at the same time, through the setting of the first universal ball, the support frame can be turned when the UAV is turning or tilting, and the tension test of the UAV when flying at other tilt angles can also be realized. BRIEF DESCRIPTION OF THE DRAWINGS

[0014] Figure 1 It is a structural schematic diagram of the utility model;

[0015] Figure 2 It is a three-dimensional structural schematic diagram of the utility model;

[0016] Figure 3 It is a schematic diagram of the axonometric structure of the utility model;

[0017] Figure 4 It is a structural schematic diagram of a hook in the utility model.

[0018] The markings in the figure are: 1. base; 2. first mounting seat; 3. first universal ball; 4. support frame; 5. side panel; 6. rotating plate; 7. hinged plate; 8. force sensor; 9. lifting plate; 10. spring; 11. guide rod; 12. second mounting seat; 13. second universal ball; 14. first support rod; 15. third mounting seat; 16. third universal ball; 17. second support rod; 18. hook; 19. threaded groove; 20. limit rope; 21. threaded cap; 22. fourth universal ball. DETAILED DESCRIPTION

[0019] In the description of the present invention, it should be noted that the terms "front", "up", "down", "left", "right", "vertical", "horizontal", etc. indicate orientations or positional relationships based on the orientations or positional relationships shown in the accompanying drawings. They are only for the convenience of describing the present invention and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation. Therefore, they cannot be understood as limitations on the present invention.

[0020] In the description of the present invention, it should be noted that, unless otherwise clearly specified and limited, the terms "installed", "connected", and "connected" should be understood in a broad sense, for example, it can be a fixed connection, a detachable connection, or an integral connection; it can be a direct connection, or an indirect connection through an intermediate medium, or it can be the internal communication of two components. For ordinary technicians in this field, the specific meanings of the above terms in the present invention can be understood according to specific circumstances.

[0021] The following is combined with Figure 1-4 The utility model is further described.

[0022] In order to solve the problems existing in the background technology, the present application proposes the following technical solutions: a test device for unmanned aerial vehicle aeromagnetic, including a base 1, a first mounting seat 2 is fixedly connected to the base 1, a first universal ball 3 is installed in the first mounting seat 2, and a support frame 4 is steered and adjusted, and the base 1 is fixedly connected to the ground or other fixed equipment, and the support frame 4 is fixedly connected to the outside of the first universal ball 3, and a guide rod 11 is fixedly connected to the support frame 4, and a lifting plate 9 is slidably connected to the outside of the guide rod 11, and the lifting plate 9 can be lifted and lowered. In order to cushion the lifting plate 9, a spring 10 is also fixedly connected to the outside of the support frame 4, and a section of the spring 10 is fixedly connected to the lifting plate 9.

[0023] In a further design, a hanging component is provided on the outside of the lifting plate 9, and a force measuring component is provided on the outside of the support frame 4.

[0024] Specifically: the force measuring assembly includes a rotating plate 6 rotatably connected to both sides of the support frame 4, a side plate 5 fixedly connected to both sides of the support frame 4, and a force sensor 8 fixedly connected to the outside of the side plate 5. A controller and a display screen are provided on the outside of the frame. The force sensor 8 and the display screen are electrically coupled to the controller. Therefore, when the drone drives the lifting plate 9 to move upward, the lifting plate 9 contacts the rotating plate 6, and the rotating plate 6 contacts the force sensor 8. The force detected by the force sensor 8 is displayed on the display screen, thereby realizing the test of the tensile force.

[0025] Among them, hinged plates 7 are fixedly connected on all four sides of the support frame 4 , and a pin is rotatably connected to the outside of the hinged plate 7 , and the pin is fixedly connected to the rotating plate 6 .

[0026] In another design, a second mounting seat 12 is fixedly connected to the outside of the lifting plate 9, a second universal ball 13 is rotatably connected to the second mounting seat 12, a first support rod 14 is fixedly connected to the outside of the second universal ball 13, a third mounting seat 15 is fixedly connected to the outside of the first support rod 14, a third universal ball 16 is installed in the third mounting seat 15, and the arrangement of the second universal ball 13 and the third universal ball 16 facilitates the angle adjustment of the first support rod 14 and the second support rod 17, thereby facilitating the flight of the UAV.

[0027] Specifically, the provided hanging assembly includes a second support rod 17 fixedly connected to the third universal ball 16 and hooks 18 arranged on both sides of the second support rod 17. The second support rod 17 is rotatably connected to the fourth universal ball 22 on both sides of the outside. The fourth universal ball 22 is fixedly connected to the hook 18. The fourth universal ball 22 is for the convenience of adjusting the angle of the hook 18, and a limiting rope 20 is fixedly connected to the outside of the hook 18. One end of the limiting rope 20 is fixedly connected to a threaded cap 21. A threaded groove 19 is provided on the outside of the hook 18, so the bracket at the bottom of the drone is connected to the hook 18, and the limiting rope 20 is passed through the bracket at the bottom of the drone and then threadedly connected to the outside of the hook 18.

[0028] In order for those skilled in the art to fully understand the technical solution, this embodiment is summarized as follows:

[0029] When in use, the bracket at the bottom of the drone is connected to the hook 18, and the limit rope 20 is passed through the bracket at the bottom of the drone and then threadedly connected to the outside of the hook 18;

[0030] Then the drone is started to fly, and the drone drives the lifting plate 9 to move upward, and the lifting plate 9 resists the rotating plate 6, and the rotating plate 6 resists the force sensor 8, and the force detected by the force sensor 8 is displayed on the display screen;

[0031] At the same time, by setting the first universal ball 3, the support frame 4 can be turned when the UAV is turning or tilting, and the tension test of the UAV when flying at other tilt angles can also be realized.

[0032] The standard parts used in the utility model can be purchased from the market, and special-shaped parts can be customized according to the description in the specification and the drawings. The specific connection methods of each part adopt the conventional means such as mature bolts, rivets, welding, etc. in the prior art. The machinery, parts and equipment all adopt the conventional models in the prior art, and the circuit connection adopts the conventional connection method in the prior art, which will not be described in detail here. The content not described in detail in this specification belongs to the prior art known to professional and technical personnel in this field.

[0033] Although the embodiments of the present invention have been shown and described, it will be apparent to those skilled in the art that the scope of the present invention is defined by the appended claims and their equivalents.

Claims

1. A test device for drone aeromagnetic, characterized in that: The invention comprises a base (1), a first mounting seat (2) being fixedly connected to the base (1), a first universal ball (3) being installed in the first mounting seat (2), a support frame (4) being fixedly connected to the outside of the first universal ball (3), a guide rod (11) being fixedly connected to the support frame (4), a lifting plate (9) being slidably connected to the outside of the guide rod (11), a hanging assembly being arranged on the outside of the lifting plate (9), and a force measuring assembly being also arranged on the outside of the support frame (4).

2. The unmanned aerial vehicle aeromagnetic testing device according to claim 1, characterized in that: A spring (10) is also fixedly connected to the outside of the support frame (4), and a section of the spring (10) is fixedly connected to the lifting plate (9).

3. The unmanned aerial vehicle aeromagnetic testing device according to claim 2, characterized in that: The force measuring assembly comprises a rotating plate (6) rotatably connected to both sides of the support frame (4), a side plate (5) fixedly connected to both sides of the support frame (4), and a force measuring sensor (8) fixedly connected to the outside of the side plate (5).

4. The unmanned aerial vehicle aeromagnetic testing device according to claim 3, characterized in that: The support frame (4) is fixedly connected to hinged plates (7) on all four sides, and the hinged plates (7) are rotatably connected to the outside with pins, which are fixedly connected to the rotating plates (6).

5. The unmanned aerial vehicle aeromagnetic testing device according to claim 4, characterized in that: The lifting plate (9) is fixedly connected to a second mounting seat (12) on the outside, a second universal ball (13) is rotatably connected to the second mounting seat (12), the second universal ball (13) is fixedly connected to a first support rod (14) on the outside, the first support rod (14) is fixedly connected to a third mounting seat (15) on the outside, and a third universal ball (16) is installed in the third mounting seat (15).

6. The unmanned aerial vehicle aeromagnetic testing device according to claim 5, characterized in that: The hanging assembly comprises a second support rod (17) fixedly connected to a third universal ball (16) and hooks (18) arranged on both sides of the second support rod (17); both sides of the outside of the second support rod (17) are rotatably connected to fourth universal balls (22); and the fourth universal ball (22) is fixedly connected to the hooks (18).

7. The unmanned aerial vehicle aeromagnetic test device according to claim 6, characterized in that: The outside of the hook (18) is fixedly connected to a limit rope (20), one end of the limit rope (20) is fixedly connected to a threaded cap (21), and the outside of the hook (18) is provided with a threaded groove (19).

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