Device for testing loading capacity of unmanned aerial vehicle

Abstract

The utility model discloses an unmanned aerial vehicle loading capacity testing device, which comprises an unmanned aerial vehicle body, a gravity traction seat, an electromagnetic rod and a metal seat, the bottom of the unmanned aerial vehicle body is fixedly connected with a lifting hook, the gravity traction seat is fixedly connected with two limiting sliding rods, the limiting sliding rods are sleeved with gravity blocks, and the gravity blocks are connected with the electromagnetic rod. The device has the advantages that the charge quantity of the electromagnetic coil can be increased or decreased by controlling the charge controller, the magnitude of magnetic attraction force of the electromagnetic rod can be controlled by the charge quantity of the electromagnetic coil, and therefore the hoisting and mating size of the unmanned aerial vehicle body can be adjusted; when the unmanned aerial vehicle body is separated from the hoisting of the electromagnetic rod, the unmanned aerial vehicle body has the maximum load value, the structure is reasonable, the maximum load capacity of the unmanned aerial vehicle body is conveniently tested, and the adjustment test is convenient.

Description

Technical Field

[0001] This utility model relates to the field of unmanned aerial vehicle (UAV) payload testing technology, and in particular to a UAV payload capacity testing device. Background Technology

[0002] During the production process of drones, their performance needs to be evaluated. Depending on the purpose of the drone, the test items also vary. For cargo drones, load capacity testing is one of the important test items. Currently, load capacity testing is only conducted by adding or removing counterweights. Since the unit weight of the counterweight is fixed, it is difficult to obtain the ultimate load value, resulting in rough test data. In addition, adding counterweights may cause the center of gravity to shift due to structural differences, which may lead to the risk of the device tipping over. This method still needs improvement.

[0003] When drones are used for loaded flights, load tests are required to prevent excessive load from causing the drone to be unable to fly or to fall, thus affecting the normal load capacity. Existing testing devices are not convenient for controlling the size of the counterweight, which in turn affects the efficiency of load testing. Therefore, there is an urgent need for a drone load capacity testing device to solve the above problems. Utility Model Content

[0004] To address the aforementioned problems, this utility model provides a device for testing the payload capacity of unmanned aerial vehicles (UAVs). This utility model is achieved through the following technical solution.

[0005] A drone payload capacity testing device includes a drone body, with a hook fixedly connected to the bottom of the drone body, and further includes:

[0006] A gravity traction seat, wherein two limiting slide rods are fixedly connected to the gravity traction seat, and a gravity block is sleeved on the limiting slide rod; a charge controller is fixedly connected to one side of the gravity traction seat.

[0007] An electromagnetic rod, wherein an electromagnetic coil is fixedly wound on the outer surface of the electromagnetic rod, and conductive wires are fixedly connected to both ends of the electromagnetic coil. The electromagnetic rod is fixedly connected to a gravity traction seat through two support plates.

[0008] A metal base, the top of which is fixedly connected to a tension detector, and one end of the tension detector is rotatably connected to a lifting ring.

[0009] Furthermore, the electromagnetic rod is magnetically connected to the metal base.

[0010] Furthermore, the charge controller is electrically connected to both conductive lines.

[0011] Furthermore, the lifting ring is suspended from the hook.

[0012] Furthermore, two limiting grooves are formed on the outer surface of the gravity block, and the gravity block is movably connected to two limiting slide rods through the limiting grooves.

[0013] The beneficial effects of this invention are as follows: During operation, a fixed weight of gravity blocks is first placed on a limiting slide bar. Several gravity blocks can be used for counterweight. Simultaneously, the charge controller is turned on to energize the electromagnetic coil through a conductive wire. Since the electromagnetic coil is wound around an electromagnetic rod, the electromagnetic rod generates a magnetic attraction force. Then, the drone body is moved by controlling the drone body to be hooked onto a lifting ring via a hook. When the drone body is driven upward, it pulls a tension detector through the lifting ring. The tension detector lifts the magnetically connected electromagnetic rod. During the lifting process, the tension detector can detect the magnitude of the tension force. Finally, the charge controller can increase or decrease the charge of the electromagnetic coil, which controls the magnitude of the magnetic attraction force of the electromagnetic rod, thereby adjusting the size of the drone body being lifted. When the drone body is detached from the electromagnetic rod, it is at its maximum load capacity. The structure is reasonable, facilitating the testing of the drone body's maximum load capacity and making adjustment and testing convenient. Attached Figure Description

[0014] To more clearly illustrate the technical solution of this utility model, the drawings used in the description of the specific embodiments will be briefly introduced below. Obviously, the drawings described below are only some embodiments of this utility model. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0015] Figure 1 : A schematic diagram of the structure of the unmanned aerial vehicle (UAV) payload capacity testing device described in this utility model;

[0016] Figure 2 : A schematic diagram of the connection between the gravity traction seat and the electromagnetic rod of this utility model;

[0017] Figure 3 : A schematic diagram of the connection between the gravity block and the limiting slide rod of this utility model.

[0018] The attached figures are labeled as follows:

[0019] 1. Unmanned aerial vehicle (UAV) fuselage; 11. Hook;

[0020] 2. Gravity traction seat; 21. Limiting slide bar;

[0021] 3. Charge controller;

[0022] 4. Gravity block; 41. Limiting groove;

[0023] 5. Electromagnetic rod; 51. Support plate; 52. Electromagnetic coil; 521. Conductive wire;

[0024] 6. Metal base; 61. Tension detector; 62. Hanging ring. Detailed Implementation

[0025] The technical solutions of the present utility model will be clearly and completely described below with reference to the accompanying drawings of the embodiments. Obviously, the described embodiments are only some embodiments of the present utility model, and not all embodiments. Based on the embodiments of the present utility model, all other embodiments obtained by those skilled in the art without creative effort are within the protection scope of the present utility model.

[0026] like Figure 1-3 As shown, the present invention has the following specific embodiments.

[0027] Example:

[0028] A drone payload capacity testing device includes a drone body 1, with a hook 11 fixedly connected to the bottom of the drone body 1, and also includes:

[0029] Gravity traction seat 2, two limiting slide rods 21 are fixedly connected to the gravity traction seat 2, a gravity block 4 is sleeved on the limiting slide rod 21, and a charge controller 3 is fixedly connected to one side of the gravity traction seat 2.

[0030] Electromagnetic rod 5, with an electromagnetic coil 52 fixedly wound on its outer surface. Both ends of the electromagnetic coil 52 are fixedly connected to conductive wires 521. The electromagnetic rod 5 is fixedly connected to the gravity traction seat 2 through two support plates 51.

[0031] A metal base 6 is fixedly connected to a tension detector 61, and a lifting ring 62 is rotatably connected to one end of the tension detector 61.

[0032] Specifically, the electromagnetic rod 5 is magnetically connected to the metal base 6, and the electromagnetic rod 5 can connect and hoist the metal base 6.

[0033] Specifically, the charge controller 3 is electrically connected to both conductive lines 521.

[0034] Specifically, the lifting ring 62 is suspended and connected to the hook 11, which facilitates the lifting of the lifting ring 62 by the UAV body 1 through the hook 11.

[0035] Specifically, two limiting grooves 41 are provided on the outer surface of the gravity block 4, and the gravity block 4 is movably connected to the two limiting slide rods 21 through the limiting grooves 41. The limiting grooves 41 enable the gravity block 4 to be limited and connected to the limiting slide rods 21.

[0036] The working principle of this utility model:

[0037] When using the device, first, a fixed-weight gravity block 4 is placed on the limiting slide bar 21. Several gravity blocks 4 can be used for counterweighting. Simultaneously, the charge controller 3 is turned on, energizing the electromagnetic coil 52 via the conductive wire 521. Since the electromagnetic coil 52 is wound around the electromagnetic rod 5, the electromagnetic rod 5 generates a magnetic attraction force. Then, the drone body 1 is moved by controlling the drone body 1, causing it to be hooked onto the lifting ring 62 via the hook 11. When the drone body 1 is driven upwards, the lifting ring 62 pulls the drone body 1, causing a pulling force detection. The tensile detector 61 is used for lifting via six pairs of magnetically connected electromagnetic rods 5. During the lifting process, the tensile detector 61 can detect the magnitude of the tensile force. Finally, the charge controller 3 can increase or decrease the charge of the electromagnetic coil 52, which can control the magnitude of the magnetic attraction of the electromagnetic rods 5, thereby adjusting the size of the drone body 1 to be lifted. When the drone body 1 is detached from the electromagnetic rods 5, the drone body 1 is at its maximum load value. The structure is reasonable, which facilitates testing the maximum load of the drone body 1 and makes adjustment and testing convenient.

[0038] The preferred embodiments of this utility model disclosed above are merely illustrative of the present utility model. These preferred embodiments do not exhaustively describe all details, nor do they limit the utility model to any specific implementation. Clearly, many modifications and variations can be made based on the content of this specification. This specification selects and specifically describes these embodiments to better explain the principles and practical applications of this utility model, thereby enabling those skilled in the art to better understand and utilize it. This utility model is limited only by the claims and their full scope and equivalents.

Claims

1. A device for testing the payload capacity of a drone, comprising a drone body (1), characterized in that, The bottom of the UAV body (1) is fixedly connected to a hook (11), and also includes: Gravity traction seat (2), two limiting slide rods (21) are fixedly connected to the gravity traction seat (2), a gravity block (4) is sleeved on the limiting slide rod (21), and a charge controller (3) is fixedly connected to one side of the gravity traction seat (2); Electromagnetic rod (5), an electromagnetic coil (52) is fixedly wound on the outer surface of the electromagnetic rod (5), and conductive wires (521) are fixedly connected to both ends of the electromagnetic coil (52). The electromagnetic rod (5) is fixedly connected to the gravity traction seat (2) through two support plates (51). A metal base (6) is fixedly connected to the top of the metal base (6), and a lifting ring (62) is rotatably connected to one end of the tension detector (61).

2. The unmanned aerial vehicle (UAV) payload capacity testing device according to claim 1, characterized in that: The electromagnetic rod (5) is magnetically connected to the metal base (6).

3. The unmanned aerial vehicle (UAV) payload capacity testing device according to claim 1, characterized in that: The charge controller (3) is electrically connected to both conductive lines (521).

4. The unmanned aerial vehicle (UAV) payload capacity testing device according to claim 1, characterized in that: The lifting ring (62) is suspended from the hook (11).

5. The unmanned aerial vehicle (UAV) payload capacity testing device according to claim 1, characterized in that: Two limiting grooves (41) are provided on the outer surface of the gravity block (4), and the gravity block (4) is movably connected to two limiting slide rods (21) through the limiting grooves (41).

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