Multi-rotor unmanned aerial vehicle power test mechanism

Abstract

The utility model relates to the technical field of unmanned aerial vehicle power detection equipment, in particular to a multi-rotor unmanned aerial vehicle power test mechanism. The multi-rotor unmanned aerial vehicle power testing mechanism comprises a supporting bottom plate, a fixed stand column, a clamping assembly, a counterweight device and a sensor assembly. A plurality of fixed stand columns are arranged, and the plurality of fixed stand columns are uniformly distributed above the supporting bottom plate; the clamping assembly is installed above the fixed stand column and used for clamping an arm of the multi-rotor unmanned aerial vehicle. The counterweight device is mounted on the supporting bottom plate; the sensor assembly is installed on the supporting bottom plate. According to the lifting force of different aircrafts, appropriate counterweight devices are selected and fixed to the two sides of the supporting bottom plate, the arms of the multi-rotor unmanned aerial vehicle are placed on the clamping bases, then the clamping assemblies are buckled in sequence, and it is ensured that the unmanned aerial vehicle is not loosened. Therefore, the unmanned aerial vehicle can be ensured not to rise, topple and other accidents during testing, and the actual performance of each power assembly in a normal working state can be accurately tested.

Description

A multi-rotor unmanned aerial vehicle (UAV) power testing mechanism Technical Field

[0001] This utility model relates to the field of unmanned aerial vehicle (UAV) power testing equipment, and in particular to a power testing mechanism for multi-rotor UAVs. Background Technology

[0002] With the continuous advancement of technology, multi-rotor drones have been widely used in agriculture, industry, urban construction, emergency rescue, and other fields. Multi-rotor drones generate lift and control force directly from their wings, enabling vertical takeoff and landing, hovering, and complex flight maneuvers, making them suitable for use on multiple platforms and in various spaces. However, for multi-rotor drones, a power system failure during use can cause almost irreparable damage, making power performance testing of drones particularly important.

[0003] However, the current equipment for testing the power of drones is quite complex, and it cannot guarantee that the drone will not experience unexpected situations such as rising or tipping over during testing. Summary of the Invention

[0004] The purpose of this utility model is to provide a multi-rotor drone power testing mechanism that can ensure that the drone will not experience accidents such as ascent or tipping over during testing, and can accurately measure the actual performance of each power component under normal working conditions.

[0005] This utility model provides a power testing mechanism for a multi-rotor unmanned aerial vehicle, including a supporting base plate, a fixed column, a clamping assembly, a counterweight device, and a sensor assembly;

[0006] Multiple fixed columns are provided, and several fixed columns are evenly distributed above the supporting base plate;

[0007] The clamping assembly is installed above the fixed column and is used to clamp the arm of the multi-rotor UAV;

[0008] The counterweight device is installed on the support base plate;

[0009] The sensor assembly is mounted on the support base plate.

[0010] Preferably, the clamping assembly includes a clamping base and a clamping pressure cap;

[0011] One side of the clamping base and one side of the clamping cover are connected by a movable hinge.

[0012] More preferably, a quick-release latch is installed on the other side of the clamping base.

[0013] More preferably, the clamping base includes a base buffer block;

[0014] The clamping base has a rectangular groove on its inner side, which is used to hold the base buffer block.

[0015] More preferably, the clamping cap includes a cap buffer block;

[0016] The inner side of the clamping cover is provided with a rectangular groove, which is used to hold the cover buffer block.

[0017] Preferably, the counterweight device is bolted to the support base plate.

[0018] More preferably, trapezoidal through holes are provided on both sides of the counterweight device;

[0019] The bottom of the counterweight device is provided with a U-shaped groove, which is engaged with the support base plate.

[0020] Preferably, the multi-rotor UAV power testing mechanism further includes a bending handle;

[0021] The bending handle is mounted on the support base plate, and the two ends of the bending handle are mounted on both sides of the counterweight device.

[0022] Preferably, the support base plate has a square hole at its center.

[0023] Preferably, the fixed column is provided with multiple triangular holes.

[0024] Beneficial effects:

[0025] The technical solution of this utility model selects appropriate counterweight devices based on the lift of different models, fixes them on both sides of the support base plate, places the multi-rotor drone arms on the clamping base, and then sequentially fastens the clamping components to ensure that the drone is not loose. This not only ensures that the drone will not experience accidents such as ascent or tipping during testing, but also accurately measures the actual performance of each power component under normal operating conditions. Attached Figure Description

[0026] To more clearly illustrate the specific embodiments of this utility model or the technical solutions in the prior art, the drawings used in the description of the specific embodiments or the prior art will be briefly introduced below. Obviously, the drawings described below are some embodiments of this utility model. For those skilled in the art, other drawings can be obtained from these drawings without creative effort.

[0027] Figure 1 is a schematic diagram of the overall structure of the multi-rotor UAV power testing mechanism of this utility model;

[0028] Figure 2 is a schematic diagram of the usage status of the multi-rotor UAV power testing mechanism in this utility model.

[0029] Explanation of reference numerals in the attached figures:

[0030] 1: Support base plate; 2: Fixed column; 3: Clamping base; 4: Clamping cover; 5: Counterweight device; 6: Base buffer block; 7: Cover buffer block; 8: Quick release lock; 9: Movable hinge; 10: Bending handle; 11: Sensor assembly. Detailed Implementation

[0031] The technical solution of this utility model will be clearly and completely described below with reference to the embodiments. Obviously, the described embodiments are only some embodiments of this utility model, not all embodiments. Based on the embodiments of this utility model, all other embodiments obtained by those skilled in the art without creative effort are within the protection scope of this utility model.

[0032] In the description of this utility model, it should be understood that the terms "center", "longitudinal", "lateral", "length", "width", "thickness", "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", "clockwise", "counterclockwise", etc., indicating the orientation or positional relationship are based on the orientation or positional relationship shown in the accompanying drawings, and are only for the convenience of describing this utility model and simplifying the description, and are not intended to indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation, and therefore should not be construed as a limitation of this utility model.

[0033] Furthermore, the terms "first" and "second" are used for descriptive purposes only and should not be construed as indicating or implying relative importance or implicitly specifying the number of indicated technical features. Thus, a feature defined as "first" or "second" may explicitly or implicitly include one or more of the stated features. In the description of this utility model, "a plurality of" means two or more, unless otherwise explicitly specified. Furthermore, the terms "installed," "connected," and "linked" should be interpreted broadly; for example, they can refer to a fixed connection, a detachable connection, or an integral connection; they can refer to a mechanical connection or an electrical connection; they can refer to a direct connection or an indirect connection through an intermediate medium; they can refer to the internal connection of two components. Those skilled in the art can understand the specific meaning of the above terms in this utility model based on the specific circumstances.

[0034] As shown in Figures 1 and 2, this utility model provides a power testing mechanism for a multi-rotor unmanned aerial vehicle (UAV), which includes a supporting base plate 1, fixed columns 2, a clamping assembly, a counterweight device 5, and a sensor assembly 11. Multiple fixed columns 2 are evenly distributed above the supporting base plate 1. The clamping assembly is installed above the fixed columns 2 for clamping the arms of the multi-rotor UAV. The counterweight device 5 and the sensor assembly 11 are installed on the supporting base plate 1.

[0035] The technical solution of this utility model selects appropriate counterweight devices 5 according to the lift of different models, and fixes them on both sides of the supporting base plate 1. The multi-rotor drone arms are placed on the clamping base 3, and then the clamping components are fastened in sequence to ensure that the drone is not loose. This not only ensures that the drone will not rise or tip over during testing, but also accurately measures the actual performance of each power component under normal working conditions.

[0036] The clamping assembly includes a clamping base 3 and a clamping cover 4, with one side of the clamping base 3 and one side of the clamping cover 4 connected by a movable hinge 9. A quick-release latch 8 is installed on the other side of the clamping base 3. The clamping base 3 includes a base buffer block 6, and a rectangular groove is provided on the inner side of the clamping base 3 for engaging the base buffer block 6. The clamping cover 4 includes a cover buffer block 7, and a rectangular groove is provided on the inner side of the clamping cover 4 for engaging the cover buffer block 7. Specifically, both the base buffer block 6 and the cover buffer block 7 are detachable and can be replaced with different specifications to accommodate the arms of different multi-rotor UAV models.

[0037] Specifically, in this embodiment, the top of the fixed column 2 is provided with three threaded holes for fixing the clamping base 3. The inner side of the clamping base 3 is provided with three countersunk holes for connecting and fixing with the fixed column 2. The bottom of the clamping base 3 is provided with a rectangular groove so that the top of the fixed column 2 can be placed in the rectangular groove.

[0038] The clamping base 3 and the clamping cover 4 are connected on one side by a movable hinge 9. Specifically, the rear side of the clamping base 3 has two threaded holes for fixing the movable hinge 9, and the rear side of the clamping cover 4 also has two threaded holes for fixing the movable hinge 9. The other side of the clamping base 3 and the clamping cover 4 are locked by a quick-release latch 8. The front side of the clamping base 3 has two threaded holes for fixing the fixing seat of the quick-release latch 8, and the top of the clamping cover 4 has two threaded holes for fixing the fixing hook of the quick-release latch 8.

[0039] The counterweight device 5 is bolted to the support base plate 1. Trapezoidal through holes are provided on both sides of the counterweight device 5, and a U-shaped groove is provided at the bottom of the counterweight device 5, which engages with the support base plate 1. Six threaded holes are provided on each of the left and right sides of the support base plate 1 for fixing the counterweight device 5. The trapezoidal through holes on both sides of the counterweight device 5 facilitate handling and placement, and the U-shaped groove at the bottom of the counterweight device 5 allows it to be snapped onto the support base plate 1, reducing its range of motion and facilitating fixation. Six captive screws are provided on the counterweight device 5 for securing it to the support base plate 1.

[0040] The multi-rotor UAV power testing mechanism also includes a bending handle 10, which is mounted on the support base plate 1. Both ends of the bending handle 10 are mounted on both sides of the counterweight device 5. Specifically, in this embodiment, the support base plate 1 has two cylindrical through holes on its left and right sides for mounting the bending handle 10.

[0041] The support base plate 1 has a square hole in its center. This square hole reduces the contact area between the support base plate 1 and the ground. The back of the support base plate 1 has a rectangular groove for placing the equipment nameplate. The front of the support base plate 1 has a rectangular groove with four threaded holes for fixing the sensor assembly 11.

[0042] Specifically, in this embodiment, as shown in Figures 1 and 2, a total of four fixed columns 2 are provided, installed at the four corners of the supporting base plate 1. Each fixed column 2 has two circular through holes at its bottom for securing it to the supporting base plate 1. Each of the four corners of the supporting base plate 1 has four threaded holes, arranged in two sets, with different distances from the center of the supporting base plate 1. The fixed columns 2 are installed by bolts passing through the circular through holes and threaded holes, allowing the fixing position of the fixed columns 2 to be adjusted according to the arm length.

[0043] The fixed column 2 has multiple triangular holes. By setting the triangular holes, the weight of the fixed column 2 can be reduced, thereby reducing the weight of the entire multi-rotor UAV power testing mechanism. Secondly, it can enhance the stress of the fixed column 2 itself, making it less prone to deformation when subjected to external forces.

[0044] The technical solution of this utility model selects appropriate counterweight devices 5 according to the lift of different models, fixes them on both sides of the supporting base plate 1, places the multi-rotor drone arms on the clamping base 3, and then sequentially fastens and locks the clamping covers 4 to ensure that the drone is not loose. This not only ensures that the drone will not experience accidents such as rising or tipping over during testing, but also accurately measures the actual performance of each power component under normal operating conditions.

[0045] Finally, it should be noted that the above embodiments are only used to illustrate the technical solutions of this utility model, and are not intended to limit it. Although the utility model has been described in detail with reference to the foregoing embodiments, those skilled in the art should understand that modifications can still be made to the technical solutions described in the foregoing embodiments, or equivalent substitutions can be made to some or all of the technical features therein. Such modifications or substitutions do not cause the essence of the corresponding technical solutions to deviate from the scope of the technical solutions of the embodiments of this utility model.

Claims

1. A power testing mechanism for a multi-rotor unmanned aerial vehicle (UAV), characterized in that, include: The system comprises a support base plate, fixed columns, a clamping assembly, a counterweight device, and a sensor assembly. Multiple fixed columns are evenly distributed above the support base plate. The clamping assembly is mounted above the fixed columns and is used to clamp the arms of the multi-rotor UAV. The counterweight device is mounted on the support base plate. The sensor assembly is mounted on the support base plate.

2. The multi-rotor UAV power testing mechanism according to claim 1, characterized in that, The clamping assembly includes a clamping base and a clamping cover; one side of the clamping base and one side of the clamping cover are connected by a movable hinge.

3. The multi-rotor UAV power testing mechanism according to claim 2, characterized in that, A quick-release latch is installed on the other side of the clamping base.

4. The multi-rotor UAV power testing mechanism according to claim 2, characterized in that, The clamping base includes a base buffer block; the inner side of the clamping base is provided with a rectangular groove, which is used to hold the base buffer block.

5. The multi-rotor UAV power testing mechanism according to claim 2, characterized in that, The clamping cover includes a cover buffer block; the inner side of the clamping cover is provided with a rectangular groove, which is used to hold the cover buffer block.

6. The multi-rotor UAV power testing mechanism according to claim 1, characterized in that, The counterweight device is bolted to the support base plate.

7. The multi-rotor UAV power testing mechanism according to claim 6, characterized in that, The counterweight device has trapezoidal through holes on both sides; the bottom of the counterweight device has a U-shaped groove, which is engaged with the support base plate.

8. The multi-rotor UAV power testing mechanism according to claim 1, characterized in that, The multi-rotor UAV power testing mechanism also includes a bending handle; the bending handle is mounted on the support base plate, and the two ends of the bending handle are mounted on both sides of the counterweight device.

9. The multi-rotor UAV power testing mechanism according to claim 1, characterized in that, The support base plate has a square hole in the center.

10. The multi-rotor UAV power testing mechanism according to claim 1, characterized in that, The fixed column is provided with multiple triangular holes.

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