Abrasion test bench for propeller carbon brush of large unmanned aerial vehicle

Abstract

The utility model discloses a large unmanned aerial vehicle propeller carbon brush wear test bench, which relates to the technical field of carbon brush wear tests and specifically comprises a structural frame, a direct-current power supply, a conductive slip ring assembly, a carbon brush fixing assembly, a load box, a servo controller, a temperature measuring assembly and a fan assembly. The large-scale unmanned aerial vehicle carbon brush wear test bench supports adjustment and measurement of parameters such as contact pressure, movement rotation speed, temperature and current, and obtains related test data for carbon brush wear influence factor analysis and life estimation; according to the utility model, through the adjustable and controllable design of various influence factors of carbon brush wear, the authenticity of test data is improved, the test cost is greatly reduced, and the problems that the influence factors of carbon brush wear are not perfectly mastered and the service life is not accurately estimated in the prior art can be effectively solved; the test bed is clear in scheme, low in manufacturing cost, simple and clear in operation process, low in requirement for technical ability of users and high in practicability.

Description

Technical Field

[0001] This utility model relates to the field of carbon brush wear testing technology, specifically a carbon brush wear testing bench for large unmanned aerial vehicle propellers. Background Technology

[0002] With the development of the low-altitude economy, large drones are experiencing explosive growth and have been widely used in typical scenarios such as cargo transportation, forest fire prevention, emergency rescue, weather modification, and maritime management. As a result, the requirements for the safety and maintenance costs of drones are becoming increasingly stringent.

[0003] Currently, most large drones use piston engines paired with propellers for power. Carbon brushes are key components for propeller control and communication transmission. As they are used, they will wear down. When the wear reaches a certain level, it will affect propeller control and may even cause drone safety accidents.

[0004] Currently, carbon brush maintenance is mainly achieved through regular replacement. However, upon inspection, the carbon brushes that were previously replaced were far from reaching their service life, resulting in a significant waste of resources. Furthermore, frequent disassembly and maintenance work can affect the uptime and maintenance costs of large drones.

[0005] To improve carbon brush utilization, identify the influencing factors of carbon brush wear, and thus correct carbon brush replacement conditions, a large-scale UAV carbon brush wear test bench was designed. Summary of the Invention

[0006] Traditional methods involve theoretical data analysis or experiments with real drones. However, theoretical data analysis does not incorporate different operating conditions, resulting in data that lacks universality and practicality. Real drone experiments are costly, complex to operate, and carry certain safety risks.

[0007] To overcome the shortcomings of existing technologies, this utility model provides a large-scale UAV carbon brush wear test bench that supports the adjustment and measurement of parameters such as contact pressure, rotation speed, temperature, and current, thus solving the problems of incomplete understanding of the influencing factors of carbon brush wear and inaccurate lifespan prediction.

[0008] The technical solution adopted by this utility model to solve the above problems is:

[0009] A large-scale UAV carbon brush wear test bench includes a structural frame, a DC power supply, a conductive slip ring assembly, a carbon brush fixing assembly, a load box, a servo controller, a temperature measurement assembly, and a fan assembly.

[0010] The structural frame is the main structure of the test bench, used to support the relevant test components.

[0011] The DC power supply provides the power required for the test bench.

[0012] The conductive slip ring assembly includes a slip ring disk, a rotating shaft, a servo motor, a perforated coupling, a slip ring conductive ring, and three support bases. The output shaft of the servo motor rotates, driving the slip ring disk to rotate through the perforated coupling. The three support bases respectively support both sides of the slip ring conductive ring and the output side of the servo motor. The slip ring disk is equipped with three conductive slip rings, consistent with the slip ring disk of a large UAV propeller.

[0013] The carbon brush fixing assembly includes two mounting brackets, a three-dimensional adjustment component, a three-dimensional force sensor, a carbon brush assembly, and two carbon brush supports. The mounting brackets are used to connect the carbon brush fixing assembly and the structural frame. The three-dimensional adjustment component can be adjusted in three dimensions (front-back, up-down, left-right) through three adjustment knobs. The carbon brush assembly includes a carbon brush support and a carbon brush head. The carbon brush head is replaceable as a test object.

[0014] The load box, DC power supply, carbon brush assembly, slip ring disk, slip ring, and slip ring conductive ring form a closed loop, and the loop current is controlled by adjusting the load box parameters.

[0015] The servo controller is connected to the structural frame via a snap-fit ​​mechanism and is used to control the output speed of the servo motor.

[0016] The temperature measurement component is connected to the structural frame via connecting lugs and is used to measure the temperature of the carbon brush head.

[0017] The fan assembly is connected to the structural frame via a fan bracket and is used to blow away carbon dust generated by the carbon brush head due to wear, preventing it from accumulating.

[0018] As a preferred technical solution, the structural frame is a cuboid aluminum profile frame with mounting grooves.

[0019] As a preferred technical solution, the three support brackets respectively support both sides of the slip ring conductive ring and the output side of the servo motor.

[0020] As a preferred technical solution, the two mounting brackets of the carbon brush fixing assembly are respectively connected to the upper frame and the side frame of the structural frame.

[0021] As a preferred technical solution, the carbon brush assembly is connected to a three-dimensional force sensor through two carbon brush supports, providing sufficient operating space for replacing the carbon brush head.

[0022] As a preferred technical solution, the three-dimensional adjustment component uses three adjustment knobs to achieve three-dimensional position adjustment, which can adapt to the relative installation position requirements of carbon brushes of propellers of different large UAVs.

[0023] As a preferred technical solution, the temperature measuring component is positioned directly above the contact point between the carbon brush head and the slip ring disk.

[0024] As a preferred technical solution, the fan assembly is located on the side of the contact point between the carbon brush head and the slip ring disk.

[0025] As a preferred technical solution, the slip ring conductive ring is selected from commercially available mature shelf products to avoid the wires being twisted during rotation.

[0026] As a preferred technical solution, the DC power supply is a commercially available, mature product with an output voltage of 24V and an output current adjustable from 0A to 10A.

[0027] As a preferred technical solution, the load box uses a mature racking product available on the market, and the circuit current can be adjusted from 0A to 10A.

[0028] Compared with the prior art, this utility model has the following advantages:

[0029] (1) The present invention allows for the adjustment of the speed of the slip ring disk, enabling constant speed testing under different speed conditions;

[0030] (2) The present invention has an adjustable circuit current to realize constant current test under different current conditions;

[0031] (3) This utility model can measure the carbon brush contact pressure in real time and obtain the pressure value under different test conditions;

[0032] (4) This utility model can record the contact temperature in real time and obtain temperature values ​​under different test conditions;

[0033] (5) The components of this utility model are easy to disassemble and assemble, and the installation position is adjustable, which can adapt to the test requirements of multiple scenarios;

[0034] (6) This utility model has a simple and reliable structure, low manufacturing cost, simple and clear operation process, low technical requirements for users, good safety effect, and strong practicality. Attached Figure Description

[0035] Figure 1 This is a schematic diagram of the overall structure of this utility model;

[0036] Figure 2 This is a schematic diagram of the conductive slip ring assembly structure of this utility model;

[0037] Figure 3 This is a schematic diagram of the carbon brush fixing assembly of this utility model;

[0038] Figure 4 This is a schematic diagram of the three-dimensional adjustment component structure of this utility model;

[0039] Figure 5 This is a schematic diagram of the carbon brush assembly structure of this utility model;

[0040] Figure 6 This is a schematic diagram of the temperature measurement component structure of this utility model;

[0041] Figure 7 This is a schematic diagram of the fan assembly structure of this utility model.

[0042] The attached diagram shows the following components and their corresponding names: 1. Structural frame, 2. DC power supply, 3. Conductive slip ring assembly, 4. Carbon brush fixing assembly, 5. Load cell, 6. Servo controller, 7. Temperature measurement assembly, 8. Fan assembly, 31. Slip ring disc, 32. Rotary shaft, 33. Servo motor, 34. Plum blossom coupling, 35. Slip ring conductive ring, 36. Support A, 37. Support B, 38. Support C, 41. Mounting bracket A, 42. Mounting bracket B, 43. Three-dimensional adjustment assembly, 44. Three-dimensional force sensor, 45. Carbon brush assembly, 46. Carbon brush bracket A, 47. Carbon brush bracket B, 71. Temperature sensor, 72. Connecting lug, 81. Fan, 82. Fan bracket, 431. Front and rear adjustment knob, 432. Up and down adjustment knob, 433. Left and right adjustment knob, 434. Adjustment block, 451. Carbon brush bracket, 452. Carbon brush head. Detailed Implementation

[0043] The present invention will be further described in detail below with reference to the embodiments and accompanying drawings, but the implementation of the present invention is not limited thereto.

[0044] Example

[0045] like Figures 1 to 7 As shown, this utility model can be implemented using the following specific scheme:

[0046] (I) Components and positional relationships of the device:

[0047] a) Overall composition:

[0048] like Figure 1 As shown, the test bench consists of a structural frame 1, a DC power supply 2, a conductive slip ring assembly 3, a carbon brush fixing assembly 4, a load box 5, a servo controller 6, a temperature measurement assembly 7, and a fan assembly 8.

[0049] b) The conductive slip ring assembly 3 consists of:

[0050] like Figure 2 As shown, the conductive slip ring assembly 3 consists of a slip ring disk 31, a rotating shaft 32, a servo motor 33, a plum blossom coupling 34, a slip ring conductive ring 35, an A support 36, a B support 37, and a C support 38.

[0051] c) The carbon brush fixing assembly consists of 4 components:

[0052] like Figure 3As shown, the carbon brush fixing assembly 4 consists of an A mounting bracket 41, a B mounting bracket 42, a three-dimensional adjustment assembly 43, a three-dimensional force sensor 44, a carbon brush assembly 45, an A carbon brush bracket 46, and a B carbon brush bracket 47.

[0053] like Figure 4 As shown, the three-dimensional adjustment component 43 consists of a front-to-back adjustment knob 431, a vertical adjustment knob 432, a horizontal adjustment knob 433, and an adjustment block 434.

[0054] like Figure 5 As shown, the carbon brush assembly 45 consists of a carbon brush support 451 and a carbon brush head 452.

[0055] The three-dimensional position of the carbon brush assembly 45 can be adjusted by rotating the front-back adjustment knob 431, the up-down adjustment knob 432, and the left-right adjustment knob 433.

[0056] d) Composition of temperature measurement component 7:

[0057] like Figure 6 As shown, the temperature measurement component 7 consists of a temperature sensor 71 and a connecting ear 72.

[0058] e) Fan assembly 8 consists of:

[0059] like Figure 7 As shown, the fan assembly 8 consists of a fan 81 and a fan bracket 82.

[0060] f) Connection relationship

[0061] Mechanical connection:

[0062] like Figure 1 As shown, the DC power supply 2 is bolted to the structural frame 1 through its own mounting holes; the conductive slip ring assembly 3 is bolted to the structural frame 1 through support brackets A 36, B 237, and C 338; the carbon brush fixing assembly 4 is bolted to the upper frame of the structural frame 1 through mounting bracket A 41 and to the side frame of the structural frame 1 through mounting bracket B 42; the load box 5 is bolted to the structural frame 1 through its own mounting holes; the servo controller 6 is bolted to the structural frame 1 through its own mounting holes; the temperature measurement assembly 7 is bolted to the structural frame 1 through connecting lugs 72; and the fan assembly 8 is bolted to the structural frame 1 through a fan bracket 82.

[0063] like Figure 2 As shown, the slip ring disk 31, rotating shaft 32, servo motor 33, plum blossom coupling 34 and slip ring conductive ring 35 are coaxially connected; the A support 36 and B support 37 are arranged on both sides of the slip ring conductive ring 35, and the C support 38 is arranged at the output end of the servo motor 33.

[0064] like Figure 3 As shown, the three-dimensional force sensor 44 is screwed to the three-dimensional adjustment component 43; the B carbon brush bracket 47 is screwed to the three-dimensional force sensor 44; the A carbon brush bracket 46 is screwed to the B carbon brush bracket 47; and the carbon brush assembly 45 is screwed to the A carbon brush bracket 46.

[0065] like Figure 4 As shown, the front-to-back adjustment knob 431, the up-to-down adjustment knob 432, and the left-to-right adjustment knob 433 are all connected to the adjustment block 434 via lead screws.

[0066] Electrical connection: The DC power supply 2, load box 5, slip ring disk 31, slip ring conductive ring 35 and carbon brush assembly 45 are connected by cables to form a current loop.

[0067] (II) Work Process:

[0068] When conducting a wear test on the carbon brushes of a large UAV propeller, follow these steps:

[0069] 1) Step 1: Record the initial data of the carbon brush head 452, including length and weight;

[0070] 2) Step 2: Install the three carbon brush heads 452 onto the carbon brush holder 451, and then onto the A carbon brush bracket 46;

[0071] 3) Step 3: Rotate the front-back adjustment knob 431, the up-down adjustment knob 432 and the left-right adjustment knob 433 to adjust the three-dimensional position of the carbon brush head 422 until it contacts and aligns with the three conductive slip rings of the slip ring disk 31.

[0072] 4) Step 4: Turn on the power switch of load cell 5;

[0073] 5) Step 5: Turn on DC power supply 2 and adjust the power supply to 24V regulated output;

[0074] 6) Step 6: Connect the power supply to fan 81 and start it running;

[0075] 7) Step 7: Adjust the relevant parameters of the servo controller 6 according to the test requirements to make the servo motor 33 start running and drive the slip ring disk 31 to rotate;

[0076] 8) Step 8: Adjust the parameters of load box 5 according to the test requirements to control the loop current;

[0077] 9) Step 9: Conduct wear tests according to the test requirements, and record the relevant test data and the data after the carbon brush head 452 is worn.

[0078] The large UAV propeller carbon brush wear test bench includes a structural frame 1, a DC power supply 2, a conductive slip ring assembly 3, a carbon brush fixing assembly 4, a load box 5, a servo controller 6, a temperature measurement assembly 7, and a fan assembly 8.

[0079] The structural frame 1 is the main structure of the test bench, used to support the relevant test components.

[0080] The DC power supply 2 provides the power required for the test bench.

[0081] The conductive slip ring assembly 3 includes a slip ring disk 31, a rotating shaft 32, a servo motor 33, a perforated coupling 34, a slip ring conductive ring 35, and three support bases 37, 38, and 39. The output shaft of the servo motor 33 rotates, and then drives the slip ring disk 31 to rotate through the perforated coupling 34. The slip ring disk 31 is provided with three conductive slip rings, which are consistent with the slip rings of large UAV propellers.

[0082] The carbon brush fixing assembly 4 includes two mounting brackets 41 and 42, a three-dimensional adjustment assembly 43, a three-dimensional force sensor 44, a carbon brush assembly 45, and two carbon brush supports 46 and 47. The two mounting brackets 41 and 42 are used to connect the carbon brush fixing assembly 4 and the structural frame 1. The three-dimensional adjustment assembly 43 can be adjusted in three dimensions (front-back, up-down, left-right) through three adjustment knobs 431, 432, and 433. The carbon brush assembly 45 includes a carbon brush support 451 and a carbon brush head 452. The carbon brush head 452 is replaceable as a test object.

[0083] The load box 5, DC power supply 2, carbon brush assembly 45, slip ring disk 31 slip ring, and slip ring conductive ring 35 form a closed loop, and the loop current is controlled by adjusting the parameters of the load box 5.

[0084] The servo controller 6 is connected to the structural frame 1 via a snap-fit ​​and is used to control the output speed of the servo motor 33.

[0085] The temperature measuring component 7 is connected to the structural frame 1 via the connecting ear 72 and is used to measure the temperature of the carbon brush head 452.

[0086] The fan assembly 8 is connected to the structural frame 1 via the fan bracket 82 and is used to blow away carbon powder generated by the carbon brush head 452 due to wear, so as to avoid accumulation.

[0087] Preferably, the structural frame 1 is a cuboid frame with mounting slots.

[0088] Preferably, the three support brackets 36, 37, and 38 respectively support both sides of the slip ring conductive ring 35 and the output side of the servo motor 33.

[0089] Preferably, the two mounting brackets 41 and 42 of the carbon brush fixing assembly 4 are connected to the upper frame and side frame of the structural frame 1, respectively.

[0090] Preferably, the carbon brush assembly 45 is connected to the three-dimensional force sensor 44 via two carbon brush supports 46 and 47, providing sufficient operating space for replacing the carbon brush head 452.

[0091] Preferably, the three-dimensional adjustment component 43 is adjusted in three dimensions by three adjustment knobs 431, 432, and 433, which can be adapted to the relative installation position requirements of carbon brushes of propellers of different large UAVs.

[0092] Preferably, the temperature measuring component 7 is positioned directly above the contact point between the carbon brush head 452 and the slip ring disk 31.

[0093] Preferably, the fan assembly 8 is located on the side of the contact point between the carbon brush head 452 and the slip ring disk 31.

[0094] Preferably, the slip ring conductive ring 35 is a commercially available shelf product to avoid the wires being twisted during rotation.

[0095] Preferably, the DC power supply 2 is a commercially available, mature product with an output voltage of 24V and an output current adjustable from 0A to 10A.

[0096] Preferably, the load box 5 is a commercially available mature shelving product, and the circuit current can be adjusted from 0A to 10A.

[0097] To address the existing problems of incomplete understanding of factors affecting carbon brush wear and inaccurate lifespan prediction, this invention designs a large-scale UAV carbon brush wear test bench that supports the measurement of parameters such as contact pressure, rotational speed, temperature, and current, and obtains relevant test data for carbon brush wear influencing factor analysis and lifespan prediction.

[0098] Traditional methods involve theoretical data analysis or experiments with real drones. However, theoretical data analysis does not incorporate different operating conditions, resulting in data that lacks universality and practicality. Real drone experiments are costly, complex to operate, and carry certain safety risks.

[0099] This invention improves the authenticity of experimental data and significantly reduces experimental costs through an adjustable and controllable design of multiple influencing factors. The experimental setup is clearly designed, inexpensive to manufacture, has a simple and straightforward operation process, requires minimal technical skills from users, and is highly practical.

[0100] As described above, this utility model can be implemented well.

[0101] The above description is merely a preferred embodiment of the present utility model and is not intended to limit the present utility model in any way. Any simple modifications, equivalent substitutions, and improvements made to the above embodiments based on the technical essence of the present utility model and within the spirit and principles of the present utility model shall still fall within the protection scope of the present utility model.

Claims

1. A large unmanned aerial vehicle propeller carbon brush wear test bench, characterized in that, Including structural frame (1), DC power supply (2), conductive slip ring assembly (3), carbon brush fixing assembly (4), load box (5), servo controller (6), temperature measurement assembly (7) and fan assembly (8); The structural frame (1) is the main structure of the test bench for bearing other components.

2. The large unmanned aerial vehicle propeller carbon brush wear test bench according to claim 1, characterized in that, The conductive slip ring assembly (3) is composed of slip ring disc (31), rotating shaft (32), servo motor (33), plum blossom coupling (34), slip ring conductive ring (35), A support seat (36), B support seat (37) and C support seat (38), the output shaft of the servo motor (33) rotates and can drive the slip ring disc (31) to rotate through the plum blossom coupling (34).

3. The large unmanned aerial vehicle propeller carbon brush wear test bench according to claim 2, characterized in that, The slip ring disc (31) is provided with three conductive slip rings.

4. The large unmanned aerial vehicle propeller carbon brush wear test bench according to claim 2, characterized in that, The carbon brush fixing assembly (4) is composed of A mounting bracket (41), B mounting bracket (42), three-dimensional adjustment assembly (43), three-dimensional force sensor (44), carbon brush assembly (45), A carbon brush bracket (46) and B carbon brush bracket (47), the three-dimensional adjustment assembly (43) can realize the front and rear, up and down, left and right three-dimensional position adjustment of the carbon brush assembly (45).

5. The large unmanned aircraft propeller carbon brush wear test bench according to claim 4, characterized in that, The carbon brush assembly (45) is composed of carbon brush support (451) and carbon brush head (452), and the carbon brush head (452) can be replaced.

6. The large unmanned aircraft propeller carbon brush wear test bench according to claim 4, characterized in that, The load box (5) is connected with the DC power supply (2), the slip ring of the slip ring disc (31) and the slip ring conductive ring (35) through cables to form a closed loop, and the loop current control can be realized by adjusting the load box (5) parameters.

7. The large unmanned aerial vehicle propeller carbon brush wear test bench according to claim 4, characterized in that, The carbon brush assembly (45) is connected with the A carbon brush bracket (46), the three-dimensional force sensor (44) is connected with the B carbon brush bracket (47), and the A carbon brush bracket (46) and the B carbon brush bracket (47) are reserved enough operation space to support the disassembly and assembly of the carbon brush assembly (45).

8. The large unmanned aerial vehicle propeller carbon brush wear test bench according to claim 1, characterized in that, The structural frame (1) is a rectangular cuboid frame with mounting grooves.

9. The large unmanned aerial vehicle propeller carbon brush wear test bench according to claim 5, characterized in that, The temperature measurement assembly (7) is arranged directly above the contact point between the carbon brush head (452) and the slip ring disc (31).

10. The large unmanned aircraft propeller carbon brush wear test bench according to claim 5, characterized in that, The fan assembly (8) is arranged directly on the side of the contact point between the carbon brush head (452) and the slip ring disc (31).

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