Unmanned aerial vehicle propeller pull test device

Abstract

The application provides a kind of unmanned aerial vehicle propeller pull test device, it relates to unmanned aerial vehicle power test technical field, including test platform and first test mechanism, the first test mechanism includes frame body, traction mechanism, gravity center detection adjusting assembly and angle auxiliary calculation assembly;Frame body includes base frame, rotating frame, support frame and mounting bracket, motor is installed on mounting bracket, motor output shaft is used to install propeller;Traction mechanism includes positioning frame, first tension sensor assembly and first traction rope;Gravity center detection adjusting assembly is used to detect and adjust the gravity center of rotating frame and its load;Angle auxiliary calculation assembly is used to assist the deflection angle of first traction rope between horizontal and vertical direction with X-axis respectively.The propeller pull of unmanned aerial vehicle is tested by using the application, the interference of the gravity of test device itself on the measurement data of force sensor can be eliminated or reduced, at the same time, the pull direction correction can be carried out in combination with the deflection angle of first traction rope, and then the accuracy of propeller pull calculation result is improved.

Description

TECHNICAL FIELD

[0001] The present application relates to the technical field of unmanned aerial vehicle power testing, and in particular to an unmanned aerial vehicle propeller pull testing device. BACKGROUND

[0002] The propeller is one of the important components of the unmanned aerial vehicle, and the performance of the propeller directly affects the flight performance of the unmanned aerial vehicle, and the greater the pull of the propeller, the greater the maximum load value of the unmanned aerial vehicle; usually, in production, performance testing needs to be performed on the propeller of the unmanned aerial vehicle, including pull testing; the current propeller pull testing device can meet certain use requirements, but the direct traction method is usually used, and the measurement effect is poor and the measurement accuracy is not high.

[0003] For example, according to the search, the patent with the Chinese patent application number CN201720447648.2 discloses a propeller pull testing table, which comprises a base, a testing support, the testing support comprising a first lever segment and a second lever segment connected to one end of the first lever segment, both ends of the first lever segment being respectively configured as a fulcrum and a power end for the lever principle, the other end of the second lever segment being configured as a resistance end for the lever principle; the fulcrum is pivotally arranged on the base; the power end is provided with the propeller which can be actively rotated; the resistance end and the base are connected with a force sensor. The propeller pull testing table in the prior art represented by the above patent at least has the following disadvantages:

[0004] Although the lever principle is used for testing, the device itself is easily disturbed by gravity, which affects the testing of the force sensor, and when in use, the actual force direction of the contact position between the resistance end and the force sensor is uncertain, and the obtained mechanical data is unreliable. SUMMARY

[0005] The present application aims to provide an unmanned aerial vehicle propeller pull testing device to alleviate the above technical problems in the prior art.

[0006] To achieve the above-mentioned purpose, the embodiments of the present application adopt the following technical solutions:

[0007] The present application provides an unmanned aerial vehicle propeller pull testing device, which comprises a testing platform and a first testing mechanism, the first testing mechanism comprising:

[0008] The frame body comprises a base frame, a rotating frame, a support frame and a mounting frame. The base frame is fixed to the top surface of the test platform. A rotating frame shaft extending in the horizontal direction and capable of rotating relative to the base frame about its axis direction is rotatably mounted on the base frame. The bottom end of the rotating frame is fixed to the rotating frame shaft. The bottom end of the support frame is mounted on the top end of the rotating frame. The mounting frame is fixed to the top end of the support frame. A motor is mounted on the mounting frame. The output rotating shaft of the motor is used to mount the propeller to be tested. Under the working condition that the motor drives the propeller to rotate, the rotating frame can rotate relative to the base frame with the rotating frame shaft driven by the power provided by the propeller.

[0009] The traction mechanism comprises a positioning frame, a first tension sensing assembly and a first traction rope. The positioning frame is fixed to the top surface of the test platform. The first tension sensing assembly is mounted on the positioning frame. The rotating frame shaft is provided with a rotating part that rotates synchronously with the rotating frame shaft. One end of the first traction rope is fixed to the rotating part. The other end of the first traction rope is connected to the force applying end of the first tension sensing assembly, so that in the initial state, the first traction rope is straightened between the rotating frame shaft and the first tension sensing assembly. In the state that the rotating frame shaft has a rotating trend, the first traction rope has a motion trend of being wound on the rotating part of the rotating frame shaft.

[0010] The gravity center detection and adjustment assembly comprises a gravity center detection assembly and a gravity center adjustment assembly. One part of the gravity center detection assembly is mounted on the test platform and the other part is mounted on the rotating frame. The gravity center detection assembly is used to detect whether the gravity center of the rotating frame and the load on the rotating frame is located directly above the rotating center of the rotating frame in the initial state. The gravity center adjustment assembly is mounted on the rotating frame and is used to adjust the position of the gravity center of the rotating frame and the load on the rotating frame in the initial state.

[0011] The angle auxiliary calculation assembly is partially mounted on the first traction rope and the other part is mounted on the top surface of the test platform. The extension direction of the rotating frame shaft in the horizontal plane is Y direction and the direction perpendicular to the extension direction of the rotating frame shaft is X direction. The angle auxiliary calculation assembly is used to assist in calculating the deflection angle of the first traction rope with the X axis in the horizontal direction and the vertical direction, respectively.

[0012] In the test, firstly, in the initial state, the propeller to be tested is installed on the output shaft of the motor, and the gravity detection assembly in the gravity adjustment assembly detects the gravity center position of the rotating frame and the load on the rotating frame. If the gravity center position is not directly above the rotating center of the rotating frame, the gravity center position of the rotating frame and the load on the rotating frame is adjusted by the gravity adjustment assembly so that the gravity center position of the rotating frame and the load on the rotating frame is directly above the rotating center of the rotating frame, thereby avoiding gravity deviation and improving test reliability. Then, the motor is started. In the working condition of the motor driving the propeller to rotate, the rotating frame will rotate with the rotating frame shaft relative to the base frame under the driving of the power provided by the propeller. However, due to the existence of the traction mechanism, the rotation of the rotating frame shaft will be hindered. In the traction mechanism, the first traction rope has a movement trend of being wound on the rotating part of the rotating frame shaft, so that the first traction rope generates a pulling force, which acts on the first pulling force sensing assembly to measure the pulling force of the first traction rope. Then, the angle auxiliary calculation assembly provides data values of the deflection angles between the first traction rope and the horizontal direction and the vertical direction respectively to help the tester calculate the actual pulling force generated by the propeller, effectively reduce the test error, and improve the test precision. (For specific calculation methods, see the specific embodiments of the specification).

[0013] In the optional embodiment of the present embodiment, preferably, the gravity detection assembly comprises a first part and a second part.

[0014] The first part comprises a support table, a pressure sensing assembly, a longitudinal slide, a pressing block, a first spring and a second spring. The support table is installed on the top surface of the test platform in a height-adjustable manner. The pressure sensing assembly is installed on the top surface of the support table, and the pressing block is arranged directly above the pressure sensor. The longitudinal slide is longitudinally slidably installed on the support table. The pressing block is connected to the top of the longitudinal slide by the first spring, and the second spring is installed between the bottom of the longitudinal slide and the bottom surface of the support table.

[0015] The second part comprises a balance frame and a pressure piece. One end of the balance frame is fixed to the rotating frame and extends towards the side of the support table. The pressure piece is installed at the other end of the balance frame, and in the initial state, the pressure piece is arranged on the top surface of the longitudinal slide.

[0016] Further preferably, the balance frame adopts a pressure wheel frame, and the pressure piece adopts a pressure wheel.

[0017] And / or, the longitudinal slide comprises a top plate, a first longitudinal rod and a second longitudinal rod; the first longitudinal rod and the second longitudinal rod both pass through the support table and are separately arranged on both sides of the pressure sensing assembly; the top of the first longitudinal rod and the top of the second longitudinal rod are both connected with the bottom surface of the top plate, the bottom of the first longitudinal rod and the bottom of the second longitudinal rod are both provided with bottom blocks, the part of the first longitudinal rod between the bottom surface of the support table and the bottom block of the first longitudinal rod and the part of the second longitudinal rod between the bottom surface of the support table and the bottom block of the second longitudinal rod are both sleeved with the second spring; the pressing block is connected with the bottom surface of the top plate through the first spring; in the initial state, the pressure piece is arranged on the top surface of the top plate.

[0018] In the optional embodiment of the embodiment, preferably, the gravity center adjusting assembly comprises a first adjusting seat and a second adjusting seat symmetrically arranged on both sides of the rotating frame; the first adjusting seat and the second adjusting seat respectively comprise respective adjusting frames, adjusting slide rails, first counterweights and second counterweights; the adjusting slide rails are arranged inside the adjusting frames, the extending directions of the adjusting frames and the adjusting slide rails are both perpendicular to the length extending direction of the rotating frame, and along the length extending direction of the adjusting frame: the middle part of the adjusting frame is fixedly connected with the rotating frame; the first counterweight and the second counterweight are slidingly arranged on the adjusting slide rails, and the first counterweight and the second counterweight are separately arranged on both sides of the middle part of the adjusting frame.

[0019] In the optional embodiment of the embodiment, preferably, the direction perpendicular to the X direction and the Y direction in the vertical plane is the Z direction: the angle auxiliary calculation assembly comprises a first Y direction slide rail, a second Y direction slide rail, a first slide seat, a second slide seat, a first X direction adjusting rail, a second X direction adjusting rail, a first infrared distance measuring assembly, a second infrared distance measuring assembly, a first infrared reflector and a second infrared reflector;

[0020] The first Y direction slide rail and the second Y direction slide rail are separately arranged on the top surface of the test platform in the X direction and located between the positioning frame and the rotating frame shaft; the first slide seat is slidingly arranged on the first Y direction slide rail, the second slide seat is slidingly arranged on the second Y direction slide rail, the first slide seat surface is provided with the first X direction adjusting rail, the second slide seat surface is provided with the second X direction adjusting rail, the first infrared distance measuring assembly is slidingly arranged on the first X direction adjusting rail, and the second infrared distance measuring assembly is slidingly arranged on the second X direction adjusting rail; the first infrared reflector and the second infrared reflector are separately arranged on the first traction rope.

[0021] Further preferably, the top surface of the first slide seat and the top surface of the second slide seat are both provided with X direction scale lines, and / or the top surface of the test platform is provided with a Y direction reference line.

[0022] In an optional implementation of the embodiment, preferably, the bottom end of the support frame is mounted to the top end of the rotating frame through a height adjustment assembly.

[0023] Further preferably, the support frame comprises a sliding rod and an adjusting cylinder, the sliding rod being slidingly mounted inside the adjusting cylinder; the height adjustment assembly comprises a fixed knob and a threaded hole provided on the cylinder wall of the adjusting cylinder; the adjusting cylinder is mounted or fixedly connected to the top end of the rotating frame, the fixed knob being threadedly connected inside the threaded hole provided on the cylinder wall of the adjusting cylinder, for fixing the sliding rod to the adjusting cylinder; and the mounting frame is fixed to the top end of the sliding rod.

[0024] In an optional implementation of the embodiment, preferably, in the traction mechanism, a pull ring is provided on the shell of the first tension sensing assembly, and a first hook is provided on the end of the first traction rope away from the rotating frame shaft, the first hook being hooked on the pull ring.

[0025] And / or, the positioning frame adopts a positioning plate with a plate surface extending along a vertical plane, a plurality of positioning holes being provided on the positioning plate, and the shell of the first tension sensing assembly being fixed to at least one of the positioning holes through a fixing assembly.

[0026] And / or, the rotating part rotating synchronously with the rotating frame shaft adopts a rotating wheel fixedly connected to one end of the rotating frame shaft, and the end of the first traction rope away from the first tension sensing assembly is fixed to the rotating wheel.

[0027] In an optional implementation of the embodiment, preferably, the unmanned aerial vehicle propeller tension testing device further comprises a second testing mechanism, the second testing mechanism comprising a second testing guide rail, a rear frame, a front frame, a second tension sensing assembly and a second traction rope.

[0028] The second testing guide rail is horizontally provided on the top surface of the testing platform; the rear frame is fixedly connected to the second testing guide rail or the top surface of the testing platform, or the rear frame is mounted to the second testing guide rail through a friction pad; the second tension sensing assembly is mounted to the rear frame; the front frame is slidingly mounted to the second testing guide rail, and is arranged on the front side of the rear frame along the extension direction of the second testing guide rail; one end of the second traction rope is connected to the second tension sensing assembly, and the other end of the second traction rope is connected to the front frame.

[0029] The front frame top is fixed with a second support frame, the second support frame top is fixed with a second mounting frame, the second mounting frame is installed with a second motor, and the output rotating shaft of the second motor is used for installing the propeller needing to be tested. BRIEF DESCRIPTION OF DRAWINGS

[0030] In order to more clearly illustrate the specific embodiments of the present application or the technical solutions in the prior art, the drawings needed to be used in the specific embodiments or the prior art description will be briefly introduced below. Obviously, the drawings in the following description are some embodiments of the present application, and other drawings can also be obtained by those skilled in the art without creative labor on the basis of these drawings.

[0031] Figure 1 The overall structure schematic diagram of the unmanned aerial vehicle propeller pull test device provided by the embodiment of the present application is shown in the figure.

[0032] Figure 2 The overall structure schematic diagram of the unmanned aerial vehicle propeller pull test device provided by the embodiment of the present application is shown in the figure.

[0033] Figure 3 The overall structure schematic diagram of the first test mechanism in the unmanned aerial vehicle propeller pull test device provided by the embodiment of the present application is shown in the figure.

[0034] Figure 4 The overall structure schematic diagram of the gravity center detection and adjustment assembly in the unmanned aerial vehicle propeller pull test device provided by the embodiment of the present application is shown in the figure.

[0035] Figure 5 The explosion structure schematic diagram of the frame body in the unmanned aerial vehicle propeller pull test device provided by the embodiment of the present application is shown in the figure.

[0036] Figure 6 The explosion structure schematic diagram of the second test mechanism in the unmanned aerial vehicle propeller pull test device provided by the embodiment of the present application is shown in the figure.

[0037] Icon: 1-test platform; 11-X direction reference line; 12-Y direction reference line; 100-first test mechanism; 200-second test mechanism; 300-propeller; 2-frame body; 20-rotary frame shaft; 201-rotating part; 21-base frame; 22-rotary frame; 23-support frame; 230-fixing knob; 231-sliding rod; 2311-Z direction scale line; 232-adjusting cylinder; 24-mounting frame; 241-motor; 3-drawing mechanism; 31-positioning frame; 310-positioning hole; 32-first tension sensor assembly; 321-pull ring; 322-positioning stud; 323-nut part; 33-first drawing rope; 331-first hook; 4-barycenter detection assembly; 41-supporting table; 42-pressure sensor assembly; 43-longitudinal sliding frame; 431-top flat plate; 432-first longitudinal rod; 433-second longitudinal rod; 44-pressing block; 45-first spring; 46-second spring; 47-balancing frame; 48-pressure part; 5-barycenter adjusting assembly; 501-first adjusting seat; 502-second adjusting seat; 51-adjusting frame; 511-first sliding groove; 512-second sliding groove; 52-adjusting sliding rail; 521-first adjusting screw; 5211-first knob; 522-second adjusting screw; 5221-second knob; 53-first counterweight block; 54-second counterweight block; 6-angle auxiliary calculation assembly; 61-first Y direction sliding rail; 62-second Y direction sliding rail; 63-first sliding seat; 631-first X direction adjusting rail; 64-second sliding seat; 641-second X direction adjusting rail; 65-first infrared distance measuring assembly; 66-second infrared distance measuring assembly; 67-first infrared reflecting part; 68-second infrared reflecting part; 69-X direction scale line; 7-second test guide rail; 8-rear frame; 9-front frame; 10-second tension sensor assembly; 101-second drawing rope; 102-second support frame; 103-second mounting frame; 104-second motor. DETAILED DESCRIPTION

[0038] In order to make the objects, technical solutions and advantages of the embodiments of the present application clearer, the technical solutions in the embodiments of the present application will be described clearly and completely below with reference to the drawings in the embodiments of the present application. Obviously, the described embodiments are only some but not all of the embodiments of the present application. The components of the embodiments of the present application described and shown in the drawings can be arranged and designed in various different configurations.

[0039] Therefore, the following detailed description of the embodiments of the present application provided in the drawings is not intended to limit the scope of the claimed present application, but only represents selected embodiments of the present application. All other embodiments obtained by those of ordinary skill in the art based on the embodiments in the present application without creative labor are within the scope of protection of the present application.

[0040] It should be noted that similar reference numerals and letters refer to like items in the accompanying drawings, and once an item is defined in one drawing, it need not be further defined and explained in subsequent drawings.

[0041] In the description of the present application, it should be noted that the terms "upper", "lower", "vertical", "horizontal", "inner", "outer" and the like indicate the orientation or positional relationship shown in the drawings, or the orientation or positional relationship in which the product of the application is usually placed, and are only for the convenience of describing the application and simplifying the description, and do not indicate or imply that the device or element referred to must have a particular orientation, be constructed and operated in a particular orientation, and therefore cannot be understood as limiting the application. In addition, the terms "first", "second" and the like are only used to distinguish the description and cannot be understood as indicating or implying relative importance.

[0042] In addition, the terms "horizontal", "vertical" and the like do not mean that the components must be absolutely horizontal or vertical, but can be slightly inclined. For example, "horizontal" only means that it is more horizontal relative to "vertical", and does not mean that the structure must be completely horizontal, but can be slightly inclined.

[0043] In the description of the present application, it should also be noted that unless otherwise explicitly specified and limited, the terms "arrangement", "installation", "connection" should be broadly understood, for example, it can be fixedly connected, or it can be detachably connected, or integrally connected; it can be directly connected, or indirectly connected through an intermediate medium; it can be the communication between the two elements inside. For those skilled in the art, the specific meaning of the above terms in the present application can be understood according to the specific circumstances.

[0044] Some embodiments of the present application will be described in detail below with reference to the accompanying drawings. The following examples and features in the examples can be combined with each other without conflict.

[0045] The present embodiment provides a UAV propeller pull test device, referring to Figure 1 and Figure 2 The UAV propeller pull test device comprises a test platform 1 and a first test mechanism 100. The first test mechanism 100 comprises a frame 2, a traction mechanism 3, a gravity center detection and adjustment assembly, and an angle auxiliary calculation assembly. Specifically, referring to Figures 1 to 3 , and focusing on Figure 3 :

[0046] The frame body 2 comprises a base frame 21, a rotating frame 22, a support frame 23 and a mounting frame 24; the base frame 21 is fixed to the top surface of the test platform 1, the rotating frame shaft 20 extending in the horizontal direction and capable of rotating relative to the base frame 21 about its own axis direction is rotatably installed on the base frame 21, and the bottom end of the rotating frame 22 is fixed to the rotating frame shaft 20; the bottom end of the support frame 23 is installed on the top end of the rotating frame 22; the mounting frame 24 is fixed to the top end of the support frame 23; the motor 241 is installed on the mounting frame 24, and the output rotating shaft of the motor 241 is used to install the propeller 300 to be tested; under the working condition that the motor 241 drives the propeller 300 to rotate, the rotating frame 22 can rotate relative to the base frame 21 under the driving of the power provided by the propeller 300 with the rotating frame shaft 20;

[0047] The traction mechanism 3 comprises a positioning frame 31, a first tension sensing assembly 32 and a first traction rope 33; the positioning frame 31 is fixed to the top surface of the test platform 1; the first tension sensing assembly 32 is installed on the positioning frame 31; the rotating frame shaft 20 is provided with a rotating part 201 rotating synchronously with the rotating frame shaft 20, one end of the first traction rope 33 is fixed to the rotating part 201, and the other end of the first traction rope 33 is connected to the force applying end of the first tension sensing assembly 32, so that in the initial state, the first traction rope 33 is straightened between the rotating frame shaft 20 and the first tension sensing assembly 32, and in the state that the rotating frame shaft 20 has a rotating tendency, the first traction rope 33 has a tendency to be wound on the rotating part 201 of the rotating frame shaft 20;

[0048] The gravity center detection and adjustment assembly comprises a gravity center detection assembly 4 and a gravity center adjustment assembly 5; one part of the gravity center detection assembly 4 is installed on the test platform 1 and the other part is installed on the rotating frame 22, which is used to detect whether the gravity center of the rotating frame 22 and the load on the rotating frame 22 is located directly above the rotating center of the rotating frame 22 in the initial state; the gravity center adjustment assembly 5 is installed on the rotating frame 22, which is used to adjust the position of the gravity center of the rotating frame 22 and the load on the rotating frame 22 in the initial state;

[0049] The angle auxiliary calculation assembly 6 is partially installed on the first traction rope 33 and partially installed on the top surface of the test platform 1; the extension direction of the rotating frame shaft 20 in the horizontal plane is Y direction, and the extension direction perpendicular to the rotating frame shaft 20 is X direction; the angle auxiliary calculation assembly 6 is used to assist in measuring the deflection angle of the first traction rope 33 between the X direction axis in the horizontal direction and the vertical direction.

[0050] When testing, first, in the initial state, the propeller 300 to be tested is installed on the output rotating shaft of the motor 241, and the gravity center detection assembly 4 in the gravity center detection and adjustment assembly detects the gravity center position of the rotating frame 22 and the load on the rotating frame 22, if the gravity center position is not directly above the rotating center of the rotating frame 22, the gravity center position of the rotating frame 22 and the load on the rotating frame 22 is adjusted by the gravity center adjustment assembly 5 so that the gravity center position of the rotating frame 22 and the load on the rotating frame 22 is directly above the rotating center of the rotating frame 22, thereby avoiding gravity center deviation and improving test reliability; then, the motor 241 is started, and under the working condition that the motor 241 drives the propeller 300 to rotate, the rotating frame 22 will rotate with the rotating frame shaft 20 relative to the base frame 21 under the driving of the power provided by the propeller 300, but the rotation of the rotating frame shaft 20 will be hindered due to the existence of the traction mechanism 3, in the traction mechanism 3, the first traction rope 33 has a movement trend of being wound on the rotating part 201 of the rotating frame shaft 20, thereby, the first traction rope 33 generates a pulling force, the pulling force acts on the first pulling force sensing assembly 32, the pulling force of the first traction rope 33 is measured, and then the angle auxiliary calculation assembly 6 provides data values of the deflection angles between the first traction rope 33 and the horizontal direction and the vertical direction respectively to help the tester to calculate the actual pulling force generated by the propeller 300, effectively reducing test error and improving test precision; the calculation formula can be carried out according to the following formula:

[0051] A coordinate system is established, as shown in Figure 1 , the extension direction of the rotating frame shaft 20 in the horizontal plane is Y direction, the extension direction perpendicular to the rotating frame shaft 20 is X direction, and the direction perpendicular to the X direction and the Y direction in the vertical plane is Z direction, preferably, the X reference line 11 and the Y reference line 12 can be provided on the top surface of the test platform 1 for reference, and the specific calculation method is according to the following formula:

[0052] In the first test mechanism 100:

[0053] Fb=Fa*R / L;

[0054] Wherein Fa=Fn*cosA*cosB;

[0055] Therefore, Fb=Fn*cosA*cosB*R / L;

[0056] Wherein Fb is the actual pulling force generated by the propeller 300, Fa is the horizontal component of the first pulling force sensing assembly 32, Fn is the pulling force received by the first pulling force sensing assembly 32, A is the angle between the pulling force received by the first pulling force sensing assembly 32 and the X-axis in the horizontal direction, B is the angle between the pulling force received by the first pulling force sensing assembly 32 and the X-axis in the vertical direction, R is the effective radius of the rotating part 201 on the rotating shaft 20, and L is the effective distance from the propeller 300 to the rotating shaft 20. A and B are obtained by the data provided by the angle auxiliary calculation assembly 6. The rotating part 201 on the rotating shaft 20 rotates synchronously with the rotating shaft 20, and is preferably a rotating wheel fixedly connected to one end of the rotating shaft 20. The end of the first traction rope 33 away from the first pulling force sensing assembly 32 is fixed to the rotating wheel.

[0057] In summary, the test of the pulling force of the propeller of the unmanned aerial vehicle can eliminate or reduce the interference of the gravity of the test device on the measurement data of the force sensor, and the pulling force direction can be corrected in combination with the deflection angle of the first traction rope 33. The torque value is greater than the pulling force value, which can effectively reduce the test error and improve the accuracy of the actual pulling force generated by the propeller 300.

[0058] For the convenience of detecting the center of gravity, in some optional embodiments of the present embodiment, more preferably, referring to Figs. 1 to Figure 5 , especially referring to Figure 5 , the center of gravity detection assembly 4 comprises a first part and a second part. The first part comprises a support table 41, a pressure sensing assembly 42, a longitudinal slide 43, a pressing block 44, a first spring 45 and a second spring 46. The support table 41 is installed on the top surface of the test platform 1 in a height-adjustable manner. The pressure sensing assembly 42 is installed on the top surface of the support table 41, and the pressing block 44 is arranged directly above the pressure sensor. The longitudinal slide 43 is longitudinally slidably installed on the support table 41. The pressing block 44 is connected to the top of the longitudinal slide 43 through the first spring 45, and the second spring 46 is installed between the bottom of the longitudinal slide 43 and the bottom surface of the support table 41. The second part comprises a balance frame 47 and a pressure piece 48. One end of the balance frame 47 is fixed to the rotating frame 22 and extends towards the side of the support table 41, and the pressure piece 48 is installed on the other end of the balance frame 47. In the initial state, the pressure piece 48 is arranged on the top surface of the longitudinal slide 43.

[0059] More preferably, as Figure 5As shown, the longitudinal slide 43 comprises a top flat plate 431, a first longitudinal rod 432 and a second longitudinal rod 433; the first longitudinal rod 432 and the second longitudinal rod 433 both pass through the support table 41 and are separately arranged at two sides of the pressure sensor assembly 42; the top of the first longitudinal rod 432 and the top of the second longitudinal rod 433 are both connected with the bottom surface of the top flat plate 431, the bottom of the first longitudinal rod 432 and the bottom of the second longitudinal rod 433 are both provided with bottom stoppers, the part of the first longitudinal rod 432 between the bottom surface of the support table 41 and the bottom stopper of the first longitudinal rod 432 and the part of the second longitudinal rod 433 between the bottom surface of the support table 41 and the bottom stopper of the second longitudinal rod 433 are both sleeved with the second spring 46; the pressing block 44 is connected with the bottom surface of the top flat plate 431 through the first spring 45; in the initial state, the pressure piece 48 is arranged on the top surface of the top flat plate 431; when the rotating frame 22 and the gravity center position of the load on the rotating frame 22 are located right above the rotating center of the rotating frame 22, the pressure sensor assembly 42 shows 0, the gravity center adjustment condition is judged based on the detection value of the pressure sensor assembly 42, which is beneficial to the operation of completing the gravity center adjustment.

[0060] More preferably, the counterbalance frame 47 adopts a pressure wheel frame and the pressure piece 48 adopts a pressure wheel, so that when the rotating frame 22 with the rotating frame shaft 20 rotates relative to the base frame 21, the pressure wheel is pushed and pulled to roll by the counterbalance frame 47, and the action is more stable under the rolling friction.

[0061] More preferably, referring to Figures 1 to 5 , especially referring to Figure 4 and Figure 5 , the gravity center adjustment assembly 5 comprises a first adjustment seat 501 and a second adjustment seat 502 symmetrically arranged at two sides of the rotating frame 22. The first adjustment seat 501 and the second adjustment seat 502 respectively comprise respective adjustment frames 51, adjustment slide rails 52, first counterweights 53 and second counterweights 54; wherein: the adjustment slide rails 52 are arranged inside the adjustment frames 51, the extension directions of the adjustment frames 51 and the adjustment slide rails 52 are both perpendicular to the length extension direction of the rotating frame 22, and along the length extension direction of the adjustment frames 51: the middle part of the adjustment frames 51 is fixedly connected with the rotating frame 22; the first counterweights 53 and the second counterweights 54 are slidingly installed on the adjustment slide rails 52, and the first counterweights 53 and the second counterweights 54 are separately arranged at two sides of the middle part of the adjustment frames 51, the operation of completing the center adjustment is realized by adjusting the positions of the counterweights.

[0062] More specifically and preferably, as Figure 5As shown, the adjusting slide rail 52 comprises a first adjusting screw 521 and a second adjusting screw 522; the first counterweight 53 is threadedly sleeved on the outside of the first adjusting screw 521, and the second counterweight 54 is threadedly sleeved on the outside of the second adjusting screw 522; the extending directions of the adjusting frame 51, the first adjusting screw 521 and the second adjusting screw 522 are all perpendicular to the length extending direction of the rotating frame 22, and along the length extending direction of the adjusting frame 51: the middle part of the adjusting frame 51 is fixedly connected to the rotating frame 22, and on both sides of the middle part of the adjusting frame 51 are respectively provided with a first sliding groove 511 and a second sliding groove 512 extending along the length direction of the adjusting frame 51, the first adjusting screw 521 is rotatably installed in the inside of the first sliding groove 511, the second adjusting screw 522 is rotatably installed in the inside of the second sliding groove 512, and the end of the first adjusting screw 521 away from the second sliding groove 512 penetrates through the end face of the adjusting frame 51 away from the second sliding groove 512 in the length direction, and the end of the second adjusting screw 522 away from the first sliding groove 511 penetrates through the end face of the adjusting frame 51 away from the first sliding groove 511 in the length direction, a first knob 5211 is arranged on the end of the first adjusting screw 521 extending out of the first sliding groove 511, and a second knob 5221 is arranged on the end of the second adjusting screw 522 extending out of the second sliding groove 512, and meanwhile, each counterweight is connected to the inner wall of the respective sliding groove through the concave-convex guide rail extending along the length direction of the adjusting frame 51, the position of the first counterweight 53 on the first adjusting screw 521 is adjusted by rotating the first knob 5211, and the position of the second counterweight 54 on the second adjusting screw 522 is adjusted by rotating the second knob 5221, so as to complete the operation of quickly adjusting the gravity center position; it should be noted by those skilled in the art that this is only an optional embodiment of the present embodiment, and is not a limitation, and the structure and mode of each counterweight relative to the respective guide rail are not limited to this.

[0063] In addition, in the present embodiment, in order to facilitate adjustment, a scale extending along the length of the adjusting frame 51 can also be arranged on the adjusting frame 51 to assist adjustment.

[0064] In order to facilitate auxiliary measurement of the deflection angle of the first traction rope 33, in the present embodiment, it is more preferred but not limited to referring to Figure 3The angle auxiliary calculation assembly 6 comprises a first Y-direction sliding rail 61, a second Y-direction sliding rail 62, a first sliding seat 63, a second sliding seat 64, a first X-direction adjusting rail 631, a second X-direction adjusting rail 641, a first infrared distance measuring assembly 65, a second infrared distance measuring assembly 66, a first infrared reflector 67 and a second infrared reflector 68; wherein: the first Y-direction sliding rail 61 and the second Y-direction sliding rail 62 are arranged on the top surface of the test platform 1 in the X-direction and between the positioning frame 31 and the rotating frame shaft 20; the first sliding seat 63 is slidingly installed on the first Y-direction sliding rail 61, the second sliding seat 64 is slidingly installed on the second Y-direction sliding rail 62, the first X-direction adjusting rail 631 is arranged on the surface of the first sliding seat 63, the second X-direction adjusting rail 641 is arranged on the surface of the second sliding seat 64, the first infrared distance measuring assembly 65 is slidingly installed on the first X-direction adjusting rail 631, and the second infrared distance measuring assembly 66 is slidingly installed on the second X-direction adjusting rail 641; the first infrared reflector 67 and the second infrared reflector 68 are arranged on the first traction rope 33 in a spaced manner; each sliding rail can be but is not limited to a sliding groove structure, and preferably but not limited to, the top surface of the first sliding seat 63 and the top surface of the second sliding seat 64 are both provided with X-direction scale lines 69. The height of the two infrared reflectors is detected by adjusting the positions of the two sliding seats and the two infrared distance measuring assemblies, so that the height difference of the two infrared reflectors is obtained to participate in the calculation, and when the calculation is performed:

[0065] cosA=(X1-X2) / √[(X1-X2) 2 +(Y1-Y2) 2 ];

[0066] cosB=(X1-X2) / √[(X1-X2) 2 +(Z1-Z2) 2 ]

[0067] wherein X1 and X2 are the readings of the two infrared distance measuring assemblies on the X-axis in the coordinate system based on the reference line, Y1 and Y2 are the readings of the two infrared distance measuring assemblies on the Y-axis in the coordinate system based on the reference line, and Z1 and Z2 are the sensing readings of the two infrared distance measuring assemblies to the first traction rope 33.

[0068] Preferably, the X-direction reference line 11 and the Y-direction reference line 12 are arranged on the top surface of the test platform 1, and the X-direction scale lines are arranged on the top surfaces of the two sliding seats, so as to improve the reliability, quickly judge the azimuth difference of the two infrared reflectors in the horizontal and vertical directions, judge the inclination angle of the first traction rope 33 in combination with the height difference, and improve the practicability.

[0069] In addition, in the embodiment, preferably, Figure 4 and Figure 5The bottom end of the support frame 23 is installed on the top end of the rotating frame 22 through a height adjusting assembly to obtain a plurality of height data, so that the torque can be changed, and further preferably, the support frame 23 comprises a sliding rod 231 and an adjusting cylinder 232, and the sliding rod 231 is slidingly installed in the adjusting cylinder 232; the height adjusting assembly can further comprise a fixed knob 230 and a threaded hole provided on the cylinder wall of the adjusting cylinder 232; the adjusting cylinder 232 is installed or fixedly connected to the top end of the rotating frame 22, and the fixed knob 230 is threadedly connected to the threaded hole provided in the cylinder wall of the adjusting cylinder 232, for fixing the sliding rod 231 to the adjusting cylinder 232; and the mounting frame 24 is fixed to the top end of the sliding rod 231, and in order to improve the height adjusting reliability, a Z-direction scale line 2311 can be further provided on the sliding rod 231, as shown in Figure 5 .

[0070] In addition, in the traction mechanism 3 of the embodiment, preferably but not limited to: the shell of the first tension sensing assembly 32 is provided with a pull ring 321, the first traction rope 33 is provided with a first hook 331 at the end away from the rotating frame shaft 20, and the first hook 331 is hooked on the pull ring 321; and / or the positioning frame 31 adopts a positioning plate with a plate surface extending along a vertical plane, and a plurality of positioning holes 310 are provided on the positioning plate, and the shell of the first tension sensing assembly 32 is fixed to at least one positioning hole 310 through a fixing assembly, which can but not limited to comprise a positioning stud 322 fixedly connected to the rear end of the shell of the first tension sensing assembly 32 and a nut member 323 threadedly connected to the positioning stud 322 to position the positioning stud 322 passing through the positioning hole 310 on the positioning plate, and the fixed position of the first tension sensing assembly 32 is adjusted by using the plurality of positioning holes 310 and the fixing assembly. Figure 2

[0071] In addition, in some more preferred embodiments of the embodiment, the top surface of the test platform 1 is provided with a base frame mounting hole, and the base frame 21 is detachably installed in the base frame mounting hole.

[0072] In addition, in some optional embodiments of the embodiment, the unmanned aerial vehicle propeller tension test device can further comprise a second test mechanism 200, as shown in Figure 1 , Figure 2 and Figure 6 ​As shown, the second test mechanism 200 comprises a second test rail 7, a rear frame 8, a front frame 9, a second tension sensor assembly 10 and a second traction rope 101; specifically: the second test rail 7 is horizontally arranged on the top surface of the test platform; the rear frame 8 is fixedly connected to the second test rail 7 or the top surface of the test platform, or the rear frame 8 is mounted to the second test rail 7 through a friction pad. The second tension sensor assembly 10 is mounted to the rear frame 8; the front frame 9 is slidingly mounted to the second test rail 7, and along the extension direction of the second test rail 7, the front frame 9 is arranged on the front side of the rear frame 8; one end of the second traction rope 101 is connected to the second tension sensor assembly 10, and the other end of the second traction rope 101 is connected to the front frame 9, and the specific connection manner can refer to but is not limited to the end connection structure of the first traction rope 33.

[0073] In the first optional structure, as shown, Figure 6 As shown, the top of the front frame 9 is fixed with a second support frame 102, the top of the second support frame 102 is fixed with a second mounting frame 103, and the second mounting frame 103 is mounted with a second motor 104, and the output rotating shaft of the second motor 104 is used to mount the propeller 300 to be tested.

[0074] In the second optional structure, in the first test mechanism 100, the support frame 23 is fixedly mounted to the top end of the rotating frame 22 in a detachable manner, and in the second test mechanism 200, the top of the front frame 9 is provided with a support frame mounting portion for mounting the support frame 23, so that the first test mechanism 100 and the second test mechanism 200 share a set of support frame 23, rotating frame 22, mounting frame 24 and motor 241.

[0075] In these optional embodiments, the friction between the front frame 9 and the second test rail 7 is small, and the front frame 9 driven by the propeller 300 pulls the rear frame 8 to move, and then the pulling force (tension) of the propeller 300 is quickly and roughly tested according to the indication of the second tension sensor assembly 10. When the rear frame 8 is mounted to the second test rail 7 through a friction pad, the friction pad makes the rear frame 8 have a larger friction with the second test rail 7, and the friction size is affected by the number of friction pads installed. If enough friction pads are installed, the front frame 9 cannot pull the rear frame 8, and at this time the maximum tension of the propeller 300 can be measured by the second tension sensor assembly 10. The result obtained by this test is a rough test result, which can be used in cooperation with the first test mechanism 100 to meet the test needs of testers in different situations.

[0076] Finally, it should be pointed out that:

[0077] 1. In this specification, the first traction rope 33 and the second traction rope 101 should be made of a material that is not easy to be pulled and elongated, such as but not limited to a metal wire;

[0078] 2、In the specification, "and / or" indicates that the structure before "and / or" and the structure after "and / or" are set simultaneously or alternatively;

[0079] 3、The various embodiments in the specification are described in a progressive manner, and each embodiment focuses on the difference from other embodiments. The same or similar parts between the various embodiments can be referred to each other. The above embodiments in the specification are used to illustrate the technical solutions of the present application, but not to limit the present application. Although the present application has been described in detail with reference to the foregoing embodiments, it should be understood by those skilled in the art that the technical solutions recorded in the foregoing embodiments can be modified, or some or all of the technical features can be replaced by equivalents. The modification or replacement does not change the essence of the corresponding technical solution out of the scope of the technical solutions of the embodiments of the present application.

Claims

1. A drone propeller pull test device, characterized by: The utility model relates to a test platform, which comprises a test platform (1) and a first test mechanism (100), wherein the first test mechanism (100) comprises: a frame body (2) comprising a base frame (21), a rotating frame (22), a support frame (23) and a mounting frame (24); the base frame (21) is fixed to the top surface of the test platform (1); a rotating frame shaft (20) extending in the horizontal direction and capable of rotating relative to the base frame (21) about its own axis direction is rotatably installed on the base frame (21); the bottom end of the rotating frame (22) is fixed to the rotating frame shaft (20); the bottom end of the support frame (23) is mounted to the top end of the rotating frame (22); the mounting frame (24) is fixed to the top end of the support frame (23); a motor (241) is installed on the mounting frame (24); the output rotating shaft of the motor (241) is used for mounting a propeller (300) to be tested; under the working condition that the motor (241) drives the propeller (300) to rotate, the rotating frame (22) can rotate relative to the base frame (21) with the rotating frame shaft (20) driven by the power provided by the propeller (300); a traction mechanism (3) comprising a positioning frame (31), a first tension sensing assembly (32) and a first traction rope (33); the positioning frame (31) is fixed to the top surface of the test platform (1); the first tension sensing assembly (32) is mounted to the positioning frame (31); the rotating frame shaft (20) is provided with a rotating part (201) rotating synchronously with the rotating frame shaft (20); one end of the first traction rope (33) is fixed to the rotating part (201); the other end of the first traction rope (33) is connected to the force applying end of the first tension sensing assembly (32), so that the first traction rope (33) is straightened between the rotating frame shaft (20) and the first tension sensing assembly (32) in the initial state; in the state that the rotating frame shaft (20) has a rotating trend, the first traction rope (33) has a motion trend of being wound on the rotating part (201) of the rotating frame shaft (20); a gravity center detection and adjustment assembly comprising a gravity center detection assembly (4) and a gravity center adjustment assembly (5); one part of the gravity center detection assembly (4) is mounted to the test platform (1) and the other part is mounted to the rotating frame (22), which is used for detecting whether the gravity center of the rotating frame (22) and the load on the rotating frame (22) is located directly above the rotating center of the rotating frame (22) in the initial state; the gravity center adjustment assembly (5) is mounted to the rotating frame (22), which is used for adjusting the position of the gravity center of the rotating frame (22) and the load on the rotating frame (22) in the initial state. And an angle auxiliary calculation assembly (6) is installed on one part of the first traction rope (33) and on the top surface of the test platform (1), with the extension direction of the rotating frame shaft (20) in the horizontal plane as the Y direction and perpendicular to the extension direction of the rotating frame shaft (20) as the X direction, and the angle auxiliary calculation assembly (6) is used for assisting in measuring the angle between the first traction rope (33) and the X direction axis in the horizontal direction and the vertical direction respectively; The gravity detection assembly (4) comprises a first part and a second part; The first part comprises a support table (41), a pressure sensing assembly (42), a longitudinal sliding frame (43), a pressing block (44), a first spring (45) and a second spring (46); the support table (41) is installed on the top surface of the test platform (1) in a height-adjustable manner; the pressure sensing assembly (42) is installed on the top surface of the support table (41), and the pressing block (44) is arranged directly above the pressure sensing assembly (42); the longitudinal sliding frame (43) is longitudinally slidably installed on the support table (41); the pressing block (44) is connected to the top of the longitudinal sliding frame (43) through the first spring (45), and the second spring (46) is installed between the bottom of the longitudinal sliding frame (43) and the bottom surface of the support table (41); The second part comprises a balancing frame (47) and a pressure piece (48); one end of the balancing frame (47) is fixed to the rotating frame (22) and extends towards one side of the support table (41), and the pressure piece (48) is installed at the other end of the balancing frame (47), and in the initial state, the pressure piece (48) is arranged on the top surface of the longitudinal sliding frame (43).

2. The unmanned aerial vehicle propeller pull test device according to claim 1, characterized in that: The balancing frame (47) is a pressure wheel frame, and the pressure piece (48) is a pressure wheel; And / or, The longitudinal sliding frame (43) comprises a top plate (431), a first longitudinal rod (432) and a second longitudinal rod (433); The first longitudinal rod (432) and the second longitudinal rod (433) both pass through the support table (41) and are arranged on opposite sides of the pressure sensing assembly (42); the top of the first longitudinal rod (432) and the top of the second longitudinal rod (433) are connected to the bottom surface of the top plate (431), the bottom of the first longitudinal rod (432) and the bottom of the second longitudinal rod (433) are both provided with a bottom stopper, and the part of the first longitudinal rod (432) between the bottom surface of the support table (41) and the bottom stopper of the first longitudinal rod (432) and the part of the second longitudinal rod (433) between the bottom surface of the support table (41) and the bottom stopper of the second longitudinal rod (433) are respectively sleeved with the second spring (46); the pressing block (44) is connected to the bottom surface of the top plate (431) through the first spring (45); In the initial state, the pressure piece (48) is arranged on the top surface of the top plate (431).

3. The unmanned aerial vehicle propeller pull test device of claim 1, wherein: The gravity center adjusting assembly (5) comprises first adjusting seats (501) and second adjusting seats (502) symmetrically mounted on both sides of the rotating frame (22); The first adjusting seat (501) and the second adjusting seat (502) respectively comprise respective adjusting frames (51), adjusting slide rails (52), first counterweights (53) and second counterweights (54); The adjusting slide rail (52) is arranged inside the adjusting frame (51), the extending directions of the adjusting frame (51) and the adjusting slide rail (52) are both perpendicular to the length extending direction of the rotating frame (22), and along the length extending direction of the adjusting frame (51), the middle part of the adjusting frame (51) is fixedly connected to the rotating frame (22); The first counterweight (53) and the second counterweight (54) are slidingly mounted on the adjusting slide rail (52), and the first counterweight (53) and the second counterweight (54) are separately arranged on both sides of the middle part of the adjusting frame (51).

4. The unmanned aerial vehicle propeller pull test device of claim 1, wherein: A direction perpendicular to the X direction and the Y direction in a vertical plane is a Z direction: The angle auxiliary calculation assembly (6) comprises first Y direction slide rails (61), second Y direction slide rails (62), first slide seats (63), second slide seats (64), first X direction adjusting rails (631), second X direction adjusting rails (641), first infrared distance measuring assemblies (65), second infrared distance measuring assemblies (66), first infrared reflectors (67) and second infrared reflectors (68); The first Y direction slide rail (61) and the second Y direction slide rail (62) are arranged in the X direction and are separately arranged on the top surface of the test platform (1) and between the positioning frame (31) and the rotating frame shaft (20); the first slide seat (63) is slidingly mounted on the first Y direction slide rail (61), the second slide seat (64) is slidingly mounted on the second Y direction slide rail (62), the first X direction adjusting rail (631) is arranged on the surface of the first slide seat (63), the second X direction adjusting rail (641) is arranged on the surface of the second slide seat (64), the first infrared distance measuring assembly (65) is slidingly mounted on the first X direction adjusting rail (631), and the second infrared distance measuring assembly (66) is slidingly mounted on the second X direction adjusting rail (641); The first infrared reflector (67) and the second infrared reflector (68) are separately arranged on the first traction rope (33).

5. The unmanned aerial vehicle propeller pull test device of claim 4, wherein: The top surfaces of the first slide seat (63) and the second slide seat (64) are respectively provided with X direction scale lines (69), and / or the top surface of the test platform is provided with an X direction reference line (11) and a Y direction reference line (12).

6. The UAV propeller pull test device of claim 1, wherein: The bottom end of the supporting frame (23) is mounted on the top end of the rotating frame (22) through a height adjusting assembly.

7. The unmanned aerial vehicle propeller pull test device of claim 6, wherein: The supporting frame (23) comprises a slide rod (231) and an adjusting cylinder (232), and the slide rod (231) is slidingly mounted in the adjusting cylinder (232); The height adjusting assembly comprises a fixed knob (230) and a threaded hole arranged on the cylinder wall of the adjusting cylinder (232); The adjusting cylinder (232) is mounted or fixedly connected to the top end of the rotating frame (22), and the fixed knob (230) is threadedly connected to the inside of the threaded hole provided on the cylinder wall of the adjusting cylinder (232) and used for fixing the sliding rod (231) to the adjusting cylinder (232); The mounting frame (24) is fixed to the top end of the sliding rod (231).

8. The UAV propeller pull test device of claim 1, wherein: In the traction mechanism (3): A pull ring (321) is arranged on the shell of the first tension sensing assembly (32), one end of the first traction rope (33) away from the rotating frame shaft (20) is provided with a first hook (331), and the first hook (331) is hooked on the pull ring (321); And / or, the positioning frame (31) adopts a positioning plate with a plate surface extending along a vertical plane, a plurality of positioning holes (310) are arranged on the positioning plate, and the shell of the first tension sensing assembly (32) is fixed to at least one of the positioning holes (310) through a fixing assembly; And / or, the rotating part (201) rotating synchronously with the rotating frame shaft (20) on the rotating frame shaft (20) adopts a rotating wheel fixedly connected to one end of the rotating frame shaft (20), and one end of the first traction rope (33) away from the first tension sensing assembly (32) is fixed to the rotating wheel.

9. The unmanned aerial vehicle propeller pull test device of claim 1, wherein: The unmanned aerial vehicle propeller tension test device further comprises a second test mechanism (200), and the second test mechanism (200) comprises a second test guide rail (7), a rear frame (8), a front frame (9), a second tension sensing assembly (10), and a second traction rope (101). The second test guide rail (7) is horizontally arranged on the top surface of the test platform. The rear frame (8) is fixedly connected to the second test guide rail (7) or the top surface of the test platform, or the rear frame (8) is mounted on the second test guide rail (7) through a friction pad. The second tension sensing assembly (10) is mounted on the rear frame (8). The front frame (9) is slidingly mounted on the second test guide rail (7) and arranged on the front side of the rear frame (8) along the extension direction of the second test guide rail (7). One end of the second traction rope (101) is connected to the second tension sensing assembly (10), and the other end of the second traction rope (101) is connected to the front frame (9). In the first test mechanism (100), the support frame (23) is fixedly mounted on the top end of the rotating frame (22) in a detachable manner, and in the second test mechanism (200), the top of the front frame (9) is provided with a support frame mounting portion for mounting the support frame (23).

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