Dynamic balance testing device
By designing a dynamic balancing test device that includes a support structure and testing components, the problem of inaccurate data during the dynamic process of dynamic balancing testing of the flight power system of flying cars is solved, achieving higher precision dynamic balancing testing and ensuring the stability and accuracy of the system in flight.
Patent Information
- Application Number
- CN202520035016.X
- Authority / Receiving Office
- CN · China
- Patent Type
- Utility models(China)
- Current Assignee / Owner
- Filing Date
- 2025-01-07
- Publication Date
- 2025-12-19
- Estimated Expiration
- 2035-01-07
AI Technical Summary
In existing technologies, the dynamic balance testing of the flight propulsion system of flying cars relies on traditional automobile testing equipment, which cannot be tested during the dynamic process of simulated flight, resulting in inaccurate test data, large errors, and failure to achieve the ideal state.
Design a dynamic balance testing device, including a support structure and a detection component. The support structure is flexible and can simulate flight at a preset height. It detects the rotational speed and vibration signal of the propeller through photoelectric sensors and vibration sensors. The support structure can swing during flight simulation by the flight propulsion system to provide dynamic balance detection data.
It improves the accuracy of dynamic balance detection of flight propulsion systems, provides reliable data, and provides accurate parameters for dynamic balance adjustment of flight propulsion systems, ensuring the stability and precision of the system in flight.
Smart Images
Figure CN223691932U_ABST
Abstract
Description
TECHNICAL FIELD
[0001] The utility model relates to aircraft testing device technical field, especially relates to a dynamic balance testing device. BACKGROUND
[0002] The flight power system in the flying car is also called power set, and is mainly combined by propeller and motor. In the related art, the dynamic balance detection of the flight power system of the flying car still depends on the testing device of the transmission car. For example, the traditional propeller dynamic balance vibration characteristic detection is carried out in the static state, and the propeller cannot be detected in the dynamic process of simulation flight. The dynamic balance detection data is not accurate, the error is large, and the flight power system adjusted according to the detection result cannot reach the ideal state. SUMMARY
[0003] The utility model discloses a kind of dynamic balance testing devices, to improve the detection precision of the dynamic balance of flight power system in flying car.
[0004] To achieve the above object, the utility model provides a kind of dynamic balance testing device, for testing the dynamic balance of flight power system, the flight power system includes the propeller and driving motor connected, the surface of one of the propeller blades is equipped with reflective area, and the dynamic balance testing device includes:
[0005] Support structure, the support structure has oppositely arranged first end and second end, the support structure is fixed at preset height by the first end, the flight power system is fixed to the second end, the support structure has flexibility, when the flight power system simulates flight state on the support structure, the second end is the center of oscillation along the line between the first end and the second end oscillates;
[0006] Detection assembly, set on the support structure, the detection assembly includes photoelectric sensor and vibration sensor, the photoelectric sensor is used to emit light signal to the reflective area, to obtain the rotating speed signal of the propeller, and the vibration sensor is used to detect the vibration signal of the support structure.
[0007] In an embodiment of the utility model, the support structure includes:
[0008] Support arm, arranged along horizontal direction, two ends of the support arm are the first end and the second end of the support structure respectively, and the photoelectric sensor is arranged on the support arm;And
[0009] A mounting base is connected to the second end of the support arm, the flight power system is fixed in the mounting base, the vibration sensor is arranged on the mounting base, and an axis of the vibration sensor is arranged at an angle with respect to an extension direction of the support arm;
[0010] When the flight power system simulates flight, the support arm and the mounting base swing about a line between the first end and the second end as a swing center.
[0011] In an embodiment of the present application, the support structure further comprises:
[0012] A fixing member is arranged to extend in a vertical direction, and the first end of the support arm is fixed to a top region of the fixing member; and
[0013] A limiting member is fixed to a bottom region of the fixing member at one end, and the other end of the limiting member is connected to the mounting base, and the limiting member is used to limit swing of the mounting base in the vertical direction.
[0014] In an embodiment of the present application, the support arm and the mounting base are an integral structure.
[0015] In an embodiment of the present application, the length of the support arm is greater than the length of the paddle.
[0016] In an embodiment of the present application, a wiring structure is further formed on the support arm.
[0017] In an embodiment of the present application, the mounting base is provided with a mounting groove, the mounting groove comprises a groove bottom wall and a groove side wall, the groove bottom wall is provided with a plurality of mounting holes arranged at intervals, the driving motor is adapted to the groove side wall, the groove bottom wall is provided with a fixing hole matched with the mounting hole, and the driving motor is fixed in the mounting groove through cooperation of the connecting member, the mounting hole and the fixing hole.
[0018] The vibration sensor is arranged on the groove side wall of the mounting groove, and a central axis of the vibration sensor is arranged at an angle with respect to a central axis of the driving motor.
[0019] In an embodiment of the present application, a positioning structure is formed between the mounting groove and the driving motor.
[0020] In an embodiment of the present application, the light reflection area is close to a root of the paddle, and the photoelectric sensor is arranged close to the mounting base.
[0021] In an embodiment of the present application, the detection assembly further comprises a data processing unit, and the data processing unit is connected to the photoelectric sensor and the vibration sensor, respectively.
[0022] The utility model discloses technical scheme through adopting the whole flight power system is fixed on the support structure, because the first end of support structure is fixed on the preset height, can make flight power system can be in the second end of support structure simulating the state of flight. When flight power system simulates the flight state on the support structure, the second end of support structure can swing along the connecting line between the first end and the second end as the swing center, vibration sensor is used for detecting the vibration signal of whole support structure, simultaneously, photoelectric sensor for emitting light signal to the light reflection area is arranged on the support structure to obtain the rotating speed signal of propeller. In the utility model discloses technical scheme, because support structure can swing to a certain extent when flight power system simulates the flight state, namely, support structure can satisfy the structure intensity of flight power system fixation and simulating flight, and support structure can swing to a certain extent when flight power system simulates the flight, can facilitate vibration sensor to detect the vibration signal of whole flight power system under the flight state, and photoelectric sensor can also detect the rotating speed signal of blade, satisfy the parameter detection of flight power system realization dynamic balance, provide reliable data basis for the adjustment of flight power system dynamic balance. BRIEF DESCRIPTION OF DRAWINGS
[0023] In order to more clearly illustrate the technical scheme in the embodiment of the utility model or prior art, the following will briefly introduce the drawing needed to be used in the embodiment or prior art description, obviously, the drawing in the following description only some embodiments of the utility model, for ordinary skilled person in the art, under the premise of not paying creative labor, still can obtain other drawings according to the structure shown in these drawings.
[0024] Figure 1 It is structural schematic diagram of an embodiment of the dynamic balance testing device of the utility model;
[0025] Figure 2 It is Figure 1 structural exploded view;
[0026] Figure 3 It is Figure 1 top view.
[0027] Brief Description of the Drawings
[0028] Reference Name Reference Name 100 Dynamic balancing test device 30 Detection assembly 10 Support structure 31 Optoelectronic sensor 11 Support arm 33 Vibration sensor 13 Mounting seat 200 Flight power system 15 Fixing member 211 Blade 17 Limiting member 2111 Reflective area 220 Driving motor
[0029] 100, dynamic balance testing device;10, support structure;11, support arm;13, mounting seat;15, fixing piece;17, limiting piece;30, detection assembly;31, photoelectric sensor;33, vibration sensor;200, flight power system;211, blade;2111, light reflection area;220, driving motor;
[0030] The purposes, functional features and advantages of the present application will be further described with reference to the embodiments and the accompanying drawings. DETAILED DESCRIPTION
[0031] The technical solutions in the embodiments of the present application will be clearly and completely described with reference to the accompanying drawings in the embodiments of the present application. Obviously, the described embodiments are only part of the embodiments of the present application, rather than all the embodiments. Based on the embodiments in the present application, all the other embodiments obtained by those skilled in the art without creative work fall within the protection scope of the present application.
[0032] It should be noted that all the directional indications (such as up, down, left, right, front, back, etc.) in the embodiments of the present application are only used to explain the relative positional relationship, movement condition, etc. between the components in a certain specific posture (as shown in the drawings), and if the specific posture changes, the directional indications will also change accordingly.
[0033] In the present application, unless otherwise explicitly specified and limited, the terms "connection", "fixation" and the like should be understood in a broad sense, for example, "fixation" can be fixed connection, or detachable connection, or integral; can be mechanical connection, or electrical connection; can be direct connection, or indirect connection through an intermediate medium; can be the internal connection of two elements or the interaction relationship between two elements, unless otherwise explicitly limited. For those skilled in the art, the specific meanings of the above terms in the present application can be understood according to the specific circumstances.
[0034] In addition, in the present application, the description such as "first", "second" and the like is only for the purpose of description, and cannot be understood as indicating or implying the relative importance of the indicated technical features or implicitly indicating the number of the indicated technical features. Therefore, the features limited by "first" and "second" can explicitly or implicitly include at least one of the features. In addition, the meaning of "and / or" appearing throughout the text is that it includes three parallel schemes, for example, "A and / or B" includes A scheme, or B scheme, or A and B schemes. In addition, the technical solutions of each embodiment can be combined with each other, but it must be based on the realization of those skilled in the art, when the combination of technical solutions appears contradictory or unachievable, it should be considered that the combination of technical solutions does not exist, and is not within the protection scope required by the present application.
[0035] The flying power system 200 in the flying car is also called a power set, which is mainly composed of a propeller and a motor. In the related art, the dynamic balance detection of the flying power system 200 of the flying car still depends on the test device of the transmission car. For example, the conventional propeller 211 dynamic balance vibration characteristic detection is carried out in a static state, and the propeller 211 cannot be detected in a dynamic process simulating flight. Such dynamic balance detection data is not accurate, and the error is large. The flying power system 200 adjusted according to the detection result cannot achieve an ideal state.
[0036] To solve the above technical problems, the utility model provides a dynamic balance testing device 100.
[0037] With reference to Figures 1 to 3 The utility model provides a dynamic balance testing device 100 for testing the dynamic balance of the flying power system, the flying power system 200 includes the propeller and the driving motor 220 connected, the surface of one propeller blade 211 of the propeller is equipped with the reflection area 2111, the dynamic balance testing device 100 includes:
[0038] The support structure 10 has the first end (not marked in the drawing) and the second end (not marked in the drawing) arranged oppositely, the support structure 10 is fixed at the first end at a preset height, the flying power system 200 is fixed at the second end, the support structure 10 has flexibility, when the flying power system 200 simulates the flight state on the support structure 10, the second end swings along the swing center line between the first end and the second end.
[0039] The detection assembly 30 is arranged on the support structure 10, and the detection assembly 30 includes a photoelectric sensor 31 and a vibration sensor 33. The photoelectric sensor 31 is used to emit an optical signal to the reflection area 2111 to obtain a rotating speed signal of the propeller. The vibration sensor 33 is used to detect a vibration signal of the support structure 10.
[0040] The utility model discloses technical scheme is through adopting the whole flight power system 200 is fixed on the support structure 10, because the first end of support structure 10 is fixed on the preset height, can make flight power system 200 can be in the second end of support structure 10 simulation flight state.When flight power system 200 is in the simulation flight state on support structure 10, the second end of support structure 10 can swing along the connecting line between the first end and the second end as the swing center;Vibration sensor 33 is used for detecting the vibration signal of whole support structure 10, simultaneously, photoelectric sensor 31 for emitting light signal to the light reflection area 2111 is arranged on support structure 10, to obtain the rotating speed signal of propeller.The utility model discloses technical scheme, because support structure 10 can swing to a certain extent when flight power system 200 simulation flight state, namely support structure 10 can satisfy the structure strength of flight power system 200 fixation and simulation flight, simultaneously, support structure 10 can swing to a certain extent when flight power system 200 simulation flight, can facilitate vibration sensor to detect the vibration signal of whole flight power system 200 under the flight state, simultaneously, photoelectric sensor 31 can also detect the rotating speed signal of blade 211, satisfies the parameter detection of flight power system 200 realization dynamic balance, provides reliable data basis for the adjustment of flight power system 200 dynamic balance.
[0041] Support structure 10 can be fixed on the test frame, also can be fixed on the wall, still can be fixed on other vertical carrier, as long as can satisfy the strength that flight power system 200 simulation flight bears just can.The preset height is the height that satisfies flight power system 200 simulation flight state, here does not limit the specific numerical value of height to limit.
[0042] The flexibility of support structure 10 is that the material of support structure 10 can bear greater bending or distortion without breaking.In the application technical scheme, support structure 10 should satisfy the requirement that it can swing along the extension direction of support arm 11 under the premise of satisfying the rigidity of fixing flight power system 200.It should be noted that support structure 10 is driven greatly when flight power system 200 simulation flight state, forces the second end (free end) of support structure 10 to twist constantly and produce vibration.The material of support structure 10 can be stainless steel, titanium alloy, aluminum alloy and the like.
[0043] In the technical scheme of the embodiment of the utility model, the overall dynamic balance of the flight power system 200 in the flight state needs to consider various factors, for example, on the one hand, the mass imbalance of the whole flight power system 200 needs to be considered, the mass imbalance needs to be detected and adjusted, on the other hand, the deviation caused by the angle of the blade 211 under different rotating speeds also needs to be considered, and the mass distribution unevenness of the motor and the blade 211 in the manufacturing and assembling process needs to be accurately detected, and is corrected through a suitable method, so that the centrifugal force deviation caused by the mass imbalance is reduced, and the deviation caused by the angle of the blade 211 under different rotating speeds can be detected and adjusted only in the process of simulating flight through the continuously changing rotating speed.
[0044] In the technical scheme of the embodiment of the utility model, the photoelectric sensor 31 can be a laser sensor, uses laser as a light source, has high precision, and can accurately detect the rotating speed of the blade 211. When the blade 211 rotates, the light change reflected by the light reflection area 2111 is captured by the laser sensor and is converted into an electric signal and is transmitted to the data processing unit in real time, and rotating speed data support is provided for dynamic balance analysis. When the vibration sensor 33 works, the internal components can convert the vibration signal into an electric signal and transmit it to the data processing unit according to the electromagnetic induction principle, and vibration data support is provided for dynamic balance analysis.
[0045] In the technical scheme of the embodiment of the utility model, the supporting mode of the supporting structure 10 to the flight power system 200 combines the advantages of hard support and soft support, compared with the traditional hard support, the application scheme can be better combined with the whole machine mode, the test precision is improved and the adaptability to different working conditions is improved, compared with the traditional soft support, the application scheme has stronger bearing capacity, can effectively bear the lift and vibration caused by the rotation of the blade 211 and the motor, and is suitable for the flight car power system which has a certain weight and high precision requirement for dynamic balance test. In the application, the flight power system 200 is fixed at a preset height through the supporting structure 10, so that the flight power system 200 can be tested in the simulated flight state, the rotating speed signal and the vibration signal can be more accurately detected, the test precision is greatly improved, the imbalance problem of the flight power system 200 can be more accurately found, reliable data is provided for adjustment, and the stability of the whole flight power system 200 can be ensured.
[0046] In an embodiment of the utility model, the light reflection area 2111 is close to the root of the paddle 211, and the photoelectric sensor 31 is arranged close to the mounting base 13. In the technical scheme of an embodiment of the utility model, the light reflection area 2111 can be a light reflection coating, or a light reflection strip, a light reflection sheet or the like structure. The mass of the light reflection strip or the light reflection sheet needs to be as light as possible to reduce the mass imbalance of the propeller caused by the light reflection strip. The light reflection area 2111 is arranged at the root of the paddle 211 as far as possible, so that the photoelectric sensor 31 can detect the rotating speed signal, and the light reflection strip can also be arranged in the middle region of the paddle 211 or the tail region of the paddle 211 to avoid the mass imbalance caused by the test requirement.
[0047] In an embodiment of the utility model, the detection assembly 30 further comprises a data processing unit, and the data processing unit is connected with the photoelectric sensor 31 and the vibration sensor 33 respectively. In an embodiment of the utility model, the connection between the data processing unit and the photoelectric sensor 31 and the vibration sensor 33 can be wireless connection, wired connection or the like. The data processing unit receives the data obtained by the photoelectric sensor 31 and the vibration sensor 33, and accurately analyzes and processes the data to obtain the accurate data of the mass imbalance of the entire flight power system 200. It can be understood that the data processing unit can be arranged on the support structure 10, or arranged on the outer side of the support structure 10, as long as the data processing unit can receive the signals transmitted by the detection assembly 30.
[0048] Referring to Figures 1 to 3 In an embodiment of the utility model, the support structure 10 comprises a support arm 11 and a mounting base 13, the support arm 11 is arranged along the horizontal direction, two ends of the support arm 11 are the first end and the second end of the support structure 10 respectively, and the photoelectric sensor 31 is arranged on the support arm 11; the mounting base 13 is connected to the second end of the support arm 11, the flight power system 200 is fixed in the mounting base 13, the vibration sensor 33 is arranged on the mounting base 13, and the axis of the vibration sensor 33 is arranged at an angle with the extension direction of the support arm 11;
[0049] When the flight power system 200 simulates flight, the support arm 11 and the mounting base 13 swing along the line between the first end and the second end as the swing center.
[0050] In the technical scheme of the embodiment of the utility model, support structure 10 with the actual arm mechanism of flying car is similar, in the testing process, the flight state can be simulated more truly, so that more accurate test data is obtained. The material of support arm 11 can be steel or other materials meeting the requirements, the length of support arm 11 should be slightly longer than the length of propeller blade 211, so that the safety of propeller in the process of simulating flight can be ensured. The cross section of support arm 11 can be square or circular, as long as the shape can meet the strength and rigidity and flexibility requirements, which are not limited here.
[0051] The line between the first end and the second end of support arm 11 is also the length direction of support arm 11, when flying power system 200 simulates flight, the outer circumferential vibration of support arm 11 in the length direction
[0052] A fixing groove is further formed on the second end of support arm 11, and photoelectric sensor 31 is fixed in the fixing groove, the fixing groove can improve the fixing efficiency of photoelectric sensor 31, and can also make the position of photoelectric sensor 31 reliable, avoid the movement of photoelectric sensor 31, and improve the testing accuracy.
[0053] Mounting seat 13 is used for mounting and fixing flying power system 200, the mounting of mounting seat 13 can improve the reliability of fixing flying power system 200, and can also improve the convenience of connecting flying power system 200 and dynamic balance testing device 100, at the same time, mounting seat 13 also provides an installation carrier for vibration sensor 33, so that vibration sensor 33 can be as close as possible to flying power system 200, and can more accurately detect the vibration signal generated by the whole flying power system 200, so as to provide more accurate data basis for the dynamic balance of flying power system 200.
[0054] In the technical scheme of the embodiment of the utility model, support arm 11 and mounting seat 13 can be a split structure, so that support arm 11 and mounting seat 13 can be respectively machined and formed, and the machining difficulty of support structure 10 can be simplified. Of course, in the technical scheme of another embodiment of the utility model, support arm 11 and mounting seat 13 can also be an integral structure, so that the assembly process between support arm 11 and mounting seat 13 can be reduced, the error between support arm 11 and mounting seat 13 due to assembly can be reduced, and the interference of the error on testing can be avoided; at the same time, support arm 11 and mounting seat 13 are an integral structure, and the overall strength of support structure 10 can be ensured.
[0055] Please refer to Figures 1 to 3 In an embodiment of the utility model, the support structure 10 further comprises:
[0056] A fixing member 15 is arranged in a vertical direction, and the first end of the support arm 11 is fixed to the top region of the fixing member 15.
[0057] A limiting member 17 is fixed to the bottom region of the fixing member 15 at one end, and the other end of the limiting member 17 is connected to the mounting seat 13, and the limiting member 17 is used to limit the swing of the mounting seat 13 in the vertical direction.
[0058] In the technical scheme of one embodiment of the utility model, the fixing member 15 is in a plate structure and is arranged in a vertical direction, the fixing member 15 is perpendicular to the support arm 11, and the support arm 11 and the fixing member 15 can be detachably connected or can be connected as an integral structure by welding, thereby improving the structural strength between the fixing member 15 and the support arm 11, which is not limited herein. When the support structure 10 is fixed, the entire fixing member 15 can be attached to the surface of the fixed object, so that the contact area between the support structure 10 and the fixed object can be increased, thereby improving the reliability of the support structure 10.
[0059] In one embodiment of the utility model, the limiting member 17 is also in a plate structure, one end of the limiting member 17 is fixed to the bottom region of the support arm 11, and the support arm 11 is supported from the bottom. The limiting member 17, the fixing member 15 and the support arm 11 form a triangle, and the stability of the triangle is used to improve the stability of the entire support structure 10. The limiting member 17 is connected to the mounting seat 13, thereby supporting the mounting seat 13, and the mounting seat 13 and the support arm 11 are limited from moving up and down in the vertical direction when the flight motion system 200 simulates flight, so as to ensure that the entire support structure 10 can be kept swinging in the horizontal direction as much as possible.
[0060] Referring to Figures 1 to 3 In one embodiment of the utility model, a wiring structure is further formed on the support arm 11.
[0061] In the technical scheme of one embodiment of the utility model, the wiring structure formed on the support arm 11 can fix the power line and / or the signal line, so that the wiring is neat, the wires are prevented from being disorderly arranged, and the neatness of the surface of the dynamic balance testing device 100 is improved. The wiring structure can be a wire passing groove (not shown in the figure) formed on the surface of the support arm 11, or a fixing buckle or other structure arranged on the surface of the support arm 11, and the specific form of the wiring structure is not limited herein.
[0062] In an embodiment of the utility model, the mounting seat 13 is equipped with mounting groove (not shown in the drawing), the mounting groove includes groove bottom wall (not show in the drawing) and groove lateral wall (not show in the drawing), the groove bottom wall is equipped with a plurality of interval arrangement's mounting hole (not show in the drawing), the drive motor 220 is also with the groove lateral wall adaptation, the groove bottom wall is equipped with with the mounting hole cooperation's fixed hole (not show in the drawing), the drive motor 220 is fixed in the mounting groove through the cooperation of connecting piece and the mounting hole and the fixed hole, the vibration sensor 33 is arranged in the groove lateral wall of the mounting groove, and the central axis of vibration sensor 33 is also set up with the central axis of drive motor 220 angle.
[0063] In the technical scheme of an embodiment of the utility model, the shape of the mounting groove is adapted to the housing of the drive motor 220. The drive motor 220 includes a bearing seat (not shown in the drawing), and the flight power system 200 is installed inside the mounting groove through the bearing seat. The mounting groove is provided with mounting holes (not shown in the drawing), and the entire flight power system is locked and fixed on the mounting seat 13 through the cooperation of connecting pieces, mounting holes and the bearing seat. Usually, the connecting pieces are screws, which can also be a combination of screws and nuts. In an embodiment of the utility model, a positioning structure is formed between the mounting groove and the drive motor 220.
[0064] In the embodiment, the positioning structure (not shown in the drawing) can be a positioning column (not shown in the drawing) and a positioning groove (not shown in the drawing) formed between the mounting groove and the drive motor 220, or a positioning protrusion and a positioning notch, etc. The positioning structure is set to improve the assembly and alignment efficiency between the mounting groove and the drive motor 220. The above description is only a preferred embodiment of the utility model, and does not limit the patent scope of the utility model. Any equivalent structural transformation or direct / indirect application in other related technical fields based on the invention concept of the utility model, the contents of the utility model specification and drawings are included in the patent protection scope of the utility model.
Claims
1. A dynamic balancing testing device for testing the dynamic balance of a flight propulsion system, the flight propulsion system comprising a propeller and a drive motor connected together, wherein one blade of the propeller has a reflective area on its surface, characterized in that, The dynamic balancing testing device includes: A support structure having a first end and a second end disposed opposite to each other. The support structure is fixed at a preset height via the first end, and the flight propulsion system is fixed to the second end. The support structure is flexible, and when the flight propulsion system simulates flight on the support structure, the second end swings along the line connecting the first end and the second end as the swing center. A detection component is disposed on the support structure. The detection component includes a photoelectric sensor and a vibration sensor. The photoelectric sensor is used to emit a light signal to the reflective area to obtain the rotational speed signal of the propeller. The vibration sensor is used to detect the vibration signal of the support structure.
2. The dynamic balancing testing device as described in claim 1, characterized in that, The supporting structure includes: A support arm, arranged horizontally, has two ends, namely the first end and the second end of the support structure, respectively, and the photoelectric sensor is disposed on the support arm; and Mounting base, the mounting base is connected to the second end of the support arm, the flight power system is fixed in the mounting base, the vibration sensor is disposed in the mounting base, and the axis of the vibration sensor is set at an angle to the extension direction of the support arm; When the flight propulsion system simulates flight, the support arm and the mounting base swing along the line connecting the first end and the second end as the swing center.
3. The dynamic balancing testing device as described in claim 2, characterized in that, The support structure also includes: A fixing member extending vertically, wherein the first end of the support arm is fixed to the top region of the fixing member; and A limiting member is provided, one end of which is fixed to the bottom area of the fixing member, and the other end of which is connected to the mounting base. The limiting member is used to restrict the vertical swing of the mounting base.
4. The dynamic balancing testing device as described in claim 2, characterized in that, The support arm and the mounting base are an integral structure.
5. The dynamic balancing testing device as described in claim 2, characterized in that, The length of the support arm is greater than the length of the blade.
6. The dynamic balancing testing device as described in claim 2, characterized in that, A wiring structure is also formed on the support arm.
7. The dynamic balancing testing device as described in claim 2, characterized in that, The mounting base is provided with a mounting groove, which includes a bottom wall and a side wall. The bottom wall is provided with a plurality of spaced mounting holes. The drive motor is also adapted to the side wall. The bottom wall is provided with a fixing hole that mates with the mounting holes. The drive motor is fixed to the mounting groove by means of a connector that mates with the mounting holes and the fixing holes. The vibration sensor is disposed on the side wall of the mounting groove, and the central axis of the vibration sensor is also set at an angle to the central axis of the drive motor.
8. The dynamic balancing testing device as described in claim 7, characterized in that, A positioning structure is formed between the mounting slot and the drive motor.
9. The dynamic balancing testing device as described in claim 2, characterized in that, The reflective area is located near the root of the blade, and the photoelectric sensor is located near the mounting base.
10. The dynamic balancing testing apparatus according to any one of claims 1 to 9, characterized in that, The detection component also includes a data processing unit, which is connected to the photoelectric sensor and the vibration sensor respectively.