A device for testing the deflection angle of an aircraft rudder

Abstract

The application relates to the technical field of rudder testing, and discloses a device for testing the deflection angle of an aircraft rudder, which comprises a shell, a wing plate, a first rack and a second rack. One side of the shell is provided with an air outlet, the wing plate is vertically arranged in the air outlet, the other side of the shell is fixedly provided with a main air pipe, the upper end of the shell is fixedly connected with a mounting rack, the mounting rack is connected with a measuring mechanism, the measuring mechanism is used for testing the change of the mechanical deflection angle of the rudder when the wing plate is subjected to wind, and the influence of the mechanical gap on the mechanical deflection angle of the rudder can be tested under the condition of no wind. A spoiler mechanism is arranged in the shell, and the spoiler mechanism is used for providing crosswind to act on both sides of the wing plate during the testing. The device for testing the deflection angle of the aircraft rudder can simulate various working conditions of different wind directions, test the control ability of the rudder to the mechanical deflection angle under complex airflow conditions, and quickly test the influence of the gap existing in the transmission mechanism of the rudder on the mechanical deflection angle.

Description

Technical Field

[0001] This invention relates to the field of servo testing technology, specifically to a device for testing the deflection angle of aircraft servos. Background Technology

[0002] Aircraft servo motors typically consist of a drive system, a transmission system, rudder blades, and a control system. The transmission system is a high-precision servo system. Its control system controls the motor to rotate, causing the rudder blades to deflect and thus changing the aircraft's flight direction. In aerospace applications, the operating conditions of aircraft servo motors are quite complex. For example, high transmission precision is required when changing direction frequently, good vibration stability is required when the transmission speed is relatively high, and small size, light weight, and high reliability are required when the load-to-mass ratio is relatively large. However, the transmission mechanism itself has mechanical backlash, and large loads or overloads can cause the backlash to increase. Due to the existence of backlash, the precision of the transmission system and the precision of the control system are directly affected. The transmission mechanism has a large load-to-mass ratio and limited component rigidity, so the elastic deformation of the components will also reduce the precision of the transmission system.

[0003] Currently, the technical method used to test the transmission accuracy of servo motors is to fix the servo motor on a mechanical deflection angle testing device under no-load conditions. The electrical zero position and mechanical zero position of the servo motor are required to be consistent. The tester inputs control signals of different angles to each servo motor and reads the corresponding mechanical deflection angle of the servo motor in sequence to ensure that it meets the requirements and load capacity.

[0004] The aforementioned existing technologies clearly have significant shortcomings. Although the tester can input control signals at different angles to the servo motor, it is not suitable for testing the impact of airflow from different wind directions on the transmission system. Furthermore, it cannot quickly test the impact of the clearance inherent in the servo motor transmission mechanism on its mechanical deflection angle. Summary of the Invention

[0005] (a) Technical problems to be solved To address the shortcomings of existing technologies, this invention provides a device for testing the deflection angle of aircraft servo motors. This device can simulate various wind directions, test the servo motor's control capability for mechanical deflection angle under complex airflow conditions, and quickly test the impact of clearances in the servo motor transmission mechanism on the mechanical deflection angle. This solves the problems of traditional testing equipment being unsuitable for testing the impact of airflow from different wind directions on the transmission system and unable to quickly test the impact of clearances in the servo motor transmission mechanism on the mechanical deflection angle.

[0006] (II) Technical Solution To achieve the above objectives, the present invention provides the following technical solution: a device for testing the deflection angle of an aircraft servo motor, comprising a housing, a wing plate, a first frame, and a second frame. An air outlet is provided on one side of the housing, and the wing plate is vertically arranged inside the air outlet. A main air duct is fixed on the other side of the housing, and a mounting frame is fixedly connected to the upper end of the housing. A measuring mechanism is connected to the mounting frame. The measuring mechanism is used to test the change of the mechanical deflection angle of the servo motor when the wingplate is exposed to wind, and can also test the influence of mechanical clearance on the mechanical deflection angle of the servo motor under windless conditions. The housing is equipped with a turbulence mechanism, which is used to provide crosswinds on both sides of the wingplate during testing, so that the wingplate is in airflows of different directions to test the stability of the servo when adjusting the deflection angle.

[0007] Preferably, the inner walls of the upper and lower ends of the housing are respectively rotatably connected to a rotating shaft and a connecting shaft via rolling bearings, and the opposite ends of the rotating shaft and the connecting shaft are fixedly connected to the wing plate by bolts; A fixing ring is connected to the shaft wall of the rotating shaft. One side of the fixing ring is connected to the measuring mechanism, and a pointer is fixedly connected to the other side of the fixing ring. A vibration sensor is fixedly connected to the pointer. A dial that cooperates with the pointer is fixedly connected to the side wall of the mounting bracket.

[0008] Preferably, the measuring mechanism includes a connecting frame connected to a fixed ring, a half-tooth ring fixedly connected to one end of the connecting frame, a gear meshing on the inner side of the half-tooth ring, a gear shaft fixedly connected to the upper end of the gear, a mounting plate and a cross plate fixedly connected to the upper end of the mounting frame through multiple columns, and the gear shaft rotatably connected to the side wall of the mounting plate through roller bearings. The upper end of the horizontal plate is connected to a transmission mechanism, which is connected to a gear shaft to drive a half-gear ring.

[0009] Preferably, the transmission mechanism includes an electromagnet and a permanent magnet. The permanent magnet is fixed to the upper end of the horizontal plate. A strip-shaped through hole is opened at the upper end of the horizontal plate. A connecting block is provided in the strip-shaped through hole. One end of the connecting block is fixedly connected to the lower end of the electromagnet. A slide block is fixedly connected to the lower end of the horizontal plate. A slide bar is slidably connected to the slide block. A rack is fixedly connected to one side of the slide bar. The rack meshes with a gear shaft.

[0010] Preferably, the turbulence mechanism includes a three-way pipe and two inclined guide plates. The two guide plates are symmetrically fixed inside the housing. A box is fixedly connected to one side of each guide plate. An exhaust port is provided on the side wall of the box. The exhaust port is inclined towards the wing plate. Two conduits are fixedly connected to the three-way pipe. The ends of the two conduits away from the three-way pipe pass through the side wall of the housing and are fixedly connected to one side of the guide plate. One side of the conduit passes through the guide plate and is fixedly connected to one side of the box. A first fan is fixedly connected to the first frame, and the exhaust end of the first fan is fixedly connected to a tee pipe through a first threaded pipe.

[0011] Preferably, a drive shaft is rotatably connected inside the housing via a needle roller bearing, and the side wall of the housing is rotatably connected to the shaft wall of the drive shaft via a sealed bearing. A flow guiding assembly is provided inside the housing and is fixed to the shaft wall of the drive shaft. An adjusting motor is fixedly connected to the mounting bracket, and the output end of the adjusting motor is fixedly connected to the upper end of the drive shaft.

[0012] Preferably, the flow guiding assembly consists of two inclined flow guiding plates, both of which are fixed to the shaft wall of the drive shaft.

[0013] Preferably, one end of the box body is provided with two exhaust sections, which are distributed in a V-shape and located on both sides of the wing plate. One end of each exhaust section is provided with an elbow, and the exhaust port is opened at the elbow. A first wind speed sensor is fixedly connected to the elbow.

[0014] Preferably, a second fan is fixedly connected to the first frame, and the exhaust end of the second fan is fixedly connected to one end of the main air duct through a second threaded pipe. A second wind speed sensor is fixedly connected to one side of the housing, and the second wind speed sensor is located at the inlet of the main air duct.

[0015] Preferably, a servo motor mounting base is fixedly connected to the upper end of the housing, and the second frame is fixed to the lower end of the housing.

[0016] (III) Beneficial Effects Compared with the prior art, the present invention provides a device for testing the deflection angle of an aircraft servo motor, which has the following advantages: 1. When using this invention, first install the servo motor body, and connect the servo motor body to the tester so that it drives the rotating shaft to make the pointer point to the "0" mark on the dial. Then, under windless conditions, use a measuring mechanism to test the mechanical clearance of the servo motor body. Then, generate airflow by working the first and second fans to simulate various working conditions and test the control accuracy and stability of the servo motor body.

[0017] 2. The measuring mechanism provided in this invention, when measuring the mechanical clearance of an aircraft servo, first uses a testing instrument to control the servo body to zero the pointer, then activates the electromagnet. The electromagnet generates a magnetic attraction force with the permanent magnet, which in turn causes the connecting block to move the rack. The rack's movement rotates the gear shaft, which in turn rotates the gear, causing the half-gear ring to rotate. This rotation of the half-gear ring then rotates the connecting frame, causing the rotating shaft to rotate. The torque generated by the rotating shaft acts on the output end of the servo body, and simultaneously, the angle pointed to by the pointer on the rotating shaft changes. This value is recorded. Then, the direction of the electromagnet's magnetic poles is changed, generating a magnetic repulsion force between it and the permanent magnet. The measuring mechanism then drives the rotating shaft to rotate in the opposite direction, causing the pointer angle to change in the opposite direction. This value is also recorded. Finally, the two recorded values ​​are added together, and the final value is the mechanical deflection angle value caused by the servo's mechanical clearance. During the formal simulation test, the power to the electromagnet is disconnected, allowing the testing device to be in a natural, unforced state. Simultaneously, the pointer and dial work together to read the changes in the servo's mechanical deflection angle throughout the entire test process.

[0018] 3. The turbulence mechanism provided in this invention guides the airflow to both sides of the wingplate through two exhaust sections during use. The oscillation of the turbulence component can change the direction of the airflow, so that the airflow speed and flow rate acting on the side of the wingplate can be arbitrarily adjusted. This allows the airflow to be coordinated with the airflow delivered by the main air duct to simulate a more natural airflow, which is convenient for testing the control accuracy and stability of the aircraft's servo motor under complex working conditions. Attached Figure Description

[0019] Figure 1 This is a schematic diagram of a device for testing the deflection angle of an aircraft servo motor, as proposed in this invention. Figure 2 This is a cross-sectional view of the housing in a device for testing the deflection angle of an aircraft servo motor, as proposed in this invention. Figure 3 This is a cross-sectional view of the housing in a device for testing the deflection angle of an aircraft servo motor, as proposed in this invention. Figure 4 This invention provides a schematic diagram of the measuring mechanism in a device for testing the deflection angle of an aircraft servo motor. Figure 1 ; Figure 5 This invention provides a schematic diagram of the measuring mechanism in a device for testing the deflection angle of an aircraft servo motor. Figure 2 ; Figure 6 This invention provides a schematic diagram of the measuring mechanism in a device for testing the deflection angle of an aircraft servo motor. Figure 3 ; Figure 7 This invention proposes a device for testing the deflection angle of an aircraft servo motor. Figure 5 Cross-sectional view of the middle horizontal plate and the mounting plate; Figure 8 This invention proposes a device for testing the deflection angle of an aircraft servo motor. Figure 5 Schematic diagram of the structure of the middle horizontal plate and the mounting plate; Figure 9 This invention proposes a device for testing the deflection angle of an aircraft servo motor. Figure 4 A schematic diagram of the structure of the pointer, shaft, and half-tooth ring.

[0020] In the diagram: 1. Shell; 2. Wing plate; 3. Mounting bracket; 4. Servo body; 5. Servo mounting base; 6. Adjustment motor; 7. Duct; 8. Second fan; 9. First fan; 10. T-joint; 11. First frame; 12. Second frame; 13. Guide plate; 14. Drive shaft; 15. Rotating shaft; 16. Main air duct; 17. Box body; 18. First wind speed sensor; 19. Guide plate; 20. Exhaust section; 21. Elbow; 22. Exhaust port; 23. Vibration sensor; 24. Dial; 25. Pointer; 26. Connecting bracket; 27. Half gear ring; 28. Mounting plate; 29. ​​Permanent magnet; 30. Horizontal plate; 31. Electromagnet; 32. Second wind speed sensor; 33. Slide; 34. Rack; 35. Gear; 36. Slide bar; 37. Gear shaft. Detailed Implementation

[0021] The technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of the present invention, and not all embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of the present invention.

[0022] Example 1: See attached document Figure 1-9A device for testing the deflection angle of an aircraft servo motor includes a housing 1, a wing plate 2, a first frame 11, and a second frame 12. An air outlet is provided on one side of the housing 1, and the wing plate 2 is vertically installed inside the air outlet. The inner walls of the upper and lower ends of the housing 1 are respectively rotatably connected to a rotating shaft 15 and a connecting shaft via rolling bearings. The opposite ends of the rotating shaft 15 and the connecting shaft are fixedly connected to the wing plate 2 by bolts. A fixing ring is connected to the shaft wall of the rotating shaft 15. One side of the fixing ring is connected to a measuring mechanism, and the other side of the fixing ring is fixedly connected to a pointer 25, on which a vibration sensor 23 is fixedly connected. A dial 24 cooperating with the pointer 25 is fixedly connected to the side wall of the mounting frame 3. A main air duct 16 is fixedly fixed to the other side of the housing 1. The upper end of the housing 1 is fixedly connected to the mounting frame 3, and a measuring mechanism is connected to the mounting frame 3. The measuring mechanism is used to test the change in the mechanical deflection angle of the servo motor when the wing plate 2 is exposed to wind, and can also test the influence of mechanical clearance on the mechanical deflection angle of the servo motor under windless conditions. The housing 1 is equipped with a turbulence mechanism, which is used to provide crosswinds on both sides of the wing plate 2 during testing, so that the wing plate 2 is in the airflow of different directions to test the stability of the servo when adjusting the deflection angle. A second fan 8 is fixedly connected to the first frame 11. The exhaust end of the second fan 8 is fixedly connected to one end of the main air duct 16 through a second threaded pipe. A second wind speed sensor 32 is fixedly connected to one side of the housing 1. The second wind speed sensor 32 is located at the pipe opening of the main air duct 16. A servo mounting base 5 is fixedly connected to the upper end of the housing 1. The servo body 4 to be tested is fixedly installed through the servo mounting base 5. The output end of the servo body 4 is coaxially connected to the upper end of the rotating shaft 15 using a coupling. The second frame 12 is fixed to the lower end of the housing 1.

[0023] In use, this invention uses a coupling to coaxially connect the output end of the servo motor body 4 to the upper end of the rotating shaft 15. Then, an existing testing instrument (not shown in the figure) is used to connect the servo motor body 4, causing it to drive the rotating shaft 15 so that the pointer 25 points to the "0" mark on the dial 24. Under windless conditions, a measuring mechanism is used to test the mechanical clearance of the servo motor body 4 and the effect of this clearance on the servo motor's mechanical deflection angle. Afterwards, the second fan 8 is activated to generate airflow, which enters the housing 1 along the second threaded pipe and the main air duct 16. At this time, the tilt angle of the wing plate 2 is controlled by the servo motor body 4, changing the angle of contact between the wing plate 2 and the airflow. This allows for the simulation of various operating conditions to test the control accuracy and stability of the servo motor body 4, as detailed below: Firstly, the mechanical deflection angle of the servo motor body 4 remains unchanged, that is, the pointer 25 points to the "0" mark on the dial 24. At this time, the wing plate 2 is in a relatively parallel state with the airflow direction, maintaining a certain airflow speed. After the airflow speed stabilizes, the corresponding data of the test instrument can be read, the angle change of the pointer 25 can be observed, and the value of the vibration sensor can be observed, thereby achieving a comprehensive judgment on the impact of the mechanical clearance of the servo motor body 4 on its control accuracy and control stability. After recording all the data, the turbulence mechanism is activated to provide crosswinds to both sides of the wing plate 2, so that the wing plate 2 is in the airflow of different directions. By recording all the data again, the impact of the mechanical clearance of the servo motor body 4 on its control accuracy and control stability can be determined.

[0024] Secondly, the mechanical deflection angle of the servo motor body 4 produces a fixed angle change. By using a tester to input control signals of different angles to the servo motor body 4, the servo motor body 4 drives the rotating shaft 15 to change the angle of the wing plate 2. This can simulate the force situation of the wing in the airflow when the aircraft is ascending or descending. At this time, by reading and recording the corresponding data, the control accuracy and control stability can be calculated. After recording all the data, the turbulence mechanism is activated to provide airflow to both sides of the wing plate 2, so that the wing plate 2 is in the airflow of different wind directions. The data is recorded again, thereby enabling the determination of the control accuracy and control stability of the servo motor body 4 during the ascent and descent process.

[0025] Thirdly, when the mechanical deflection angle of the servo motor body 4 is fixed at a specific angle, the airflow speed provided by the first fan 9 and the second fan 8 is controlled and arbitrarily adjusted by an external controller, so as to simulate the fixed change of the mechanical deflection angle of the aircraft in the unstable airflow and test the control accuracy and control stability of the servo motor body 4.

[0026] Fourth, the mechanical deflection angle of the servo motor body 4 produces continuous alternating changes. The tester provides a signal of continuous angle change, causing the servo motor body 4 to make continuous reciprocating control actions. Furthermore, by controlling the first fan 9 and the second fan 8 to provide different airflows, the control accuracy and control stability of the servo motor body 4 are tested when the aircraft continuously produces mechanical deflection angle changes in unstable airflow.

[0027] Fifth, by controlling the mechanical deflection angle of the servo motor body 4 to a certain angle through the test instrument, even if the wing plate 2 is at a certain deflection angle, only the spoiler mechanism can be turned on, and the airflow on one side of the spoiler mechanism can be made to be at its maximum value. At this time, the wing plate 2 is subjected to a single lateral wind, and the resistance of the airflow acting on the wing plate 2 can be used to test the mechanical strength and elastic deformation of the aircraft servo motor transmission system, which is used to test the maximum load of the aircraft servo motor transmission system. At the same time, by adjusting the wing plate 2 to the maximum deflection angle, the second fan 8 can be turned on and the airflow gradually increased for testing.

[0028] Example 2: The difference from Example 1 is that; See attached document Figure 4-9The measuring mechanism includes a connecting frame 26, which is connected to a fixed ring. A half-gear ring 27 is fixedly connected to one end of the connecting frame 26. A gear 35 meshes with the inner side of the half-gear ring 27. A gear shaft 37 is fixedly connected to the upper end of the gear 35. A mounting plate 28 and a horizontal plate 30 are fixedly connected to the upper end of the mounting frame 3 through multiple columns. The gear shaft 37 is rotatably connected to the side wall of the mounting plate 28 through roller bearings. A transmission mechanism is connected to the upper end of the horizontal plate 30. The transmission mechanism is connected to the gear shaft 37 to drive the half-gear ring 27. The transmission mechanism includes an electromagnet 31 and a permanent magnet 29. The permanent magnet 29 is fixed to the upper end of the horizontal plate 30. A strip-shaped through hole is opened at the upper end of the horizontal plate 30. A connecting block is provided in the strip-shaped through hole. One end of the connecting block is fixedly connected to the lower end of the electromagnet 31. A slide block 33 is fixedly connected to the lower end of the horizontal plate 30. A slide bar 36 is slidably connected to the slide block 33. A rack 34 is fixedly connected to one side of the slide bar 36. The rack 34 meshes with a gear shaft 37.

[0029] The measuring mechanism provided in this invention, when measuring the mechanical clearance of an aircraft servo motor, first uses a testing instrument to control the servo motor body 4 to bring the pointer 25 to zero. Then, the electromagnet 31 is activated. When the electromagnet 31 is working, a magnetic attraction force is generated between it and the permanent magnet 29. This magnetic attraction force acts on the electromagnet 31, causing the connecting block to move the rack 34. The movement of the rack 34 causes the gear shaft 37 to rotate. The rotation of the gear shaft 37 causes the gear 35 to rotate the half-gear ring 27. The rotation of the half-gear ring 27 causes the connecting frame 26 to rotate the rotating shaft 15. The torque generated when the rotating shaft 15 rotates acts on the output end of the servo motor body 4. At the same time, the rotating shaft 15... When the angle pointed to by the pointer 25 changes, the value is recorded. Then, the direction of the magnetic poles of the electromagnet 31 is changed, generating a magnetic repulsion force between it and the permanent magnet 29. At this time, the measuring mechanism drives the rotating shaft 15 to rotate in the opposite direction, causing the angle of the pointer 25 to change in the opposite direction. The value is recorded again. Finally, the two recorded values ​​are added together, and the final value is the mechanical deflection angle value generated by the mechanical backlash of the servo. Then, when entering the simulation test, the power supply of the electromagnet 31 is disconnected, and the test device is in a natural state. At the same time, the pointer 25 and the dial 24 can be used to read the change of the mechanical deflection angle of the servo throughout the test.

[0030] Example 3: The difference from Example 1 is that; See attached document Figure 2-3The turbulence mechanism includes a three-way pipe 10 and two inclined guide plates 13. The two guide plates 13 are symmetrically fixed inside the housing 1. A box 17 is fixedly connected to one side of the guide plate 13. The side wall of the box 17 is provided with an exhaust port 22, which is inclined towards the wing plate 2. One end of the box 17 is provided with two exhaust sections 20, which are distributed in a V shape and located on both sides of the wing plate 2. One end of each exhaust section 20 is provided with a bend 21, and the exhaust port 22 is opened at the bend 21. A first wind speed sensor 18 is fixedly connected to the bend 21. Two conduits 7 are fixedly connected to the three-way pipe 10. The ends of the two conduits 7 away from the three-way pipe 10 pass through the side wall of the housing 1 and are fixedly connected to one side of the guide plate 13. One side of the conduits 7 passes through the guide plate 13 and is fixedly connected to one side of the box 17. A first fan 9 is fixedly connected to the first frame 11. The exhaust end of the first fan 9 is fixedly connected to the three-way pipe 10 through a first threaded pipe. A drive shaft 14 is rotatably connected inside the housing 1 via a needle roller bearing. The side wall of the box 17 is rotatably connected to the shaft wall of the drive shaft 14 via a sealed bearing. A flow guide assembly is provided inside the box 17 and is fixed on the shaft wall of the drive shaft 14. The flow guide assembly consists of two inclined flow guide plates 19, both of which are fixed on the shaft wall of the drive shaft 14. An adjustment motor 6 is fixedly connected to the mounting bracket 3, and the output end of the adjustment motor 6 is fixedly connected to the upper end of the drive shaft 14.

[0031] The present invention features a turbulence-inducing mechanism. In use, the first fan 9 generates airflow that enters the three-way pipe 10 through the first threaded pipe. The airflow in the three-way pipe 10 then enters the housing 17 through the duct 7. Two exhaust sections 20 on the housing 17 guide the airflow to both sides of the wing plate 2, thereby providing lateral airflow on both sides of the wing plate 2. The transmission shaft 14 is rotated by controlling the regulating motor 6. When the transmission shaft 14 rotates, it drives the turbulence-inducing component to swing. When the turbulence-inducing component swings, it changes the direction of the airflow through the guide plate 19, thereby changing the airflow speed and flow rate discharged from the two exhaust sections 20. Ultimately, the airflow speed and flow rate acting on the side of the wing plate 2 can be arbitrarily adjusted, achieving a more natural airflow simulation in conjunction with the airflow delivered by the main air duct 16. This allows for testing the influence of airflow on the mechanical deflection angle of the servo motor under complex operating conditions, facilitating the testing of the control accuracy and stability of the aircraft servo motor under complex operating conditions.

[0032] It should be noted that the term "comprising" or any other variation thereof is intended to cover non-exclusive inclusion, such that a device that includes a list of elements includes not only those elements but also other elements not expressly listed, or elements inherent to such a device. Without further limitation, an element defined by the phrase "comprising one..." does not exclude the presence of other identical elements in the device that includes said element.

[0033] Although embodiments of the invention have been shown and described, it will be understood by those skilled in the art that various changes, modifications, substitutions and alterations can be made to these embodiments without departing from the principles and spirit of the invention, the scope of which is defined by the appended claims and their equivalents.

Claims

1. A device for testing the deflection angle of an aircraft servo motor, comprising a housing (1), a wing plate (2), a first frame (11), and a second frame (12), characterized in that: An air outlet is provided on one side of the housing (1), and the wing plate (2) is vertically arranged in the air outlet. A main air duct (16) is fixed on the other side of the housing (1). A mounting bracket (3) is fixedly connected to the upper end of the housing (1), and a measuring mechanism is connected to the mounting bracket (3). The inner walls of the upper and lower ends of the housing (1) are respectively rotatably connected to a rotating shaft (15) and a connecting shaft via rolling bearings. The opposite ends of the rotating shaft (15) and the connecting shaft are fixedly connected to the wing plate (2) by bolts. A fixing ring is connected to the shaft wall of the rotating shaft (15). One side of the fixing ring is connected to the measuring mechanism. A pointer (25) is fixedly connected to the other side of the fixing ring. A vibration sensor (23) is fixedly connected to the pointer (25). A dial (24) that cooperates with the pointer (25) is fixedly connected to the side wall of the mounting bracket (3). The measuring mechanism includes a connecting frame (26), which is connected to a fixed ring. A half-gear ring (27) is fixedly connected to one end of the connecting frame (26). A gear (35) meshes with the inner side of the half-gear ring (27). A gear shaft (37) is fixedly connected to the upper end of the gear (35). A mounting plate (28) and a horizontal plate (30) are fixedly connected to the upper end of the mounting frame (3) through multiple columns. The gear shaft (37) is rotatably connected to the side wall of the mounting plate (28) through roller bearings. A transmission mechanism is connected to the upper end of the horizontal plate (30). The transmission mechanism is connected to the gear shaft (37) to drive the half-gear ring (27). The measuring mechanism is used to test the change of the mechanical deflection angle of the servo motor when the wingplate (2) is exposed to wind, and can also test the influence of mechanical clearance on the mechanical deflection angle of the servo motor under windless conditions. The housing (1) is provided with a flow disturbance mechanism, which includes a three-way pipe (10) and two inclined guide plates (13). The two guide plates (13) are symmetrically fixed inside the housing (1). A box body (17) is fixedly connected to one side of the guide plate (13). An exhaust port (22) is provided on the side wall of the box body (17). The exhaust port (22) is inclined towards the wing plate (2). Two conduits (7) are fixedly connected to the three-way pipe (10). The ends of the two conduits (7) away from the three-way pipe (10) pass through the side wall of the housing (1) and are fixedly connected to one side of the guide plate (13). One side of the conduit (7) passes through the guide plate (13) and is fixedly connected to one side of the box body (17). A first fan (9) is fixedly connected to the first frame (11). The exhaust end of the first fan (9) is fixedly connected to the three-way pipe (10) through the first threaded pipe. The turbulence mechanism is used to provide crosswinds to both sides of the wing plate (2) during the test, so that the wing plate (2) is in the airflow of different wind directions to test the stability of the servo when adjusting the deflection angle.

2. The device for testing the deflection angle of an aircraft servo motor according to claim 1, characterized in that: The transmission mechanism includes an electromagnet (31) and a permanent magnet (29). The permanent magnet (29) is fixed to the upper end of the horizontal plate (30). The upper end of the horizontal plate (30) has a strip-shaped through hole. A connecting block is provided in the strip-shaped through hole. One end of the connecting block is fixedly connected to the lower end of the electromagnet (31). A slide block (33) is fixedly connected to the lower end of the horizontal plate (30). A slide bar (36) is slidably connected to the slide block (33). A rack (34) is fixedly connected to one side of the slide bar (36). The rack (34) meshes with a gear shaft (37).

3. The device for testing the deflection angle of an aircraft servo motor according to claim 1, characterized in that: The housing (1) is rotatably connected to the drive shaft (14) via a needle roller bearing. The side wall of the box (17) is rotatably connected to the shaft wall of the drive shaft (14) via a sealed bearing. The box (17) is provided with a flow guiding component, which is fixed on the shaft wall of the drive shaft (14). An adjusting motor (6) is fixedly connected to the mounting bracket (3), and the output end of the adjusting motor (6) is fixedly connected to the upper end of the drive shaft (14).

4. The device for testing the deflection angle of an aircraft servo motor according to claim 3, characterized in that: The flow guiding assembly consists of two inclined flow guiding plates (19), both of which are fixed on the shaft wall of the drive shaft (14).

5. The device for testing the deflection angle of an aircraft servo motor according to claim 1, characterized in that: The box (17) has two exhaust sections (20) at one end. The two exhaust sections (20) are distributed in a V shape and are located on both sides of the wing plate (2). Each exhaust section (20) has an elbow (21) at one end. The exhaust port (22) is opened at the elbow (21). A first wind speed sensor (18) is fixedly connected at the elbow (21).

6. The device for testing the deflection angle of an aircraft servo motor according to claim 1, characterized in that: A second fan (8) is fixedly connected to the first frame (11). The exhaust end of the second fan (8) is fixedly connected to one end of the main air duct (16) through a second threaded pipe. A second wind speed sensor (32) is fixedly connected to one side of the housing (1). The second wind speed sensor (32) is located at the opening of the main air duct (16).

7. The device for testing the deflection angle of an aircraft servo motor according to claim 1, characterized in that: The upper end of the housing (1) is fixedly connected to a servo mounting base (5), and the second frame (12) is fixed to the lower end of the housing (1).

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