Aviation turbine engine rotor borescope driver

Abstract

The invention, which relates to the technical field of aviation turbine engine detection, discloses an aviation turbine engine rotor borescope driver comprising an equipment box, a host, a tablet computer, a universal support, a driving assembly and an operating system. According to the aero-turbine engine rotor borescope driver, through the tablet computer, the engine rotor can be accurately driven to rotate by a circle and stop, in the rotating process, a user can adjust the rotating speed of the rotor on a touch screen on the tablet computer, and position point information of defective blades in the engine rotor is recorded; the position where the defective blade is recorded can be quickly rotated through the touch screen, a user can conveniently and repeatedly check the defective blade, the rotor can quickly rotate by an angle with a gear clearance during reversing, the gear rotates, the engine rotor is fixed during reversing, the waiting time of workers is shortened, the working efficiency is improved, and the working efficiency is improved according to the test. And the waiting time can be reduced to 20-30% of the original waiting time, so that the working efficiency is obviously improved.

Description

Technical Field

[0001] The invention relates to the technical field of aviation turbine engine detection, in particular to an aviation turbine engine rotor boresight driver. Background Art

[0002] The two major aircraft engine rotor drives currently in use around the world are developed and manufactured by developed countries in Europe and the United States. They are very expensive and have very long maintenance cycles. Domestic airlines have not purchased similar products, and only a few engine maintenance companies have purchased very few drive products to meet the production needs of maintenance operations. However, since aircraft engine boresight has very high requirements for the uniformity and accuracy of high-pressure rotor rotation, manual rotation cannot meet the requirements. There is an urgent need to solve the problem of equipment shortage. Therefore, an aircraft turbine engine rotor boresight drive is proposed. Summary of the invention

[0003] In view of the deficiencies in the prior art, the present invention provides an aviation turbine engine rotor boresight driver, which solves the problems raised in the above-mentioned background technology.

[0004] To achieve the above objectives, the present invention is implemented through the following technical solutions: an aviation turbine engine rotor boresight driver, comprising an equipment box, a host, a tablet computer, a universal bracket, a drive assembly and an operating system; a host is placed inside the equipment box, a tablet computer is placed inside the equipment box and on one side of the host, and a drive assembly is placed inside the equipment box and in front of the tablet computer. The drive assembly is composed of a stepper motor, a reducer body and a reducer bracket, a reducer body is installed at one end of the stepper motor, and a reducer bracket is installed at one end of the reducer body. A fan exhaust port is provided on one side of the host, a WIFI antenna interface is installed on one side of the host, a drive assembly interface is installed on one side of the host and on the right side of the WIFI antenna interface, a power plug is installed on one side of the host and above the drive assembly interface, a switch is installed on the top of the host, and fans are installed on both sides of the host cavity.

[0005] Optionally, the operating system is integrated in a tablet computer, and the operating system includes a language selection module, a model selection module, an information input module and an operation module;

[0006] The language selection module is used to select the operating language of the operating system, including English and Chinese;

[0007] The model selection module is used to select the target engine type;

[0008] The operation module is used to operate the device during the detection of the rotor of the air turbine engine.

[0009] Optionally, the model selection module includes a parameter setting module and a record query module, the parameter setting module is used to select the target engine type; the record query module is used to query the stored test records.

[0010] Optionally, the information input module includes an employee number input module, an engine ESN module, an information identification module and a record storage module. The employee number input module is used to input the operator's employee number after selecting the target engine type; the engine ESN module is used to display the engine's ESN number; the information identification module is used to identify whether the input information is correct and confirm it; the record storage module is used to store the usage record of the drive.

[0011] Optionally, the operation module includes a data monitoring module, a marking point module, a counterclockwise module, a clockwise module, a state switching module, a deceleration module, a mark clearing module, an acceleration module, a marking module, an angle zeroing module, a virtual position calibration module and a virtual position calibration correction module. The data monitoring module is used to monitor and obtain the data generated by the driver during operation; the marking point module is used to record the marked points; the virtual position calibration module is used to perform virtual position calibration; the virtual position calibration correction module is used to use the virtual position calibration correction function in the operation interface to fine-tune the calibration if there is a deviation; the counterclockwise module is used to drive the drive component to rotate counterclockwise; the clockwise module is used to drive the drive component to rotate clockwise; the state switching module is used to control whether the drive component is working; the deceleration module is used to click once, and the speed of the drive component will be decelerated and adjusted once again, 5 degrees / time, and long press to decelerate continuously. The minimum speed is 0 degrees / minute, and there is no rotation state; the acceleration module is used to accelerate and adjust the speed of the drive component once for each click, 5 degrees / time, and long press for continuous acceleration, and the maximum speed is limited to 360 degrees / minute; the marking module is used to store the current rotor angle position data in the system. The marking angle position can be performed when the drive component is rotating or stopped. The system records the marking information in sequence, and a total of angle positions can be stored. Even if the operator performs angle zeroing, the value of the marked point is still available, and the stored value will be modified according to the angle reset; the angle zeroing module is used to set the current rotor position to the starting point and the displayed value to zero degrees. If the device has stored some marked points, the angle zeroing operation will not cause the original stored position data to be lost, and the displayed stored angle value will change accordingly. The mark clearing module is used to clear the rotor angle position information recorded in 10 marks, and the number on the mark is set to zero.

[0012] Optionally, the virtual position calibration module includes a data monitoring unit, a counterclockwise unit, a clockwise unit, a state switching unit, a calibration starting point module, a calibration end point module and a display value module, wherein the data monitoring unit is used to monitor the data generated during the virtual position calibration; the counterclockwise unit is used to set the rotation direction of the drive component to clockwise; the clockwise unit is used to set the rotation direction of the drive component to counterclockwise; the state switching unit is used to control the operation of the drive component; the calibration starting point module is used to drive the component to rotate, observe the rotation of the engine blades, wait for the engine rotor to rotate for 10-15 seconds, and then record the starting point data; the calibration end point module is used to reverse the rotation direction of the drive component, change the direction from clockwise to counterclockwise, or from counterclockwise to clockwise, start the drive component to rotate, pay attention to whether the engine blades start to rotate, and when it is observed that the engine blades start to rotate, immediately pause the rotation of the drive component and then record the end point data; the display value module is used to display the measured value of this gear virtual position calibration.

[0013] Optionally, when the counterclockwise module is used, the clockwise module cannot be used, and when the clockwise module is used, the counterclockwise module cannot be used. Both the counterclockwise module and the clockwise module have an interlocking function.

[0014] Optionally, the reducer body is designed with a reduction ratio of 70:1, 3-stage reduction and transmission through helical gears.

[0015] The present invention provides an aviation turbine engine rotor boresight driver, which has the following beneficial effects:

[0016] 1. The aviation turbine engine rotor boresight driver can accurately drive the engine rotor to rotate one circle and stop through a tablet computer. During the rotation process, the user can adjust the rotor rotation speed on the touch screen of the tablet computer, record the position point information of the defective blades in the engine rotor, and quickly go to the position of the recorded defective blades through the touch screen, so that the user can repeat the inspection of the defective blades. When the rotor is reversed, the angle with gear gap can be quickly rotated. During this period, the gears rotate and the engine rotor does not move, which reduces the waiting time of the workers and improves the work efficiency. According to the test, the waiting time can be reduced to 20-30% of the original waiting time, thereby significantly improving the work efficiency.

[0017] 2. The aviation turbine engine rotor boresight driver is provided with an equipment box, a host, a tablet computer and a driving component. When used on site, the driving component can be installed on the engine adapter and powered on, which saves on-site assembly and disassembly time and improves work efficiency. Wireless connection is adopted between the host and the tablet computer to avoid confusion caused by too many lines on the work site. BRIEF DESCRIPTION OF THE DRAWINGS

[0018] Figure 1 This is a schematic diagram of the internal structure of the equipment box of the present invention;

[0019] Figure 2 This is a schematic diagram of the connection structure between the universal bracket and the tablet computer of the present invention;

[0020] Figure 3 This is a schematic diagram of the structure of the drive assembly of the present invention;

[0021] Figure 4 It is a structural schematic diagram of the device box of the present invention when it is moved;

[0022] Figure 5 This is a schematic diagram of the outer structure of the host of the present invention;

[0023] Figure 6 It is a schematic diagram of the structure of the operating system of the present invention;

[0024] Figure 7 It is a schematic diagram of the structure of the virtual position calibration module of the present invention;

[0025] Figure 8 It is a model selection page diagram in the software developed by the operating system of the present invention;

[0026] Fig. 9 This is the operation interface diagram of the present invention;

[0027] Fig.10 It is a virtual position calibration page diagram of the present invention;

[0028] Fig.11 This is the wiring diagram of the internal line board of the host of the present invention.

[0029] In the figure: 1. Equipment box; 2. Host; 3. Tablet computer; 4. Universal bracket; 5. Fan exhaust port; 6. WIFI antenna interface; 7. Drive component interface; 8. Power plug; 9. Switch; 10. Stepper motor; 11. Reducer body; 12. Reducer bracket; 13. Language selection module; 14. Model selection module; 15. Parameter setting module; 16. Record query module; 17. Information input module; 18. Employee number input module; 19. Engine ESN module; 20. Information identification module; 21. Record storage module; 2 2. Operation module; 23. Data monitoring module; 24. Marking point module; 25. Counterclockwise module; 26. Clockwise module; 27. State switching module; 28. Deceleration module; 29. ​​Mark clearing module; 30. Acceleration module; 31. Marking module; 32. Angle zeroing module; 33. Virtual position calibration module; 34. Virtual position calibration correction module; 35. Data monitoring unit; 36. Counterclockwise unit; 37. Clockwise unit; 38. State switching unit; 39. Calibration starting point module; 40. Calibration end point module; 41. Display value module. DETAILED DESCRIPTION

[0030] The technical solutions in the embodiments of the present invention will be described clearly and completely below in conjunction with the drawings in the embodiments of the present invention. Obviously, the described embodiments are only part of the embodiments of the present invention, rather than all the embodiments.

[0031] See also Figures 1 to 11 The present invention provides a technical solution: an aviation turbine engine rotor boresight driver, comprising an equipment box 1, a host 2, a tablet computer 3, a universal bracket 4, a drive component and an operating system; the host 2 is placed inside the equipment box 1, the tablet computer 3 is placed inside the equipment box 1 and on one side of the host 2, and a 42 is placed inside the equipment box 1 and in front of the tablet computer 3. The drive component is composed of a stepper motor 10, a reducer body 11 and a reducer bracket 12. The reducer body 11 is installed at one end of the stepper motor 10, and the reducer bracket 12 is installed at one end of the reducer body 11. A fan exhaust port 5 is provided on one side of the host 2, a WIFI antenna interface 6 is installed on one side of the host 2, a drive component interface 7 is installed on one side of the host 2 and on the right side of the WIFI antenna interface 6, a power plug 8 is installed on one side of the host 2 and above the drive component interface 7, and a top of the host 2 is installed A switch 9 is installed, fans are installed on both sides of the inner cavity of the host 2, a female drive connector is installed on the host 2, a male head is installed on the stepper motor 10, a power board, a PLC module, an HMI module and a stepper motor driver board are installed in the inner cavity of the host 2, a PLC and a separate HMI module are installed on the host 2 using RS-4852W two-wire wiring, the signals connected to the PLC module and the closed stepper motor driver board are four signals: pulse signal positive, pulse signal negative, direction signal positive, and direction signal negative, the motor driver board encoder signal, encoder signal A positive, encoder signal A negative, encoder signal B positive, encoder signal B negative, encoder power supply, encoder power supply positive, encoder power supply negative and stepper motor line, motor line A positive, motor line A negative, motor line B positive, motor line B negative are connected to the female drive connector on the host 2, and the female connector of the host 2 and the male head of the drive component can be quickly connected and decomposed.

[0032] The operating system is integrated in the tablet computer 3, and the operating system includes a language selection module 13, a model selection module 14, an information input module 17 and an operation module 22;

[0033] A language selection module 13, used to select an operating language of the operating system, including English and Chinese;

[0034] The model selection module 14 is used to select the target engine type;

[0035] The operation module 22 is used to operate the device during the detection of the air turbine engine rotor.

[0036] The engine type selection module 14 includes a parameter setting module 15 and a record query module 16. The parameter setting module 15 is used to select the target engine type; the record query module 16 is used to query the stored test records.

[0037] Among them, the information input module 17 includes an employee number input module 18, an engine ESN module 19, an information identification module 20 and a record storage module 21. The employee number input module 18 is used to input the operator's employee number after selecting the target engine type; the engine ESN module 19 is used to display the engine's ESN number; the information identification module 20 is used to identify whether the input information is correct and confirm it; the record storage module 21 is used to store the drive usage record.

[0038] Among them, the operation module 22 includes a data monitoring module 23, a marking point module 24, a counterclockwise module 25, a clockwise module 26, a state switching module 27, a deceleration module 28, a mark clearing module 29, an acceleration module 30, a marking module 31, an angle zeroing module 32, a virtual position calibration module 33 and a virtual position calibration correction module 34. The data monitoring module 23 is used to monitor and obtain the data generated by the driver during operation; the marking point module 24 is used to record the marked points; the virtual position calibration module 33 is used to perform virtual position calibration; the virtual position calibration correction module 34 is used to use the virtual position calibration correction function in the operation interface to fine-tune if the calibration has deviations; the counterclockwise module 25 is used to drive the drive component to rotate counterclockwise; the clockwise module 26 is used to drive the drive component to rotate clockwise; the state switching module 27 is used to control whether the drive component is working; the deceleration module 28 is used to click once, and the speed of the drive component is decelerated and adjusted once again, 5 degrees / time, and long press to continuously decelerate, and the minimum speed is 0 degrees / minute, no rotation state; acceleration module 30, used for each click, the drive component speed is accelerated and adjusted once, 5 degrees / time, long press for continuous acceleration, and the maximum speed is limited to 360 degrees / minute; marking module 31, used to store the current rotor angle position data in the system, marking the angle position can be performed when the drive component is rotating or stopped, the system records the marking information in sequence, and the corresponding recording position mark point changes from gray to light green, indicating that the data of the mark point has been stored. A total of 10 angle positions can be stored. Even if the operator performs angle zeroing, the value of the mark point is still available, and the stored value will be modified according to the angle reset; angle zeroing module 32, used to set the current rotor position to the starting point and the displayed value to zero. If the device has stored some mark points, the angle zeroing operation will not cause the original stored position data to be lost, and the displayed stored angle value will change accordingly. The mark clearing module 29 is used to clear the rotor angle position information recorded in the 10 marks, and the number on the mark is set to zero.

[0039] Among them, the virtual position calibration module 33 includes a data monitoring unit 35, a counterclockwise unit 36, a clockwise unit 37, a state switching unit 38, a calibration starting point module 39, a calibration end point module 40 and a display value module 41. The data monitoring unit 35 is used to monitor the data generated during the virtual position calibration; the counterclockwise unit 36 ​​is used to set the rotation direction of the drive component to be clockwise; the clockwise unit 37 is used to set the rotation direction of the drive component to be counterclockwise; the state switching unit 38 is used to control the operation of the drive component; the calibration starting point module 39 is used to drive the component to rotate, observe the rotation of the engine blades, wait for the engine rotor to rotate for 10-15 seconds, and then record the starting point data; the calibration end point module 40 is used to reverse the rotation direction of the drive component, change the direction from clockwise to counterclockwise, or from counterclockwise to clockwise, start the drive component to rotate, pay attention to observe whether the engine blades start to rotate, and when it is observed that the engine blades start to rotate, immediately pause the rotation of the drive component and then record the end point data; the display value module 41 is used to display the measured value of the current gear virtual position calibration.

[0040] When the counterclockwise module 25 is used, the clockwise module 26 cannot be used, and when the clockwise module 26 is used, the counterclockwise module 25 cannot be used. Both the counterclockwise module 25 and the clockwise module 26 have an interlocking function.

[0041] The reducer body 11 is designed with a reduction ratio of 70:1, 3-stage reduction and transmission through helical gears.

[0042] In summary, when using the aviation turbine engine rotor boresight driver, the equipment box 1 is moved to the side of the aviation turbine engine, and then the host 2 and the tablet computer 3 are taken out from the equipment box 1, and the tablet computer 3 is installed on the universal bracket 4, and the universal bracket 4 is fixed to a suitable position of the engine, and the drive assembly is fixed to the engine rotor adapter with the two built-in 42, and the power cable is inserted into the power plug 8, and the other end of the power cable is connected to the drive assembly, and the switch 9 is pressed to start the host 2, and the driver is controlled by the tablet computer 3. The host initialization needs to wait for 15-20 seconds, and the tablet computer 3 and the host 2 are automatically connected via WIFI. Select the operating language as Chinese or English, select the target engine type, and press the OK key to enter the information. The operator enters the information input interface, enters the operator's employee number through the employee number input module 18, and enters the engine serial number through the engine ESN module 19. If the employee number and engine serial number are not entered, a warning message will pop up to identify whether the input information is correct, and confirm it, and store the usage record of the storage drive. Then enter the virtual position calibration interface through the virtual position calibration module 33. Press Start / Pause on the virtual position calibration interface, the drive component rotates, observe the rotation of the engine blades, wait for the engine rotor to rotate for 10-15 seconds, press Start / Pause, pause the rotation of the drive component, press the calibration starting point to record the starting point data, press the clockwise or counterclockwise button, reverse the rotation direction of the drive component and change the direction from clockwise to counterclockwise, or from counterclockwise to clockwise. Press Start / Pause to start the rotation of the drive component, pay attention to whether the engine blades start to rotate, and when the engine blades are observed to start to rotate, immediately pause the rotation of the drive component, and then press the calibration end point to record the end point data. The data on the display value is the measured value of this gear virtual position calibration. Press the OK button to enter the operation interface. If the calibration is deviated, you can use the virtual position calibration correction function in the operation interface to make fine adjustments. In the operation interface, make sure that the flexible probe of the borescope equipment is in the proper position before pressing the start / pause button. During the rotation of the engine rotor, the flexible probe cannot physically contact the engine rotor blades, otherwise it may damage the flexible probe or the engine blades. When the clockwise button is selected, the background turns green, the background of the counterclockwise button turns orange, and the direction of rotation of the drive component is clockwise. The clockwise and counterclockwise buttons are interlocked. When the counterclockwise button is selected, the background turns green, the background of the clockwise button turns orange, and the direction of rotation of the drive component is counterclockwise. The clockwise and counterclockwise buttons are interlocked buttons. Each time the acceleration button is touched, the speed of the drive component is adjusted once in acceleration by 5 degrees / time. Long press the acceleration to continuously accelerate. The maximum speed is limited to 360 degrees / minute. Each time the deceleration button is touched, the speed of the drive component is adjusted once in deceleration by 5 degrees / time. Long press the deceleration to continuously decelerate. The minimum speed is 0 degrees / minute without rotation. Press the mark button and the current rotor angle position data is stored in the system.Marking the angle position can be performed both when the drive assembly is rotating and stopped. The system records the marking information in sequence, and the corresponding recording position mark point changes from gray to light green, indicating that the data of the marked point has been stored. A total of 10 angle positions can be stored. Even if the operator performs an angle zeroing, the value of the marked point is still available, and the stored value will be modified according to the angle reset. Angle zeroing is used to set the current rotor position to the starting point and the displayed value to zero degrees. If the device has already stored some marked points, the angle zeroing operation will not cause the original stored position data to be lost, and the displayed stored angle value will change accordingly. In order to ensure the accuracy of the rotation of the drive engine rotor, please perform angle zeroing after the engine gear is in meshing state. Perform angle zeroing when the gear is not in meshing state. Some rotor blades may be missed in the first rotation of the engine rotor. The drive assembly performs ramp deceleration before reaching the target position to ensure that the output shaft and gear are in meshing state when the drive assembly stops. The mark reset is used to clear the rotor angle position information recorded in the 10 marks. The number on the mark is set to zero and the background becomes gray. When the drive assembly is in a stopped or paused state, the background color of the independent mark point that stores the angle position is light green when touched. The system automatically makes a judgment to let the drive assembly select the best route to drive the rotor to the target point at a maximum speed of 360 degrees / minute, and accurately display the marked engine blade on the borescope device. After reaching the target point, fine-tune the engine rotor clockwise or counterclockwise as needed to obtain a good defect observation angle. The system automatically selects the best route to reach the target marked blade. The drive assembly rotates in the previous direction or the opposite direction. The final route rotates less than 180 degrees. The PW1100G series engine will always rotate clockwise to the target mark point because the PW1100G engine manual recommends driving the rotor clockwise. During the execution of the drive assembly to the target marked blade instruction, the drive assembly rotation can be paused, a new marked blade can be reselected, or a new circle of rotation can be performed automatically at zero degrees.

[0043] The above description is only a preferred specific implementation manner of the present invention, but the protection scope of the present invention is not limited thereto. Any technician familiar with the technical field can make equivalent replacements or changes according to the technical scheme and inventive concept of the present invention within the technical scope disclosed by the present invention, which should be covered by the protection scope of the present invention.

Claims

1. An aviation turbine engine rotor boresight driver, characterized in that: The device comprises a device box (1), a host (2), a tablet computer (3), a universal bracket (4), a drive component and an operating system; the host (2) is placed inside the device box (1), the tablet computer (3) is placed inside the device box (1) and on one side of the host (2), and (42) is placed inside the device box (1) and in front of the tablet computer (3); the drive component is composed of a stepper motor (10), a reducer body (11) and a reducer bracket (12); the reducer body (11) is installed at one end of the stepper motor (10) A reducer bracket (12) is installed at one end of the reducer body (11), a fan exhaust port (5) is provided on one side of the host (2), a WIFI antenna interface (6) is installed on one side of the host (2), a drive component interface (7) is installed on one side of the host (2) and located on the right side of the WIFI antenna interface (6), a power plug (8) is installed on one side of the host (2) and located above the drive component interface (7), a switch (9) is installed on the top of the host (2), and fans are installed on both sides of the inner cavity of the host (2).

2. The aircraft turbine engine rotor boresight driver according to claim 1, characterized in that: The operating system is integrated in a tablet computer (3), and comprises a language selection module (13), a model selection module (14), an information input module (17) and an operation module (22); The language selection module (13) is used to select the operating language of the operating system, and the languages ​​include English and Chinese; The engine type selection module (14) is used to select a target engine type; The operation module (22) is used to operate the device during the detection of the rotor of the air turbine engine.

3. The aircraft turbine engine rotor boresight driver according to claim 2, characterized in that: The model selection module (14) comprises a parameter setting module (15) and a record query module (16); the parameter setting module (15) is used to select a target engine type; and the record query module (16) is used to query stored test records.

4. The aircraft turbine engine rotor boresight driver according to claim 2, characterized in that: The information input module (17) comprises an employee number input module (18), an engine ESN module (19), an information identification module (20) and a record storage module (21); the employee number input module (18) is used to input the operator's employee number after selecting the target engine type; the engine ESN module (19) is used to display the engine's ESN number; The information identification module (20) is used to identify whether the input information is correct and to confirm it; the record storage module (21) is used to store the use record of the drive.

5. The aircraft turbine engine rotor boresight driver according to claim 2, characterized in that: The operation module (22) comprises a data monitoring module (23), a marking point module (24), a counterclockwise module (25), a clockwise module (26), a state switching module (27), a deceleration module (28), a mark clearing module (29), an acceleration module (30), a marking module (31), an angle zeroing module (32), a virtual position calibration module (33) and a virtual position calibration correction module (34), wherein the data monitoring module (23) is used to monitor and obtain data generated by the driver during operation; the marking point module The block (24) is used to record the marked point position; the virtual position calibration module (33) is used to perform virtual position calibration; the virtual position calibration correction module (34) is used to use the virtual position calibration correction function in the operation interface to perform fine adjustment if there is a calibration deviation; the counterclockwise module (25) is used to drive the driving component to rotate counterclockwise; the clockwise module (26) is used to drive the driving component to rotate clockwise; the state switching module (27) is used to control whether the driving component is working; the deceleration module (28) is used to Click once, the speed of the drive component is decelerated and adjusted once, 5 degrees / time, long press to continuously decelerate, the minimum speed is 0 degrees / minute, and there is no rotation state; the acceleration module (30) is used for each click, the speed of the drive component is accelerated and adjusted once, 5 degrees / time, long press to continuously accelerate, and the maximum speed is limited to 360 degrees / minute; the marking module (31) is used to store the current rotor angle position data in the system, marking the angle position can be performed when the drive component is rotating or stopped, the system records the marking information in sequence, and a total of 10 angle positions can be stored. Even if the operator performs angle zeroing, the value of the marked point is still available, and the stored value will be modified according to the angle reset; the angle zeroing module (32) is used to set the current rotor position as the starting point and the displayed value to zero. If the device has stored some marked points, the angle zeroing operation will not cause the original stored position data to be lost, and the displayed stored angle value will be changed accordingly. The mark clearing module (29) is used to clear the rotor angle position information recorded in the 10 marks, and the number on the mark is set to zero.

6. The aircraft turbine engine rotor boresight driver according to claim 5, characterized in that: The virtual position calibration module (33) comprises a data monitoring unit (35), a counterclockwise unit (36), a clockwise unit (37), a state switching unit (38), a calibration starting point module (39), a calibration end point module (40) and a display value module (41), wherein the data monitoring unit (35) is used to monitor the data generated during the virtual position calibration; the counterclockwise unit (36) is used to set the rotation direction of the driving component to be clockwise; the clockwise unit (37) is used to set the rotation direction of the driving component to be counterclockwise; and the state switching unit (38) is used to control the operation of the driving component; The calibration starting point module (39) is used to drive the component to rotate, observe the rotation of the engine blades, wait for the engine rotor to rotate for 10-15 seconds, and then record the starting point data; the calibration end point module (40) is used to reverse the rotation direction of the drive component, change the direction from clockwise to counterclockwise, or from counterclockwise to clockwise, start the drive component to rotate, and observe whether the engine blades start to rotate. When the engine blades are observed to start to rotate, the drive component rotation is immediately paused, and then the end point data is recorded; the display value module (41) is used to display the measured value of the current gear virtual position calibration.

7. The aircraft turbine engine rotor boresight driver according to claim 5, characterized in that: When the counterclockwise module (25) is used, the clockwise module (26) cannot be used, and when the clockwise module (26) is used, the counterclockwise module (25) cannot be used. Both the counterclockwise module (25) and the clockwise module (26) have an interlocking function.

8. The aircraft turbine engine rotor boresight driver according to claim 1, characterized in that: The reducer body (11) is designed with a reduction ratio of 70:1, three-stage reduction and transmission via helical gears.

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