Aero-engine gas environment flow self-adaptive control method and device

Abstract

The invention discloses an aero-engine gas environment flow self-adaptive control method and device.The aero-engine gas environment flow self-adaptive control device comprises an aero-engine gas inlet pipe, an air flow potentiometer, a controller, blades and an air filtering ring, a gas channel is formed in the aero-engine gas inlet pipe, and a deflation window is formed in a mounting plate; a rotating rod is rotationally installed between the supporting plates, a deflation valve is installed on the rotating rod, a torsion spring and an air flow potentiometer are installed on the rotating rod, an air inlet window is formed in the adjusting ring, blades are installed on the rotating shaft in a surrounding mode, a gear B is installed at one end of the rotating shaft, and a gear A is installed at the power shaft end of the servo motor. And the gear A is meshed with the gear B. According to the method, the amount of air entering the aero-engine can be automatically adjusted according to the actual air flow requirement of the aero-engine, stable operation of the aero-engine is guaranteed, the gas environment flow self-adaption capacity of the aero-engine is improved, and the operation efficiency of the aero-engine is improved.

Description

Technical Field

[0001] This invention relates to the field of adaptive control methods and devices for gas environment flow in aero-engines, specifically to an adaptive control method and device for gas environment flow in aero-engines. Background Technology

[0002] An aero-engine is a device that converts the thermal energy or other forms of energy of fuel into mechanical energy to provide power for aircraft such as airplanes and helicopters. It is a highly complex and precise thermodynamic machine that provides the power required for aircraft to fly. Aero-engines are mainly divided into two categories: piston engines and jet engines. When the power of an aero-engine changes, the intake air volume needs to be precisely adjusted according to the actual intake air requirements of the aero-engine in order to achieve stable operation of the aero-engine.

[0003] The existing equipment has the following shortcomings when in use: it cannot accurately adjust the intake volume according to the actual intake requirements of the aero engine, which affects the operational stability of the aero engine, reduces the performance of the aero engine, and leads to a decrease in the operating efficiency of the aero engine. Summary of the Invention

[0004] The purpose of this invention is to provide an adaptive control method and apparatus for gas environment flow in aero-engines, so as to solve the problems mentioned in the background art.

[0005] To achieve the above objectives, the present invention provides the following technical solution: an adaptive control device for gas environment flow in an aero-engine, comprising an aero-engine intake pipe, an air flow potentiometer, a controller, blades, and an air filter ring. A gas passage is provided on the aero-engine intake pipe, and a mounting plate is provided in the gas passage. An air vent is provided on the mounting plate, and a support plate is mounted on the mounting plate. A rotating rod is rotatably mounted between the support plates, and an air vent valve is mounted on the rotating rod. A torsion spring and an air flow potentiometer are mounted on the rotating rod. An adjusting ring is provided in the gas passage, and an intake window is provided on the adjusting ring. A rotating shaft is rotatably mounted on the side of the adjusting ring, and blades are mounted around the rotating shaft. A gear B is mounted at one end of the rotating shaft. A servo motor is mounted in the adjusting ring, and a gear A is mounted on the power shaft end of the servo motor. Gear A meshes with gear B.

[0006] Using the above technical solution, air flows in from the gas passage of the aero-engine intake pipe. When it passes through the vent window on the mounting plate, the inhaled air rushes towards the vent valve. Due to the air pressure, the vent valve rotates and opens, causing the rotating rod mounted between the support plates to rotate. This causes the sliding arm of the air flow potentiometer to rotate synchronously with the vent valve. The voltage drop of the sliding resistor is used to convert the opening degree of the vent valve into an electrical signal. This electrical signal is then transmitted to the controller. Based on the received electrical signal, the controller can detect the air flow entering the aero-engine in real time. When the air flow exceeds the preset maximum value, the controller sends a command to the servo motor. The servo motor starts, and gear A mounted on its power shaft drives gear B, which meshes with it, to rotate. Since gear B is mounted on the rotating shaft, the rotating shaft rotates along with gear B. The rotation of the shaft further drives the rotation of the blades mounted around it. The blades are larger than the air intake window. Adjusting the position of the blades increases the area of ​​the air intake window they cover, thereby reducing the airflow entering the aero-engine. When the airflow is lower than a preset minimum value, the controller sends another command to the servo motor to adjust the position of the blades, reducing the area of ​​the air intake window they cover, thereby increasing the airflow entering the aero-engine. This allows the aero-engine intake pipe to automatically adjust the amount of air entering the aero-engine according to the actual airflow requirements, ensuring the stable operation of the aero-engine, improving the aero-engine's gas environment flow self-adaptation capability, and enhancing the aero-engine's operating efficiency.

[0007] Preferably, the air intake pipe of the aircraft engine is equipped with a mounting cover, and an electric telescopic rod is installed in the mounting cover. An adjusting rod is installed at one end of the electric telescopic rod.

[0008] By adopting the above technical solution, the electric telescopic rod is activated, causing the adjusting rod to move up and down. By adjusting the height of the adjusting rod, the vent valve is made to abut against one end of the adjusting rod when it is rotated open. This allows for adjustment of the maximum opening of the vent valve, providing a dual regulation mechanism for the airflow entering the aero-engine. This further enhances the adaptive capability of the aero-engine's airflow into the intake pipe and ensures the stable operation of the aero-engine under various operating conditions.

[0009] Preferably, an air filter ring is threadedly installed in the gas channel, and an air filter screen is provided on the air filter ring.

[0010] Using the above technical solution, the air filter ring is connected to the gas channel by a thread, which is convenient for disassembly and replacement. The air filter screen filters the air drawn into the air intake pipe of the aircraft engine, effectively blocking impurities and dust in the air, ensuring the air quality entering the aircraft engine, avoiding damage to the aircraft engine caused by impurities and dust, and extending the service life of the aircraft engine.

[0011] Preferably, a controller is installed in the air intake pipe of the aircraft engine, and the controller is connected to electronic components in the air intake pipe of the aircraft engine.

[0012] Using the above technical solution, the controller receives electrical signals from the air flow potentiometer and processes and analyzes these signals according to a preset algorithm logic. By sending commands to the servo motor, the position of the blades is adjusted, thereby achieving precise control of air flow. The control module and electronic components involved in this application are all existing mature technologies, with many products on the market. They are all general standard parts or components known to those skilled in the art. Their structure and principles can be learned by those skilled in the art through technical manuals or conventional use. The protection content of this application does not involve improvements to the control module, air flow detection electronic components, or air flow measurement methods. Therefore, the model of the air flow detection electronic components and the control flow of the control system will not be described in detail here. The motor equipment in this application is equipped with a circuit controller and a brake mechanism. The circuit controller allows the motor to flexibly adjust the rotation direction and rotation angle according to actual operating needs, significantly improving the operational flexibility and safety performance of the equipment. The brake mechanism reliably locks the position when the motor stops, preventing accidental displacement caused by inertia and ensuring the stability and safety of the device in the stopped state.

[0013] Preferably, one end of the aero-engine air intake pipe is connected to the aero-engine.

[0014] By adopting the above technical solution, the aero-engine draws in the required air through the intake pipe, ensuring precise control of airflow and purity of air quality, thus providing a strong guarantee for the efficient and stable operation of the aero-engine.

[0015] Preferably, one side of the blade is fitted to the side of the adjusting ring, and the size of the blade is larger than the size of the air intake window.

[0016] With the above technical solution, one side of the blade fits into the side of the regulating ring. This design ensures that it can completely cover or expose the air intake window during rotation, thereby achieving precise adjustment of airflow to meet the airflow requirements of the aero-engine under different operating conditions.

[0017] An adaptive control method for gas environment flow in an aero-engine, using the aforementioned adaptive control device for gas environment flow in an aero-engine, includes the following steps:

[0018] S1. Air flows in from the gas passage 2 of the air intake pipe 1 of the aircraft engine. When it passes through the vent window 4 on the mounting plate 3, the air is drawn in and rushes towards the vent valve 5. Due to the pressure of the air, the vent valve 5 rotates and opens, causing the rotating rod 7 mounted between the support plates 6 to rotate. This causes the sliding arm of the air flow potentiometer 9 to rotate synchronously with the vent valve 5. The opening degree of the vent valve 5 is converted into an electrical signal by the voltage drop of the sliding resistor. This electrical signal is then transmitted to the controller 10.

[0019] S2. The controller 10 can detect the airflow entering the aircraft engine in real time based on the received electrical signal. When the airflow exceeds the preset maximum value, the controller 10 will send a command to the servo motor 19. The servo motor 19 starts, and the gear A20 installed at the end of its power shaft will drive the gear B18 that meshes with it to rotate. Since the gear B18 is installed on the rotating shaft 16, the rotating shaft 16 will rotate with the rotation of the gear B18.

[0020] S3, the rotation of the shaft 16 further drives the rotation of the blade 17 mounted around it. The size of the blade 17 is larger than that of the air inlet window 15. Adjusting the position of the blade 17 increases the area of ​​the blade 17 blocking the air inlet window 15, thereby reducing the airflow entering the aircraft engine. When the airflow is less than the preset minimum value, the controller 10 sends a command to the servo motor 19 again to adjust the position of the blade 17, thereby reducing the area of ​​the blade 17 blocking the air inlet window 15, thereby increasing the airflow entering the aircraft engine. This allows the aircraft engine intake pipe to automatically adjust the amount of air entering the aircraft engine according to the actual airflow requirements.

[0021] S4. By activating the electric telescopic rod 12, the adjusting rod 13 is moved up and down. By adjusting the height of the adjusting rod 13, the vent valve 5 is opened and then abuts against one end of the adjusting rod 13, thereby adjusting the maximum opening of the vent valve 5.

[0022] Compared with the prior art, the beneficial effects of the present invention are as follows: the intake air rushes towards the vent valve, and the opening and closing angle of the vent valve drives the sliding arm of the air flow potentiometer to rotate synchronously with the vent valve, which can detect the air flow entering the aero engine in real time. The controller controls the servo motor to start and drive the blades to rotate according to the received electrical signal, adjusts the position of the blades, and changes the area of ​​the blades blocking the air intake window, thereby adjusting the amount of air intake of the aero engine to adapt to the air intake requirements of the aero engine at different power levels. This allows the aero engine intake pipe to automatically adjust the amount of air entering the aero engine according to the actual air flow requirements, ensuring the stable operation of the aero engine, improving the aero engine's gas environment flow self-adaptation capability, and improving the operating efficiency of the aero engine. Attached Figure Description

[0023] Figure 1 This is a three-dimensional structural diagram of the present invention;

[0024] Figure 2 This is a cross-sectional structural diagram of the present invention;

[0025] Figure 3 This is a schematic diagram of one end face structure of the present invention;

[0026] Figure 4 This is a schematic diagram of the structure of another end face of the present invention.

[0027] In the diagram: 1. Air intake pipe of aircraft engine; 2. Gas passage; 3. Mounting plate; 4. Vent window; 5. Vent valve; 6. Support plate; 7. Rotating rod; 8. Torsion spring; 9. Air flow potentiometer; 10. Controller; 11. Mounting cover; 12. Electric telescopic rod; 13. Adjusting rod; 14. Adjusting ring; 15. Air intake window; 16. Rotating shaft; 17. Blade; 18. Gear B; 19. Servo motor; 20. Gear A; 21. Air filter ring; 22. Air filter screen. Detailed Implementation

[0028] The technical solutions of the present invention will be clearly and completely described below with reference to the accompanying drawings of the embodiments of the present invention. Obviously, the described embodiments are only some embodiments of the present invention, and not all embodiments.

[0029] Please see Figure 1-4An embodiment of the present invention provides an adaptive control device for gas environment flow of an aero-engine, comprising an aero-engine intake pipe 1, an air flow potentiometer 9, a controller 10, blades 17, and an air filter ring 21. The aero-engine intake pipe 1 has a gas channel 2, a mounting plate 3 is disposed in the gas channel 2, an air vent 4 is disposed on the mounting plate 3, a support plate 6 is mounted on the mounting plate 3, a rotating rod 7 is rotatably mounted between the support plates 6, an air vent valve 5 is mounted on the rotating rod 7, a torsion spring 8 and an air flow potentiometer 9 are mounted on the rotating rod 7, an adjusting ring 14 is disposed in the gas channel 2, an air intake window 15 is disposed on the adjusting ring 14, a rotating shaft 16 is rotatably mounted on the side of the adjusting ring 14, blades 17 are mounted around the rotating shaft 16, a gear B18 is mounted at one end of the rotating shaft 16, a servo motor 19 is mounted in the adjusting ring 14, and a gear A20 is mounted at the power shaft end of the servo motor 19, the gear A20 meshing with the gear B18. Air flows in from the gas passage 2 of the air intake pipe 1 of the aircraft engine. When it passes through the vent window 4 on the mounting plate 3, the intake air rushes towards the vent valve 5. Due to the air pressure, the vent valve 5 rotates and opens, causing the rotating rod 7 mounted between the support plates 6 to rotate. This drives the sliding arm of the air flow potentiometer 9 to rotate synchronously with the vent valve 5. The voltage drop of the sliding resistor is used to convert the opening degree of the vent valve 5 into an electrical signal. This electrical signal is then transmitted to the controller 10. Based on the received electrical signal, the controller 10 can detect the air flow entering the aircraft engine in real time. When the air flow exceeds the preset maximum value, the controller 10 will send a command to the servo motor 19. The servo motor 19 starts, and the gear A20 mounted on its power shaft will drive the gear B18 that meshes with it to rotate. Since the gear B18 is mounted on the rotating shaft 16, the rotating shaft 16 will rotate with the rotation of the gear B18. The rotation of the shaft 16 further drives the rotation of the blades 17 mounted around it. The size of the blades 17 is larger than that of the air inlet 15. Adjusting the position of the blades 17 increases the area of ​​the air inlet 15 that the blades 17 cover, thereby reducing the airflow entering the aero-engine. When the airflow is less than the preset minimum value, the controller 10 sends a command to the servo motor 19 again to adjust the position of the blades 17, thereby reducing the area of ​​the air inlet 15 that the blades 17 cover, thereby increasing the airflow entering the aero-engine. This allows the aero-engine intake pipe to automatically adjust the amount of air entering the aero-engine according to the actual airflow requirements, ensuring the stable operation of the aero-engine, improving the aero-engine's gas environment flow self-adaptability, and enhancing the aero-engine's operating efficiency.

[0030] A mounting cover 11 is installed on the air intake pipe 1 of the aero-engine, and an electric telescopic rod 12 is installed in the mounting cover 11. An adjusting rod 13 is installed at one end of the electric telescopic rod 12. By activating the electric telescopic rod 12, the adjusting rod 13 moves up and down. By adjusting the height of the adjusting rod 13, the vent valve 5 is opened and then abuts against one end of the adjusting rod 13, thereby adjusting the maximum opening of the vent valve 5. This provides a dual regulation mechanism for the airflow entering the aero-engine, further enhancing the adaptive capability of the gas flow in the aero-engine air intake pipe and ensuring the stable operation of the aero-engine under various operating conditions.

[0031] An air filter ring 21 is threadedly installed in the gas channel 2, and an air filter screen 22 is provided on the air filter ring 21. The air filter ring 21 is threadedly connected in the gas channel 2, which is convenient for disassembly and replacement. The air filter screen 22 filters the air drawn into the aero-engine intake pipe 1, effectively blocking impurities and dust in the air, ensuring the quality of the air entering the aero-engine, avoiding damage to the aero-engine caused by impurities and dust, and extending the service life of the aero-engine.

[0032] A controller 10 is installed in the air intake pipe 1 of the aero-engine, and the controller 10 is connected to the electronic components in the air intake pipe 1. The controller 10 is responsible for receiving electrical signals from the air flow potentiometer 9, and processing and analyzing these signals according to the preset algorithm logic. By sending instructions to the servo motor 19, the position of the blade 17 is adjusted, thereby achieving precise control of the air flow. The control module and electronic components involved in this application are all existing mature technologies, and there are many products on the market. They are all general standard parts or components known to those skilled in the art. Their structure and principle can be learned by those skilled in the art through technical manuals or conventional use. The protection content of this application does not involve the improvement of the control module, the air flow detection electronic components, or the air flow measurement method. Therefore, the model of the air flow detection electronic components and the control process of the control system will not be described in detail here. The motor equipment in this application is equipped with a circuit controller and a brake mechanism. The circuit controller allows the motor to flexibly adjust the rotation direction and rotation angle according to the actual operation requirements, which significantly improves the operation flexibility and safety performance of the equipment. The brake mechanism reliably locks the motor in position when it stops, preventing accidental displacement due to inertia and ensuring the stability and safety of the device when it is stopped.

[0033] One end of the aero-engine intake pipe 1 is connected to the aero-engine. The aero-engine draws in the required air through this intake pipe, ensuring precise control of airflow and purity of air quality, thus providing a strong guarantee for the efficient and stable operation of the aero-engine.

[0034] One side of the blade 17 is fitted against the side of the adjusting ring 14, and the size of the blade 17 is larger than the size of the air intake window 15. This design ensures that one side of the blade 17 can completely cover or expose the air intake window 15 during rotation, thereby achieving precise adjustment of airflow to meet the airflow requirements of the aero-engine under different operating conditions.

[0035] An adaptive control method for gas environment flow in an aero-engine, using the aforementioned adaptive control device for gas environment flow in an aero-engine, includes the following steps:

[0036] S1. Air flows in from the gas passage 2 of the air intake pipe 1 of the aircraft engine. When it passes through the vent window 4 on the mounting plate 3, the air is drawn in and rushes towards the vent valve 5. Due to the pressure of the air, the vent valve 5 rotates and opens, causing the rotating rod 7 mounted between the support plates 6 to rotate. This causes the sliding arm of the air flow potentiometer 9 to rotate synchronously with the vent valve 5. The opening degree of the vent valve 5 is converted into an electrical signal by the voltage drop of the sliding resistor. This electrical signal is then transmitted to the controller 10.

[0037] S2. The controller 10 can detect the airflow entering the aircraft engine in real time based on the received electrical signal. When the airflow exceeds the preset maximum value, the controller 10 will send a command to the servo motor 19. The servo motor 19 starts, and the gear A20 installed at the end of its power shaft will drive the gear B18 that meshes with it to rotate. Since the gear B18 is installed on the rotating shaft 16, the rotating shaft 16 will rotate with the rotation of the gear B18.

[0038] S3, the rotation of the shaft 16 further drives the rotation of the blade 17 mounted around it. The size of the blade 17 is larger than that of the air inlet window 15. Adjusting the position of the blade 17 increases the area of ​​the blade 17 blocking the air inlet window 15, thereby reducing the airflow entering the aircraft engine. When the airflow is less than the preset minimum value, the controller 10 sends a command to the servo motor 19 again to adjust the position of the blade 17, thereby reducing the area of ​​the blade 17 blocking the air inlet window 15, thereby increasing the airflow entering the aircraft engine. This allows the aircraft engine intake pipe to automatically adjust the amount of air entering the aircraft engine according to the actual airflow requirements.

[0039] S4. By activating the electric telescopic rod 12, the adjusting rod 13 is moved up and down. By adjusting the height of the adjusting rod 13, the vent valve 5 is opened and then abuts against one end of the adjusting rod 13, thereby adjusting the maximum opening of the vent valve 5.

[0040] Working principle: Air flows in from the gas passage 2 of the air intake pipe 1 of the aircraft engine. When it passes through the vent window 4 on the mounting plate 3, the inhaled air rushes towards the vent valve 5. Due to the air pressure, the vent valve 5 rotates and opens, causing the rotating rod 7 mounted between the support plates 6 to rotate. This drives the sliding arm of the air flow potentiometer 9 to rotate synchronously with the vent valve 5. The voltage drop of the sliding resistor is used to convert the opening degree of the vent valve 5 into an electrical signal. This electrical signal is then transmitted to the controller 10. Based on the received electrical signal, the controller 10 can detect the air flow entering the aircraft engine in real time. When the air flow exceeds the preset maximum value, the controller 10 will send a command to the servo motor 19. The servo motor 19 starts, and the gear A20 mounted on its power shaft will drive the gear B18 that meshes with it to rotate. Since the gear B18 is mounted on the rotating shaft 16, the rotating shaft 16 will rotate with the rotation of the gear B18. The rotation of the shaft 16 further drives the rotation of the blades 17 mounted around it. The blades 17 are larger than the air inlet 15. Adjusting the position of the blades 17 increases the area of ​​the blades 17 blocking the air inlet 15, thereby reducing the airflow entering the aero-engine. When the airflow is lower than a preset minimum value, the controller 10 sends another command to the servo motor 19 to adjust the position of the blades 17, reducing the area of ​​the blades 17 blocking the air inlet 15, thereby increasing the airflow entering the aero-engine. This allows the aero-engine intake pipe to automatically adjust the amount of air entering the aero-engine according to the actual airflow requirements, ensuring the stable operation of the aero-engine, improving the aero-engine's gas environment flow self-adaptation capability, and enhancing the aero-engine's operating efficiency. The telescopic rod 12 moves the adjusting rod 13 up and down. By adjusting the height of the adjusting rod 13, the vent valve 5 is opened and then abuts against one end of the adjusting rod 13, thereby adjusting the maximum opening of the vent valve 5. This provides a dual regulation mechanism for the airflow entering the aero-engine, further enhancing the adaptive capability of the aero-engine's intake pipe and ensuring the stable operation of the aero-engine under various operating conditions. The air filter ring 21 is threaded into the gas channel 2 for easy disassembly and replacement. The air filter 22 filters the air drawn into the aero-engine's intake pipe 1, effectively blocking impurities and dust in the air, ensuring the quality of the air entering the aero-engine, avoiding damage to the aero-engine caused by impurities and dust, and extending the service life of the aero-engine.

[0041] It will be apparent to those skilled in the art that the present invention is not limited to the details of the exemplary embodiments described above, and that the invention can be implemented in other specific forms without departing from its spirit or essential characteristics. Therefore, the embodiments should be considered in all respects as exemplary and non-limiting, and the scope of the invention is defined by the appended claims rather than the foregoing description. Thus, all variations falling within the meaning and scope of equivalents of the claims are intended to be included within the present invention. No reference numerals in the claims should be construed as limiting the scope of the claims.

Claims

1. An adaptive control device for gas environment flow in an aero-engine, comprising an aero-engine intake pipe (1), an air flow potentiometer (9), a controller (10), blades (17), and an air filter ring (21), characterized in that: The air intake pipe (1) of the aircraft engine is provided with a gas passage (2), and a mounting plate (3) is provided in the gas passage (2). A vent window (4) is provided on the mounting plate (3). A support plate (6) is installed on the mounting plate (3). A rotating rod (7) is rotatably installed between the support plates (6). A vent valve (5) is installed on the rotating rod (7). A torsion spring (8) and an air flow potentiometer (9) are installed on the rotating rod (7). The gas passage (2) is provided with An adjusting ring (14) is provided, and an air inlet window (15) is provided on the adjusting ring (14). A rotating shaft (16) is rotatably mounted on the side of the adjusting ring (14). A blade (17) is mounted around the rotating shaft (16). A gear B (18) is mounted on one end of the rotating shaft (16). A servo motor (19) is installed in the adjusting ring (14). A gear A (20) is mounted on the power shaft end of the servo motor (19). The gear A (20) meshes with the gear B (18).

2. The adaptive control device for gas environment flow in an aero-engine according to claim 1, characterized in that: An installation cover (11) is installed on the air intake pipe (1) of the aircraft engine. An electric telescopic rod (12) is installed in the installation cover (11). An adjusting rod (13) is installed at one end of the electric telescopic rod (12).

3. The adaptive control device for gas environment flow in an aero-engine according to claim 1, characterized in that: An air filter ring (21) is threadedly installed in the gas channel (2), and an air filter screen (22) is provided on the air filter ring (21).

4. The adaptive control device for gas environment flow in an aero-engine according to claim 1, characterized in that: A controller (10) is installed in the air intake pipe (1) of the aircraft engine, and the controller (10) is connected to the electronic components in the air intake pipe (1) of the aircraft engine.

5. The adaptive control device for gas environment flow in an aero-engine according to claim 1, characterized in that: One end of the aero-engine air intake pipe (1) is connected to the aero-engine.

6. The adaptive control device for gas environment flow in an aero-engine according to claim 1, characterized in that: One side of the blade (17) is attached to the side of the adjusting ring (14), and the size of the blade (17) is larger than the size of the air intake window (15).

7. An adaptive control method for gas environment flow in an aero-engine, characterized in that: The use of an adaptive control device for gas environment flow in an aero-engine according to any one of claims 1-6 includes the following steps: S1. Air flows in from the gas passage (2) of the air intake pipe (1) of the aircraft engine. When it passes through the vent window (4) on the mounting plate (3), the air is drawn in and rushes towards the vent valve (5). Due to the pressure of the air, the vent valve (5) rotates and opens, causing the rotating rod (7) mounted between the support plates (6) to rotate. This causes the sliding arm of the air flow potentiometer (9) to rotate synchronously with the vent valve (5). The opening degree of the vent valve (5) is converted into an electrical signal by the voltage drop of the sliding resistor. This electrical signal is then transmitted to the controller (10). S2. The controller (10) can detect the airflow entering the aircraft engine in real time according to the received electrical signal. When the airflow exceeds the preset maximum value, the controller (10) will send a command to the servo motor (19). The servo motor (19) starts, and the gear A (20) installed on its power shaft will drive the gear B (18) meshing with it to rotate. Since the gear B (18) is installed on the rotating shaft (16), the rotating shaft (16) will rotate with the rotation of the gear B (18). S3. The rotation of the shaft (16) further drives the rotation of the blade (17) mounted around it. The size of the blade (17) is larger than that of the air inlet window (15). Adjusting the position of the blade (17) increases the area of ​​the blade (17) blocking the air inlet window (15), thereby reducing the airflow into the aircraft engine. When the airflow is less than the preset minimum value, the controller (10) sends a command to the servo motor (19) again to adjust the position of the blade (17) so that the area of ​​the blade (17) blocking the air inlet window (15) decreases, thereby increasing the airflow into the aircraft engine. This allows the aircraft engine intake pipe to automatically adjust the amount of air entering the aircraft engine according to the actual airflow requirements. S4. By starting the electric telescopic rod (12), the adjusting rod (13) is moved up and down. By adjusting the height of the adjusting rod (13), the vent valve (5) is rotated and opened to abut against one end of the adjusting rod (13), thereby adjusting the maximum opening of the vent valve (5).

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