Aviation propulsion system air inlet channel inclined plate control function verification device and method

Abstract

The invention provides an aviation propulsion system air inlet channel inclined plate control function verification device and method, and belongs to the technical field of aircraft detection, the verification device comprises a computer, a signal case, an engine input simulation current source and an inclined plate angle detection platform, and the computer and the signal case simulate an aircraft master control system. An instruction is sent to a to-be-detected propulsion system computer, the engine input simulation current source is used for simulating current when an engine is started, the inclined plate angle detection platform simulates rotation of a left inclined plate and a right inclined plate, and angle signals are collected through an angle sensor and fed back to the computer to judge the functionality of the propulsion system computer. The method can timely detect the damaged or function error propulsion system computer, mainly aims at the air inlet channel inclined plate control function, and verifies whether the propulsion system computer can correctly receive an airplane main control calculation control instruction and whether the effective control of the angle of the air inlet channel inclined plate can be ensured after the instruction is received.

Description

Technical Field

[0001] The invention belongs to the technical field of aircraft detection, and relates to a device and method for verifying the control function of an inlet ramp of an aviation propulsion system. Background Art

[0002] The propulsion system of an aircraft plays a vital role in aviation and directly affects the performance of the aircraft. The propulsion system provides powerful thrust, allowing the aircraft to reach high speeds and perform complex maneuvers. An efficient propulsion system improves the flight performance of the aircraft, including maximum speed, climb rate, and range, which is essential for completing various missions. In addition, the reliability and safety of the propulsion system are directly related to the life safety of the pilot, ensuring stable operation in various harsh environments and emergency situations. In short, the aircraft propulsion system is the basis for achieving flight safety.

[0003] The reliability of the propulsion system is directly related to flight safety. During long-distance flights, the propulsion system must maintain stable operation under various complex weather conditions. Modern propulsion systems use redundant designs and advanced monitoring technologies to detect and adjust system parameters in real time to ensure that the system can respond and adjust quickly when encountering failures. The maintenance and inspection of the propulsion system is also an important part of ensuring its reliability. Regular maintenance and detailed inspections can prevent potential problems and ensure that the system is in optimal condition.

[0004] In addition, the propulsion system also plays an important role in the maneuverability and controllability of the aircraft. An efficient propulsion system can provide fast-response thrust adjustment, allowing the aircraft to be flexible and maneuverable under complex flight conditions. This is especially important for pilots when dealing with emergencies and complex flight missions.

[0005] The verification of the inlet ramp control function is crucial because it directly affects the engine's intake efficiency and stability. By precisely adjusting the intake volume and airflow direction, the inlet ramp ensures that the engine obtains the best air supply under various flight conditions, thereby improving thrust output and fuel efficiency. This functional verification is crucial to ensuring the overall performance and flight safety of the propulsion system. It can detect and solve potential problems in advance, ensure that the ramp control system operates reliably in actual operation, and thus guarantee the aircraft's flight performance.

[0006] First of all, the inlet ramp control function is one of the core components for the stable operation of aircraft engines. During different flight phases of the aircraft, such as takeoff, climb, cruise and landing, the inlet ramp needs to adjust its angle and position in real time according to flight conditions to optimize air flow. This not only helps to maintain the best working state of the engine, but also effectively prevents the occurrence of airflow separation and turbulence, avoiding engine performance degradation or damage. The functional verification device can simulate various flight environments and test the responsiveness and adjustment accuracy of the ramp control system under different conditions, so as to ensure its reliable operation in actual flight.

[0007] Secondly, the verification device of the inlet ramp control function also plays a key role in maintenance and fault diagnosis. The complexity and high requirements of the aviation propulsion system determine that it must have high reliability and long service life. Through regular testing and monitoring, potential problems of the ramp control system, such as mechanical wear, electrical failure or control algorithm deviation, can be discovered early, so that maintenance and correction can be carried out before the problem worsens, avoiding flight accidents or downtime maintenance caused by system failures, and improving flight safety and economic benefits.

[0008] In addition, the verification of the inlet ramp control function involves not only hardware testing, but also software algorithm verification. The ramp control system is usually managed by a complex electronic control unit (ECU), which achieves precise control through real-time calculation and feedback adjustment. The device for functional verification of the ramp control system needs to have the ability to simulate and test these control algorithms, verify their stability and reliability under different flight conditions, and ensure that the ramp control system can respond quickly and accurately in various situations.

[0009] In conclusion, the development of a functional verification device for aviation propulsion systems is crucial to verify the control function of the inlet ramp. Summary of the invention

[0010] The purpose of the present invention is to provide an inlet ramp control function verification device and method for an aviation propulsion system, which is mainly used to verify the inlet ramp control function and ensure the efficient operation and reliability of the propulsion system. Specifically, the present invention is used to verify whether the propulsion system computer can correctly receive the control instructions of the aircraft main control computer, and whether it can accurately control the angle and airflow direction of the inlet ramp after receiving the instructions; through testing, it can be ensured that the inlet ramp always maintains the optimal angle under different flight conditions, thereby optimizing the intake efficiency and engine performance. In addition, the present invention can also detect and record the response time and accuracy of the inlet ramp control system, help identify and eliminate potential control problems, which not only improves the overall performance of the propulsion system, but also enhances the flight safety of the aircraft. Through this comprehensive functional verification, potential problems can be discovered and solved before the propulsion system is installed, ensuring the stability and reliability of the aircraft in actual operation. In short, the present invention can not only improve the intake efficiency and stability of the engine, ensure the overall performance and flight safety of the propulsion system, but also play an irreplaceable role in the development, optimization and maintenance of the aviation propulsion system, and ensure the excellent performance and reliability of the aircraft in a complex flight environment.

[0011] A device for verifying the control function of an inlet ramp of an aviation propulsion system is used to verify the performance of a propulsion system computer 4, which is the aircraft propulsion system main control system. The verification device includes: a computer 1, a signal chassis 2, an engine input simulation current source 3, and a ramp angle detection platform 5. The computer 1 and the signal chassis 2 jointly simulate the aircraft main control system. The computer 1 is used to input instructions and judge the detection results, and the signal chassis 2 is used to convert the input instructions into voltage signals and send them to the propulsion system computer 4; the engine input simulation current source 3 is used to simulate the current when the engine is started, and is connected to the propulsion system computer 4; the ramp angle detection platform 5 receives the signal of the propulsion system computer 4 and simulates the function of changing the inlet ramp angle.

[0012] The inclined plate angle detection platform 5 includes a base 6 and two sets of inclined plate angle simulation sensing components. The two sets of inclined plate angle simulation sensing components include an inclined plate angle moving rod, a sensor support and an angle sensor. The sensor support is installed on the base 6. The inclined plate angle moving rod is rotatably connected to the sensor support and is used to receive the signal of the propulsion system computer 4 to simulate the rotation of the inclined plate. The angle sensor collects the rotation angle signal of the two inclined plates. Specifically:

[0013] The two sets of inclined plate angle simulation sensing components respectively include a left inclined plate angle moving rod 7, a left angle sensor support 8, a left angle sensor 9, a right angle sensor 10, a right angle sensor support 11, and a right inclined plate angle moving rod 12. Two arc-shaped grooves are symmetrically arranged on one side of the base 6, and the left angle sensor support 8 and the right angle sensor support 11 are symmetrically installed side by side in the middle of the other side. One end of the left inclined plate angle moving rod 7 and the right inclined plate angle moving rod 12 are rotatably connected to the left angle sensor support 8 and the right angle sensor support 11 respectively, and the other ends of both are installed with pins, and the ends of the two pins are respectively stuck in the two arc-shaped grooves on the base 6 for rotation guidance. The left angle sensor 9 and the right angle sensor 10 are respectively installed on the left angle sensor support 8 and the right angle sensor support 11 to detect the rotation angles of the left inclined plate angle moving rod 7 and the right inclined plate angle moving rod 12 respectively.

[0014] Furthermore, the angle rotation range of the left inclined plate angle moving rod 7 or the right inclined plate angle moving rod 12 is 0 to 90 degrees.

[0015] Furthermore, the left angle sensor 9 detects the angle change of the left inclined plate angle moving rod 7, and the right angle sensor 10 detects the angle change of the right inclined plate angle moving rod 12, and the detection response time is less than 1 s.

[0016] Furthermore, the computer 1 and the signal box 2 are mainly used to simulate the signal input of the aircraft main control system, and the signal input can also be directly output by the aircraft main control system.

[0017] A method for verifying the control function of an inlet ramp of an aviation propulsion system is implemented based on the above verification device, and the verification method comprises:

[0018] 1) Computer 1 issues a control command; 2) Signal box 2 converts the command into a voltage signal; 3) The voltage signal is transmitted to the propulsion system computer 4, and the propulsion system computer 4 calculates the rotation angle; 4) The left inclined plate angle moving rod 7 or the right inclined plate angle moving rod 12 rotates according to the calculated result; 5) The left angle sensor 9 or the right angle sensor 10 detects the angle change and feeds it back to computer 1; 6) Computer 1 determines the functionality of the propulsion system computer 4 based on the detection result.

[0019] Beneficial effects of the present invention:

[0020] The present invention provides a verification function for the propulsion system computer before installation on the aircraft, which can timely detect the damaged or malfunctioning propulsion system computer. The functions that can be verified by the present invention include the inlet ramp control function. The inlet ramp control function is mainly used to verify whether the propulsion system computer can correctly receive the aircraft main control calculation control instruction, and whether the inlet ramp angle can be effectively controlled after receiving the instruction. BRIEF DESCRIPTION OF THE DRAWINGS

[0021] Figure 1 : is an overall diagram of a device for verifying the control function of an inlet ramp plate of an aviation propulsion system according to an embodiment of the present invention;

[0022] Figure 2 is a composition diagram of an inclined plate angle detection platform according to an embodiment of the present invention;

[0023] Figure 3 is a schematic diagram of the left inclined plate angle moving rod rotating 45 degrees according to an embodiment of the present invention;

[0024] Figure 4 is a schematic diagram of the intake slant plate control according to an embodiment of the present invention;

[0025] Figure 5 4 is a flow chart of the intake slant plate control according to an embodiment of the present invention.

[0026] In the figure: 1 computer; 2 signal chassis; 3 engine input analog current source; 4 propulsion system computer; 5 ramp angle detection platform; 6 base; 7 left ramp angle moving rod; 8 left angle sensor support; 9 left angle sensor; 10 right angle sensor; 11 right angle sensor support; 12 right ramp angle moving rod. DETAILED DESCRIPTION

[0027] In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings required for use in the embodiments or the description of the prior art will be briefly introduced below. The drawings described below are only some embodiments of the present invention. For ordinary technicians in this field, other drawings can be obtained based on these drawings without paying creative labor.

[0028] This embodiment provides an inlet ramp control function verification device for an aviation propulsion system, which is mainly used for function verification of the propulsion system computer 4 before installation, and the verified functions include inlet ramp control. The inlet ramp control function is mainly used to verify whether the propulsion system computer can correctly receive the aircraft main control calculation control command, and whether the inlet ramp angle can be effectively controlled after receiving the command.

[0029] like Figure 1 and Figure 4 As shown, the verification device includes: a computer 1, a signal box 2, an engine input analog current source 3, and a ramp angle detection platform 5. The computer 1 is used to input instructions and judge the detection results; the signal box 2 is used to convert the input instructions into voltage signals and send them to the propulsion system computer 4; the engine input analog current source 3 is used to simulate the current when the engine is started, and is connected to the propulsion system computer 4; the ramp angle detection platform 5 receives the signal of the propulsion system computer 4 and simulates the function of the change of the inlet ramp angle.

[0030] like Figure 2 As shown, the inclined plate angle detection platform 5 includes a base 6 and two sets of inclined plate angle simulation sensing components, and the two sets of inclined plate angle simulation sensing components respectively include a left inclined plate angle moving rod 7, a left angle sensor support 8, a left angle sensor 9 and a right angle sensor 10, a right angle sensor support 11, and a right inclined plate angle moving rod 12. Two arc-shaped grooves are symmetrically arranged on one side of the base 6, and a left angle sensor support 8 and a right angle sensor support 11 are symmetrically installed side by side in the middle of the other side. One end of the left inclined plate angle moving rod 7 and the right inclined plate angle moving rod 12 are respectively rotatably connected to the left angle sensor support 8 and the right angle sensor support 11, and pins are installed at the other ends of both. The ends of the two pins are respectively inserted into the two arc-shaped grooves on the base 6 for rotation guidance. The angle rotation range of the left inclined plate angle moving rod 7 or the right inclined plate angle moving rod 12 is 0 to 90°. The left angle sensor 9 and the right angle sensor 10 are respectively installed on the left angle sensor support 8 and the right angle sensor support 11. The left angle sensor 9 detects the angle change of the left inclined plate angle moving rod 7, and the right angle sensor 10 detects the angle change of the right inclined plate angle moving rod 12. The detection response time is less than 1s.

[0031] This embodiment also provides a method for verifying the control function of the inlet ramp of an aviation propulsion system, and the process is as follows: Figure 5 As shown, the verification method includes: (1) the operator issues a control command on the computer 1, the command is that the left inclined plate angle moving rod 7 rotates 45°; (2) the computer 1 sends a digital signal below 5V, and the signal box 2 converts the digital signal into a voltage signal with an amplitude of 28V; (3) the voltage signal is transmitted to the propulsion system computer 4, the propulsion system computer 4 solves that the left inclined plate angle moving rod 7 needs to rotate 45°, and transmits the control command of rotating 45° to the left inclined plate angle moving rod 7; (4) Figure 3 As shown, the left inclined plate angle moving rod 7 rotates 45°; (5) the left angle sensor 9 detects that the left inclined plate angle moving rod 7 rotates 45°, and then feeds back to the computer 1. The computer 1 interface shows that there is no problem with the propulsion system computer inclined plate control function.

[0032] The above-described embodiments merely express the implementation methods of the present invention, but they should not be understood as limiting the scope of the present invention. It should be pointed out that for those skilled in the art, several modifications and improvements can be made without departing from the concept of the present invention, which all belong to the protection scope of the present invention.

Claims

1. An aviation propulsion system inlet ramp control function verification device, used to verify the performance of a propulsion system computer (4), characterized in that: The verification device comprises: a computer (1), a signal box (2), an engine input simulation current source (3), and a ramp angle detection platform (5); wherein the computer (1) and the signal box (2) jointly simulate an aircraft main control system, the computer (1) is used to input instructions and judge detection results, and the signal box (2) is used to convert the input instructions into voltage signals and send them to a propulsion system computer (4); the engine input simulation current source (3) is used to simulate the current when the engine is started, and is connected to the propulsion system computer (4); the ramp angle detection platform (5) receives signals from the propulsion system computer (4) and simulates the function of changing the ramp angle of the air inlet duct.

2. The device for verifying the control function of the inlet ramp of an aviation propulsion system according to claim 1, characterized in that: The inclined plate angle detection platform (5) comprises a base (6) and two sets of inclined plate angle simulation sensing components, both sets of inclined plate angle simulation sensing components comprise an inclined plate angle moving rod, a sensor support and an angle sensor, the sensor support is mounted on the base (6), the inclined plate angle moving rod is rotatably connected to the sensor support and is used to receive signals from a propulsion system computer (4) to simulate the rotation of the inclined plate, and the angle sensor collects the rotation angle signals of the two inclined plates.

3. The device for verifying the control function of the inlet ramp of an aviation propulsion system according to claim 2, characterized in that: The two sets of inclined plate angle simulation sensing components respectively comprise a left inclined plate angle moving rod (7), a left angle sensor support (8), a left angle sensor (9), a right angle sensor (10), a right angle sensor support (11), and a right inclined plate angle moving rod (12); the left angle sensor support (8) and the right angle sensor support (11) are mounted on the base (6); the left inclined plate angle moving rod (7) and the right inclined plate angle moving rod (12) are respectively rotatably connected to the left angle sensor support (8) and the right angle sensor support (11); the left angle sensor (9) and the right angle sensor (10) are respectively mounted on the left angle sensor support (8) and the right angle sensor support (11) to respectively detect the rotation angles of the left inclined plate angle moving rod (7) and the right inclined plate angle moving rod (12).

4. The device for verifying the control function of the inlet ramp of an aviation propulsion system according to claim 1, characterized in that: Two arc-shaped grooves are symmetrically arranged on one side of the base (6), and a left angle sensor support (8) and a right angle sensor support (11) are symmetrically installed side by side in the middle of the other side. One end of the left inclined plate angle moving rod (7) and the right inclined plate angle moving rod (12) are respectively rotatably connected to the left angle sensor support (8) and the right angle sensor support (11), and the other ends of both are installed with pins, and the ends of the two pins are respectively inserted into the two arc-shaped grooves on the base (6) for rotation guidance.

5. The device for verifying the control function of the inlet ramp of an aviation propulsion system according to claim 3, characterized in that: The angle rotation range of the left inclined plate angle moving rod (7) or the right inclined plate angle moving rod (12) is 0 to 90 degrees.

6. The device for verifying the control function of the inlet ramp of an aviation propulsion system according to claim 3, characterized in that: The detection response time of the left angle sensor (9) and the right angle sensor (10) is less than 1 second.

7. The device for verifying the control function of the inlet ramp of an aviation propulsion system according to claim 1, characterized in that: The computer (1) and the signal box (2) are replaced by the aircraft main control system.

8. A method for verifying the control function of an inlet ramp of an aviation propulsion system, implemented based on the verification device according to any one of claims 1 to 7, characterized in that: The verification method includes: 1) The computer (1) issues a control command; 2) The signal box (2) converts the command into a voltage signal; 3) The voltage signal is transmitted to the propulsion system computer (4), and the propulsion system computer (4) calculates the rotation angle; 4) The left inclined plate angle moving rod (7) or the right inclined plate angle moving rod (12) rotates according to the calculation result; 5) The left angle sensor (9) or the right angle sensor (10) detects the angle change and feeds it back to the computer (1); 6) The computer (1) determines the functionality of the propulsion system computer (4) based on the detection result.

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