A device and method for verifying the function of an air inlet ramp control of an aviation propulsion system

Abstract

The application provides an aviation propulsion system inlet ramp control function verification device and method, and belongs to the technical field of airplane detection. The verification device comprises a computer, a signal machine box, an engine input analog current source and a ramp angle detection platform. The computer and the signal machine box simulate the main control system of an airplane, send instructions to a propulsion system computer to be detected, the engine input analog current source is used for simulating the current when the engine starts, the ramp angle detection platform simulates the rotation of the left and right ramps, and the angle signals are collected through an angle sensor and fed back to the computer to judge the functionality of the propulsion system computer. The application can detect the damaged or malfunctioning propulsion system computer in time, mainly aims at the inlet ramp control function, verifies whether the propulsion system computer can correctly receive the control instruction of the main control computer of the airplane, and whether the inlet ramp angle can be effectively controlled after receiving the instruction.

Description

TECHNICAL FIELD

[0001] The application belongs to the technical field of aircraft detection, and relates to an aviation propulsion system air inlet duct inclined plate control function verification device and method. BACKGROUND

[0002] The propulsion system of an aircraft plays a crucial role in aviation, directly affecting the performance of the aircraft. The propulsion system provides powerful thrust, enabling the aircraft to reach high speeds and perform complex maneuvering actions. An efficient propulsion system enhances the flight performance of the aircraft, including maximum speed, climb rate, and range, which is essential for completing various tasks. In addition, the reliability and safety of the propulsion system are directly related to the safety of the pilot, ensuring stable operation in various harsh environments and emergency situations. In summary, the aircraft propulsion system is the foundation of flight safety.

[0003] The reliability of the propulsion system is directly related to flight safety. During long-distance flights, the propulsion system must remain stable under various complex weather conditions. Modern propulsion systems employ redundant design and advanced monitoring technology to detect and adjust system parameters in real time, ensuring that the system can respond quickly and adjust when encountering failures. Maintenance and inspection of the propulsion system are also important aspects of ensuring its reliability, and regular maintenance and detailed inspection 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 rapid response thrust adjustment, enabling the aircraft to be flexible and maneuverable under complex flight conditions. This is particularly important for pilots when dealing with unexpected situations and complex flight tasks.

[0005] Verification of the control function of the air inlet duct inclined plate is crucial because it directly affects the air intake efficiency and stability of the engine. By precisely adjusting the air intake amount and airflow direction, the air inlet duct inclined plate ensures that the engine obtains the best air supply under various flight conditions, thereby improving thrust output and fuel efficiency. This function verification is crucial for ensuring the overall performance and flight safety of the propulsion system, enabling the early detection and resolution of potential problems, ensuring the reliable operation of the inclined plate control system in actual operation, and thus ensuring the flight performance of the aircraft.

[0006] Firstly, the inlet ramp control function is one of the core components for the stable operation of an aero-engine. During different flight stages such as take-off, 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 optimal working state of the engine, but also effectively prevents airflow separation and turbulence, avoiding engine performance degradation or damage. The functional verification device can simulate various flight environments to test the response ability and adjustment accuracy of the ramp control system under different conditions, ensuring 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 aero-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 found early, so that maintenance and correction can be carried out before the problem worsens, avoiding flight accidents or maintenance caused by system failure, and improving flight safety and economic benefits.

[0008] In addition, the verification of the inlet ramp control function not only involves the testing of hardware, but also includes the verification of software algorithms. The ramp control system is usually managed by a complex electronic control unit (ECU), which realizes 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 summary, the development of a functional verification device for the aero-propulsion system is crucial for verifying the inlet ramp control function. SUMMARY

[0010] The application aims to provide an aero-propulsion system air inlet ramp control function verification device and method, which is mainly used for verifying the air inlet ramp control function and ensuring the efficient operation and reliability of the propulsion system. Specifically, the application is used for verifying whether the propulsion system computer can correctly receive the control instructions from the aircraft main control computer and whether the angle and airflow direction of the air inlet ramp can be accurately controlled after receiving the instructions; through the test, it can be ensured that the air inlet ramp always maintains the optimal angle under different flight conditions, thereby optimizing the air inlet efficiency and engine performance. In addition, the application can also detect and record the response time and accuracy of the air inlet ramp control system, help to 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 found and solved before the propulsion system is installed, ensuring the stability and reliability of the aircraft in actual operation. In summary, the application can not only improve the air inlet efficiency and stability of the engine, ensure the overall performance and flight safety of the propulsion system, but also plays an irreplaceable role in the development, optimization and maintenance of the aero-propulsion system, and guarantees the excellent performance and reliability of the aircraft in complex flight environments.

[0011] An aero-propulsion system air inlet ramp control function verification device is used for verifying the performance of a propulsion system computer 4, which is the main control system of the aircraft propulsion system, and the verification device comprises a computer 1, a signal machine box 2, an engine input analog current source 3 and a ramp angle detection platform 5. The computer 1 and the signal machine box 2 jointly simulate the aircraft main control system, the computer 1 is used for inputting instructions and judging detection results, and the signal machine box 2 is used for converting the input instructions into voltage signals and sending them to the propulsion system computer 4; the engine input analog current source 3 is used for simulating the current when the engine starts and is connected with the propulsion system computer 4; and the ramp angle detection platform 5 receives the signals of the propulsion system computer 4 and simulates the air inlet ramp angle change function.

[0012] The ramp angle detection platform 5 comprises a base 6 and two sets of ramp angle simulation sensing assemblies, each of which comprises a ramp angle moving rod, a sensor support and an angle sensor. The sensor support is installed on the base 6, the ramp angle moving rod is rotationally connected to the sensor support and is used for receiving the signals of the propulsion system computer 4 to simulate the rotation of the ramp, and the angle sensor collects the rotation angle signals of the two ramps.

[0013] The two sets of angle simulation induction components of the inclined plate 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 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 is respectively rotatably connected to the left angle sensor support 8 and the right angle sensor support 11, and the other end of both is provided with a pin, and the two pin ends are respectively clamped into the two arc-shaped grooves on the base 6 for rotation guide. 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 angle of the left inclined plate angle moving rod 7 and the right inclined plate angle moving rod 12 respectively.

[0014] Further, the angle rotation range of the left inclined plate angle moving rod 7 or the right inclined plate angle moving rod 12 is 0-90°.

[0015] Further, 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 1s.

[0016] Further, the computer 1 and the signal box 2 are mainly used for simulating the signal input of the main control system of the airplane, and the signal input can also be directly output by the main control system of the airplane.

[0017] An aviation propulsion system inlet ramp control function verification method is realized based on the above verification device, and the verification method comprises:

[0018] 1) The computer 1 sends a control instruction; 2) the signal box 2 converts the instruction 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 back to the computer 1; 6) the computer 1 judges the functionality of the propulsion system computer 4 through the detection result.

[0019] The beneficial effects of the present application are as follows:

[0020] The present application provides a verification function of the propulsion system computer before the airplane is installed, which can timely detect the damaged or functionally incorrect propulsion system computer, and the functions that can be verified by the present application include the inlet ramp control function. The inlet ramp control function is mainly used for verifying whether the propulsion system computer can correctly receive the control instruction of the main control computer of the airplane and whether the angle of the inlet ramp can be effectively controlled after the instruction is received. BRIEF DESCRIPTION OF DRAWINGS

[0021] Figure 1 This is an overall diagram of the verification device for the control function of the air intake ramp of the aviation propulsion system according to an embodiment of the present invention;

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

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

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

[0025] Figure 5 This is a flowchart of the intake ramp control according to an embodiment of the present invention.

[0026] In the diagram: 1 Computer; 2 Signal housing; 3 Engine input analog current source; 4 Propulsion system computer; 5 Inclined plate angle detection platform; 6 Base; 7 Left inclined plate angle moving rod; 8 Left angle sensor support; 9 Left angle sensor; 10 Right angle sensor; 11 Right angle sensor support; 12 Right inclined plate angle moving rod. Detailed Implementation

[0027] To more clearly illustrate the technical solutions in the embodiments of the present invention or the prior art, the drawings used in the description of the embodiments or the prior art will be briefly introduced below. The drawings described below are only some embodiments of the present invention. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0028] This embodiment provides a verification device for the inlet ramp control function of an aviation propulsion system. The verification device is mainly used for functional verification of the propulsion system computer 4 before its installation, and the verified function includes inlet ramp control. The inlet ramp control function is mainly used to verify whether the propulsion system computer can correctly receive the aircraft's main control calculation and control commands, and whether it can ensure effective control of the inlet ramp angle after receiving the commands.

[0029] like Figure 1 and Figure 4 As shown, the verification device includes: a computer 1, a signal housing 2, an engine input analog current source 3, and a ramp angle detection platform 5. The computer 1 is used to input commands and judge the detection results; the signal housing 2 is used to convert the input commands 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 during engine startup 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 in the air intake.

[0030] As shown in Figure 2 The inclined plate angle detection platform 5 includes a base 6 and two sets of inclined plate angle analog sensing components, and the two sets of inclined plate angle analog 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. The base 6 is symmetrically provided with two arc-shaped grooves on one side, and the left angle sensor support 8 and the right angle sensor support 11 are symmetrically installed side by side in the middle on the other side. 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 at one end, and the other end of each of the left inclined plate angle moving rod 7 and the right inclined plate angle moving rod 12 is provided with a pin, and 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 0-90°. 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] The embodiment also provides an aviation propulsion system air inlet channel inclined plate control function verification method, and the flow thereof is as shown in Figure 5 The verification method comprises the following steps: (1) an operator issues a control instruction on a computer 1, and the instruction is that the left inclined plate angle moving rod 7 is rotated by 45°; (2) the computer 1 issues a digital signal below 5V, and a signal machine box 2 converts the digital signal into a voltage signal with an amplitude of 28V; (3) the voltage signal is transmitted to a propulsion system computer 4, the propulsion system computer 4 calculates that the left inclined plate angle moving rod 7 needs to be rotated by 45°, and transmits the control command of rotating by 45° to the left inclined plate angle moving rod 7; (4) as shown in Figure 3 The left inclined plate angle moving rod 7 is rotated by 45°; (5) the left angle sensor 9 detects that the left inclined plate angle moving rod 7 is rotated by 45°, and then feeds back to the computer 1, and the computer 1 interface shows that the propulsion system computer inclined plate control function is not a problem.

[0032] The above-described embodiments only express the implementation of the present application, but cannot be understood as a limitation on the scope of the present application. It should be pointed out that, for those skilled in the art, without departing from the concept of the present application, a number of modifications and improvements can be made, which all belong to the protection scope of the present application.

Claims

1. An aircraft propulsion system inlet ramp control function verification device for verifying 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 analog current source (3), and a slope plate 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 for inputting instructions and judging detection results, and the signal box (2) is used for converting the input instructions into voltage signals and sending the voltage signals to a propulsion system computer (4); the engine input analog current source (3) is used for simulating current during engine starting and is connected with the propulsion system computer (4); and the slope plate angle detection platform (5) receives signals of the propulsion system computer (4) and simulates an air inlet channel slope plate angle change function. The slope plate angle detection platform (5) comprises a base (6) and two sets of slope plate angle simulation sensing components, each of the two sets of slope plate angle simulation sensing components comprises a slope plate angle moving rod, a sensor support and an angle sensor, the sensor support is installed on the base (6), the slope plate angle moving rod is rotationally connected to the sensor support, is used for receiving signals of the propulsion system computer (4) to simulate slope plate rotation, and the angle sensor is used for collecting rotation angle signals of the two slope plates. Two arc-shaped grooves are symmetrically arranged on one side of the base (6), a left angle sensor support (8) and a right angle sensor support (11) are symmetrically installed side by side on the middle of the other side of the base (6), a left slope plate angle moving rod (7) and a right slope plate angle moving rod (12) are rotationally connected to the left angle sensor support (8) and the right angle sensor support (11) respectively at one end, pins are installed at the other ends of the left slope plate angle moving rod (7) and the right slope plate angle moving rod (12), and the two pins are respectively clamped into the two arc-shaped grooves on the base (6) to guide rotation.

2. An aircraft propulsion system inlet ramp control function verification apparatus according to claim 1, wherein, The two sets of slope plate angle simulation sensing components respectively comprise the left slope plate angle moving rod (7), the left angle sensor support (8), a left angle sensor (9), a right angle sensor (10), the right angle sensor support (11) and the right slope plate angle moving rod (12); the left angle sensor support (8) and the right angle sensor support (11) are installed on the base (6), the left slope plate angle moving rod (7) and the right slope plate angle moving rod (12) are rotationally connected to the left angle sensor support (8) and the right angle sensor support (11) respectively, and the left angle sensor (9) and the right angle sensor (10) are installed on the left angle sensor support (8) and the right angle sensor support (11) respectively to detect rotation angles of the left slope plate angle moving rod (7) and the right slope plate angle moving rod (12) respectively.

3. An aircraft propulsion system inlet ramp control function verification apparatus according to claim 2, wherein, The left slope plate angle moving rod (7) or the right slope plate angle moving rod (12) rotates in an angle range of 0-90°.

4. The device according to claim 2, wherein The left angle sensor (9) and the right angle sensor (10) have a detection response time less than 1s.

5. The device according to claim 1, wherein The computer (1) and the signal box (2) are replaced by an aircraft main control system.

6. A method for verifying the function of a ramp control of an air intake of an aircraft propulsion system, implemented on the basis of a verification device according to any one of claims 1 to 5, characterized in that, The verification method comprises: 1) the computer (1) sends control instructions; 2) the signal box (2) converts the instructions into voltage signals; 3) the voltage signals are transmitted to the propulsion system computer (4), which calculates the rotation angle; 4) the left or right angle moving rod (7) or (12) rotates according to the calculation result; 5) the left or right angle sensor (9) or (10) detects the angle change and feeds back to the computer (1); 6) the computer (1) judges the functionality of the propulsion system computer (4) through the detection result.

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