An engine inlet passage ice prevention control method and system

Abstract

The present application relates to the field of airborne electromechanical comprehensive control and management, and provides an engine air inlet anti-icing control method and system, the present application drives the engine air inlet icing sensor to work, collects and solves the resonant frequency signal output by the icing sensor which changes with the thickness of the ice layer, and controls the vibration head heating and support heating, to realize the engine air inlet icing monitoring and deicing control functions. The technical purpose of improving the control precision and intelligent level of the engine air inlet anti-icing is achieved, and the technical problem of low control precision and intelligent level caused by the conversion control link and monitoring components of the icing sensor in the prior art is solved.

Description

Technical Field

[0001] This invention relates to the field of airborne electromechanical integrated control and management, and in particular to an engine intake anti-icing control method and system. Background Technology

[0002] In the aircraft electromechanical management subsystem, monitoring and de-icing of engine inlet icing is one of its key tasks. When an engine is flying at high altitudes or in cold regions, its inlet is prone to icing. Once the engine's air inlet is icy, it affects the engine's intake conditions. If the icing continues, ice particles may enter the engine's intake duct, potentially causing engine blade breakage. This could result in fatal damage to the engine during high-altitude flight. Traditional methods for monitoring and de-icing engine inlet icing have significant drawbacks: they are affected by the switching control links of icing sensors and the monitoring components, resulting in low control accuracy and a low level of intelligence. Summary of the Invention

[0003] In view of this, embodiments of the present invention provide an engine intake anti-icing control method to solve the technical problems of low control accuracy and intelligence level in the prior art due to the influence of the conversion control link and monitoring components of the icing sensor. The method employs an excitation circuit, a data acquisition circuit, an icing sensor, and an FPGA, wherein the FPGA is connected to the automatic anti-icing system and the avionics system respectively. The method includes:

[0004] An excitation signal is output from the excitation circuit and sent to the icing sensor.

[0005] The icing sensor outputs an AC resonant frequency signal according to the excitation signal;

[0006] The acquisition circuit converts the AC resonant frequency signal into a rectangular wave. The FPGA calculates the frequency value based on the rectangular wave and determines whether to output an icing signal based on the frequency value.

[0007] If the FPGA outputs the icing signal, the icing signal is sent to the avionics system.

[0008] Furthermore, the acquisition circuit has an acquisition period of 10ms for the AC resonant frequency signal.

[0009] Furthermore, the FPGA calculates the frequency value based on the rectangular wave using a fixed-frequency counting method.

[0010] Furthermore, the FPGA has an automatic anti-icing state machine, which calculates the frequency value based on the rectangular wave.

[0011] Furthermore, if the frequency value is higher than 6015Hz, the automatic anti-icing state machine outputs a de-icing control command to the automatic anti-icing system.

[0012] Furthermore, when the frequency value is below 6015Hz, the automatic anti-icing state machine controls the de-icing control command to be cancelled.

[0013] Furthermore, if the frequency value remains above 6015Hz during the delay process, the automatic anti-icing state machine outputs the de-icing control command to the automatic anti-icing system.

[0014] Furthermore, the automatic anti-icing system includes vibration head heating control and bracket heating control.

[0015] Furthermore, if the heating time of the vibrating head continues to reach 40 seconds, the automatic anti-icing state machine controls the automatic anti-icing system to stop starting. After 40 seconds, if the frequency value continues to be higher than 6015Hz, the automatic anti-icing system will stop starting.

[0016] Furthermore, the present invention also provides an engine intake anti-icing control system, comprising:

[0017] The excitation signal acquisition module is used to output an excitation signal from the excitation circuit and send the excitation signal to the icing sensor;

[0018] A resonant signal acquisition module is used for the icing sensor to output an AC resonant frequency signal according to the excitation signal;

[0019] The frequency value acquisition module is used to acquire the AC resonant frequency signal by converting it into a rectangular wave. The FPGA calculates the frequency value based on the rectangular wave and determines whether to output an icing signal based on the frequency value.

[0020] An icing signal acquisition module is used to send the icing signal to the avionics system if the FPGA outputs the icing signal.

[0021] Compared with the prior art, the beneficial effects achieved by at least one of the above-mentioned technical solutions adopted in the embodiments of this specification include at least the following: This invention provides an engine intake duct anti-icing control method. This invention drives an engine intake duct icing sensor to operate, collects and calculates the resonant frequency signal output by the icing sensor that varies with the ice layer thickness, and controls the heating of the vibrating head and the support, thereby realizing the functions of engine intake duct icing monitoring and de-icing control. This achieves the technical objective of improving the control accuracy and intelligence level of engine intake duct anti-icing. Attached Figure Description

[0022] To more clearly illustrate the technical solutions of the embodiments of this application, the drawings used in the embodiments will be briefly introduced below. Obviously, the drawings described below are only some embodiments of this application. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0023] Figure 1 This is an architecture diagram of an engine intake anti-icing control method provided in an embodiment of the present invention;

[0024] Figure 2 This is a schematic diagram of the automatic anti-icing state machine provided in an embodiment of the present invention;

[0025] Figure 3 This is a structural diagram of an engine intake anti-icing control system provided in an embodiment of the present invention.

[0026] The attached figures are labeled as follows: 300, System; 301, Excitation signal acquisition module; 302, Resonance signal acquisition module; 303, Frequency value acquisition module; 304, Icing signal acquisition module. Detailed Implementation

[0027] The embodiments of this application will now be described in detail with reference to the accompanying drawings.

[0028] The following specific examples illustrate the implementation of this application. Those skilled in the art can easily understand other advantages and effects of this application from the content disclosed in this specification. Obviously, the described embodiments are only a part of the embodiments of this application, and not all of them. This application can also be implemented or applied through other different specific embodiments, and the details in this specification can also be modified or changed based on different viewpoints and applications without departing from the spirit of this application. It should be noted that, in the absence of conflict, the following embodiments and features in the embodiments can be combined with each other. Based on the embodiments in this application, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of this application.

[0029] This invention provides an engine inlet anti-icing control method, employing an excitation circuit, a data acquisition circuit, an icing sensor, and an FPGA. The FPGA is connected to both an automatic anti-icing system and an avionics system. The engine inlet anti-icing control method includes:

[0030] Step S100: The excitation circuit outputs an excitation signal and sends the excitation signal to the icing sensor;

[0031] Step S200: The icing sensor outputs an AC resonant frequency signal according to the excitation signal;

[0032] Step S300: The acquisition circuit converts the AC resonant frequency signal into a rectangular wave, the FPGA calculates the frequency value based on the rectangular wave, and determines whether to output an icing signal based on the frequency value;

[0033] Step S400: If the FPGA outputs the icing signal, the icing signal is sent to the avionics system.

[0034] Specifically, the architecture diagram of the engine intake anti-icing control method is as follows: Figure 1 As shown, the system includes an excitation circuit, a data acquisition circuit, an icing sensor, and an FPGA. The FPGA is connected to both the automatic anti-icing system and the avionics system. The FPGA contains an automatic anti-icing state machine. The automatic anti-icing system includes vibration head heating control and support heating control. The icing sensor is connected to both the data acquisition circuit and the automatic anti-icing system. The signal processing functions of the data acquisition circuit include phase shifting, signal amplification, gain control, and waveform transformation.

[0035] Furthermore, the icing sensor is driven by an internal excitation circuit that outputs an excitation signal. The icing sensor outputs an AC resonant frequency signal that varies with the ice thickness. This AC resonant frequency signal is a sine wave, which is converted into a rectangular wave after phase shifting, signal amplification, gain control, and waveform transformation by the acquisition circuit. The frequency is measured as parallel data using the FPGA's fixed-frequency counting method. The application software calculates the icing signal based on the parallel data and sends the icing alarm to the avionics system for display. The automatic anti-icing state machine is located inside the FPGA and performs frequency value calculations. A schematic diagram of the automatic anti-icing state machine is shown below. Figure 2 As shown. When the resonant frequency detected by the automatic anti-icing state machine is higher than 6015Hz, it outputs a de-icing control command; when the resonant frequency is lower than 6015Hz, the above commands are canceled after a delay; if the resonant frequency is higher than 6015Hz during the continuous process, the automatic anti-icing system is activated and continues; if the heating time of the vibrating head reaches 40s during the above process, the output of the de-icing control command stops; thereafter, if the resonant frequency remains higher than 6015Hz, the automatic anti-icing system will not be activated again to avoid damaging the vibrating head and the icing sensor.

[0036] Preferably, in order to reliably remove ice from the vibrator head and form a continuous anti-icing signal, when the aircraft is flying in an icing area, the command to turn off the vibrator head heating will be delayed by 8 seconds, while the command to turn off the anti-icing system heating and the support heating will be delayed by 140 seconds.

[0037] Based on the same inventive concept, this invention also provides an engine intake manifold anti-icing control system, as described in the following embodiments. Since the principle of solving the problem in an engine intake manifold anti-icing control system is similar to that of an engine intake manifold anti-icing control method, the implementation of an engine intake manifold anti-icing control system can refer to the implementation of an engine intake manifold anti-icing control method; repeated details will not be elaborated further. As used below, the terms "unit" or "module" can refer to a combination of software and / or hardware that performs a predetermined function. Although the system described in the following embodiments is preferably implemented in software, hardware implementation, or a combination of software and hardware, is also possible and contemplated.

[0038] like Figure 3 As shown, the present invention also provides an engine intake anti-icing control system, comprising:

[0039] The excitation signal acquisition module 301 is used to output an excitation signal from the excitation circuit and send the excitation signal to the icing sensor;

[0040] The resonant signal acquisition module 302 is used for the icing sensor to output an AC resonant frequency signal according to the excitation signal;

[0041] The frequency value acquisition module 303 is used to acquire the AC resonant frequency signal by converting it into a rectangular wave, and the FPGA calculates the frequency value based on the rectangular wave and determines whether to output an icing signal based on the frequency value.

[0042] The icing signal acquisition module 304 is used to send the icing signal to the avionics system if the FPGA outputs the icing signal.

[0043] The embodiments of the present invention achieve the following technical effects:

[0044] This invention designs an anti-icing control method and system for engine intake ducts. By using artificial intelligence methods and historical data of system operation, a container fault early warning model is designed. This model can monitor the real-time operating status of containers and provide early warnings for containers that may fail, so that the management system can take measures in advance, such as activating backup containers, to ensure the safe operation of the application and greatly improve the reliability and safety of the system.

[0045] The above description is merely a preferred embodiment of the present invention and is not intended to limit the present invention. For those skilled in the art, various modifications and variations can be made to the embodiments of the present invention. Any modifications, equivalent substitutions, improvements, etc., made within the spirit and principles of the present invention should be included within the protection scope of the present invention.

Claims

1. A method for controlling anti-icing in an engine intake manifold, characterized in that, The method employs an excitation circuit, a data acquisition circuit, an icing sensor, and an FPGA, wherein the FPGA is connected to both an automatic anti-icing system and an avionics system. An excitation signal is output from the excitation circuit and sent to the icing sensor. The icing sensor outputs an AC resonant frequency signal according to the excitation signal; The acquisition circuit converts the AC resonant frequency signal into a rectangular wave. The FPGA calculates the frequency value based on the rectangular wave and determines whether to output an icing signal based on the frequency value. If the FPGA outputs the icing signal, the icing signal is sent to the avionics system; The FPGA calculates the frequency value based on the rectangular wave using a fixed-frequency counting method, and the FPGA has an internal automatic anti-icing state machine. When the frequency value is higher than 6015Hz, the automatic anti-icing state machine outputs a de-icing control command to the automatic anti-icing system; when the frequency value is lower than 6015Hz, the automatic anti-icing state machine cancels the de-icing control command.

2. The engine intake duct anti-icing control method according to claim 1, characterized in that, The acquisition circuit has an acquisition period of 10ms for the AC resonant frequency signal.

3. The engine intake duct anti-icing control method according to claim 1, characterized in that, The automatic anti-icing system includes vibration head heating control and bracket heating control.

4. An engine intake duct anti-icing control system, characterized in that, include: The excitation signal acquisition module is used to output an excitation signal from the excitation circuit and send the excitation signal to the icing sensor; A resonant signal acquisition module is used for the icing sensor to output an AC resonant frequency signal according to the excitation signal; The frequency value acquisition module is used to acquire the AC resonant frequency signal by converting it into a rectangular wave. The frequency value is then calculated by the FPGA based on the rectangular wave. The FPGA also has an automatic anti-icing state machine. An icing signal acquisition module is used by the FPGA to calculate the frequency value based on the rectangular wave using a fixed-frequency counting method. When the frequency value is higher than 6015Hz, the automatic anti-icing state machine outputs a de-icing control command to the automatic anti-icing system. When the frequency value is lower than 6015Hz, the automatic anti-icing state machine controls the de-icing control command to be canceled.

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