Asymmetric fault fusion detection method and system for high lift system

Abstract

The invention belongs to the technical field of aircraft control, and particularly relates to an asymmetric fault fusion detection method and system for a high lift system, and the method comprises the following steps: 1, monitoring the position of a high lift airfoil on line through a high lift airfoil position sensor, and enabling the position to comprise the deflection angle of the high lift airfoil; the position difference of the left and right high-lift airfoils is calculated, and when the position difference of the left and right high-lift airfoils exceeds a threshold value, the system generates an asymmetric fault signal 1; step 2, acquiring an aileron level flight compensation angle, and comparing the aileron rudder output of one side with a relatively small lift augmentation wing surface position with the aileron level flight compensation angle; and step 3, if the asymmetric fault signal 1 is generated in the system and the aileron rudder output amount of one side with the small high lift airfoil position is greater than the aileron level flight compensation angle, carrying out system asymmetric fault alarm, otherwise, regarding the asymmetric fault signal 1 as a false alarm and not reporting the false alarm.

Description

Technical Field

[0001] This application belongs to the field of aircraft control technology, and specifically relates to a method and system for fusion detection of asymmetric faults in lift enhancement systems. Background Technology

[0002] Lift-enhancing surfaces are symmetrically arranged on both sides of an aircraft, increasing lift by altering the wing area during takeoff and landing. However, because these surfaces are generally large, asymmetrical malfunctions during their movement can cause significant roll effects, potentially leading to loss of control and damage. Current methods for asymmetrical monitoring of lift-enhancing systems typically involve comparing the positions of the left and right surfaces in real-time. This involves monitoring the position information of the left and right lift-enhancing surfaces and performing differential processing. If the difference exceeds an asymmetry threshold, an alarm is triggered, and the lift-enhancing surfaces are protected to their current fault position to prevent further damage. In this case, the lift-enhancing surfaces become uncontrollable, and the aircraft lands in the current lift configuration. While this design principle generally enables the detection and protection against asymmetric faults, relying solely on lift-enhancing surface position information for asymmetric detection frequently results in false alarms due to lift position sensor malfunctions. This causes the lift-enhancing surfaces to be falsely protected at the false alarm position, preventing normal deployment or retraction, which is detrimental to takeoff and landing and ultimately impacts flight operations. Summary of the Invention

[0003] To address the aforementioned problems, this application provides a method for fusion detection of asymmetric faults in an augmentation system, comprising the following steps:

[0004] Step 1: Monitor the position of the lift-enhancing wing surface online using a lift-enhancing wing surface position sensor. The position includes the lift-enhancing wing surface deflection angle. Calculate the position difference between the left and right lift-enhancing wing surfaces. When the position difference between the left and right lift-enhancing wing surfaces exceeds a threshold value, the system generates an asymmetric fault signal 1.

[0005] Step 2: Obtain the aileron level flight compensation angle and compare the rudder output of the aileron on the side with the smaller lift-enhancing surface with the aileron level flight compensation angle.

[0006] Step 3: If the system generates asymmetric fault signal 1, and the aileron rudder movement on the side with the smaller lift surface is greater than the aileron level flight compensation angle, then the system will issue an asymmetric fault alarm; otherwise, asymmetric fault signal 1 will be considered a false alarm and will not be reported.

[0007] Preferably, the left and right lift-enhancing wing surfaces are positioned... The difference calculation method is as follows:

[0008] ;

[0009] This refers to the position of the left lift-enhancing wing surface. This is the position of the right lift-enhancing wing surface.

[0010] Preferably, the threshold value is an asymmetric monitoring threshold for the position of the left and right lift-enhancing wing surfaces, which is determined by the aircraft itself.

[0011] Preferably, the specific steps for comparing the rudder extension of the aileron on the side with the smaller lift-enhancing surface with the aileron's level flight compensation angle include:

[0012] like < If the left lift-enhancing wing surface is too small, then it is judged that... Does it meet the following requirements:

[0013]

[0014] If in step 1 < If the right lift-enhancing wing surface is too small, then it is judged that... Does it meet the following requirements:

[0015] ;

[0016] To compensate for the angle of aileron during level flight.

[0017] Preferably, the expression for system asymmetric fault alarm is:

[0018] and ;

[0019] or and .

[0020] Preferably, the method is implemented by a flight control computer, which is connected to lift-enhancing wing position sensors and aileron position sensors for data acquisition and logic processing.

[0021] Preferably, the method is applicable to the aircraft takeoff and landing phases, used to detect asymmetric faults in the lift enhancement system and reduce the false alarm rate caused by sensor malfunctions.

[0022] A fusion detection system for asymmetric faults in an augmentation system, used to implement the aforementioned fusion detection method for asymmetric faults in an augmentation system, comprising:

[0023] Lift-enhancing wing surface position sensor, used to monitor the position of the left and right lift-enhancing wing surfaces;

[0024] Aileron position sensor, used to monitor aileron rudder extension;

[0025] The flight control computer is configured to execute the asymmetric fault fusion detection method for the lift enhancement system as described in claims 1-7, generate asymmetric fault signals and perform logical judgments;

[0026] An alarm device is used to issue an alarm when an asymmetric fault is detected.

[0027] A computer-readable storage medium having a computer program stored thereon, which, when executed by a processor, implements the aforementioned method for fusion detection of asymmetric faults in an augmentation system.

[0028] An aircraft flight control system includes a lift enhancement system asymmetric fault fusion detection system, which is integrated into the aircraft avionics system to improve the mission reliability of the lift enhancement system. This invention achieves asymmetric fault fusion detection of the lift enhancement system by simultaneously detecting the position information of the lift enhancement surfaces and the ailerons, reducing the false alarm rate of asymmetric fault detection, improving system mission reliability, and providing strong support for the successful completion of flight missions. Attached Figure Description

[0029] Figure 1 This is a flowchart of a method for enhancing the fusion detection of asymmetric faults in a system. Detailed Implementation

[0030] To make the objectives, technical solutions, and advantages of this application clearer, the technical solutions in the embodiments of this application will be described in more detail below with reference to the accompanying drawings. In the drawings, the same or similar reference numerals denote the same or similar elements or elements having the same or similar functions throughout. The described embodiments are only some, not all, of the embodiments of this application. The embodiments described below with reference to the accompanying drawings are exemplary and intended to explain this application, and should not be construed as limiting this application. All other embodiments obtained by those skilled in the art based on the embodiments of this application without creative effort are within the scope of protection of this application. The embodiments of this application will be described in detail below with reference to the accompanying drawings. Figure 1 As shown, a method for fusion detection of asymmetric faults in a lift enhancement system is characterized by firstly monitoring the position information of the lift enhancement surface online through a lift enhancement surface position sensor. If the position information of the two sides of the lift enhancement surface is out of sync and exceeds a threshold value, the system generates an "asymmetric fault signal 1" and records the position of the left and right sides of the lift enhancement surface at this time.

[0031] Specifically, the lift-enhancing surfaces and ailerons are symmetrically arranged on both sides of the aircraft. The flight control computer can collect real-time position information of the lift-enhancing surfaces and ailerons through wing position sensors. The position of the left lift-enhancing surface is defined as... The position of the right lift-enhancing wing surface is defined as ,definition:

[0032] (1)

[0033] in, This refers to the position difference of the left and right lift-enhancing wing surfaces. If satisfy

[0034] (2)

[0035] in, The asymmetric monitoring threshold for the left and right lift-enhancing wing surface positions is determined by the aircraft itself. The system then generates an "asymmetric fault signal 1" and simultaneously records the position of the left lift-enhancing wing surface at that moment. Right lift surface position .

[0036] Confirm whether the rudder extension of the aileron on the side with the smaller lift-enhancing surface has reached the level flight compensation angle.

[0037] Specifically: If the left and right lift-enhancing surfaces are truly asymmetrical, when the aircraft maintains level flight, the ailerons need to engage rudders to compensate for the roll torque caused by the asymmetry of the lift-enhancing surfaces, and the aileron level flight compensation angle... Determined by the aircraft itself.

[0038] Define the position of the left aileron as The position of the right aileron is .

[0039] If in step 1 < If the left lift-enhancing wing surface is too small, then it is judged that... Does it meet the requirements?

[0040] (3)

[0041] If in step 1 < If the right lift-enhancing wing surface is too small, then it is judged that... Does it meet the requirements?

[0042] (4)

[0043] The lift enhancement system uses an AND logic to process "Asymmetric Fault Signal 1" and aileron rudder extension. If the aileron rudder extension reaches the threshold value synchronously after the system has generated "Asymmetric Fault Signal 1", the system will issue an asymmetric fault alarm. Otherwise, the system will treat "Asymmetric Fault Signal 1" as a false alarm and will not report it.

[0044] Specifically: If either step 1 or step 2 meets one of the following conditions, the system will report an asymmetric fault alarm for the enhancement system; otherwise, no alarm will be reported.

[0045] a) If formula (2) holds and formula (3) holds, that is:

[0046] and (5)

[0047] b) If formula (2) holds and formula (4) holds, that is:

[0048] and (6)

[0049] By following the steps above, asymmetric fault fusion detection that takes into account both lift-enhancing surface position information and aircraft response status can be achieved, reducing the false alarm rate of system detection caused by using only lift-enhancing surface position sensors.

[0050] A fusion detection system for asymmetric faults in an augmentation system, used to implement the aforementioned fusion detection method for asymmetric faults in an augmentation system, comprising:

[0051] Lift-enhancing wing surface position sensor, used to monitor the position of the left and right lift-enhancing wing surfaces;

[0052] Aileron position sensor, used to monitor aileron rudder extension;

[0053] The flight control computer is configured to execute the asymmetric fault fusion detection method for the lift enhancement system as described in claims 1-7, generate asymmetric fault signals and perform logical judgments;

[0054] An alarm device is used to issue an alarm when an asymmetric fault is detected.

[0055] A computer-readable storage medium having a computer program stored thereon, which, when executed by a processor, implements the aforementioned method for fusion detection of asymmetric faults in an augmentation system.

[0056] An aircraft flight control system includes a lift enhancement system asymmetric fault fusion detection system, which is integrated into the aircraft avionics system to improve the mission reliability of the lift enhancement system. This invention achieves asymmetric fault fusion detection of the lift enhancement system by simultaneously detecting the position information of the lift enhancement surfaces and the ailerons, reducing the false alarm rate of asymmetric fault detection, improving system mission reliability, and providing strong support for the successful completion of flight missions.

[0057] The above description is merely a specific embodiment of this application, but the scope of protection of this application is not limited thereto. Any variations or substitutions that can be easily conceived by those skilled in the art within the technical scope disclosed in this application should be included within the scope of protection of this application. Therefore, the scope of protection of this application should be determined by the scope of the claims.

Claims

1. A method for fusion detection of asymmetric faults in an augmentation system, characterized in that, Includes the following steps: Step 1: Monitor the position of the lift-enhancing wing surface online using a lift-enhancing wing surface position sensor. The position includes the lift-enhancing wing surface deflection angle. Calculate the position difference between the left and right lift-enhancing wing surfaces. When the position difference between the left and right lift-enhancing wing surfaces exceeds a threshold value, the system generates an asymmetric fault signal 1. Step 2: Obtain the aileron level flight compensation angle and compare the rudder output of the aileron on the side with the smaller lift-enhancing surface with the aileron level flight compensation angle. Step 3: If the system generates asymmetric fault signal 1, and the aileron rudder movement on the side with the smaller lift surface is greater than the aileron level flight compensation angle, then the system will issue an asymmetric fault alarm; otherwise, asymmetric fault signal 1 will be considered a false alarm and will not be reported.

2. The asymmetric fault fusion detection method for augmentation systems as described in claim 1, characterized in that, Left and right lift-enhancing wing surface positions The difference calculation method is as follows: ； This refers to the position of the left lift-enhancing wing surface. This is the position of the right lift-enhancing wing surface.

3. The asymmetric fault fusion detection method for augmentation systems as described in claim 2, characterized in that, The threshold value is the asymmetric monitoring threshold for the position of the left and right lift-enhancing wing surfaces, which is determined by the aircraft itself.

4. The asymmetric fault fusion detection method for augmentation systems as described in claim 3, characterized in that, The specific steps for comparing the rudder extension of the aileron on the side with the smaller lift-enhancing wing surface with the aileron's level flight compensation angle include: like < If the left lift-enhancing wing surface is too small, then it is judged that... Does it meet the following requirements: If in step 1 < If the right lift-enhancing wing surface is too small, then it is judged that... Does it meet the following requirements: ； To compensate for the aileron's angle during level flight.

5. The asymmetric fault fusion detection method for augmentation systems as described in claim 4, characterized in that, The expression for triggering asymmetric fault alarms in the system is: and ; or and .

6. The asymmetric fault fusion detection method for augmentation systems as described in claim 1, characterized in that, The method is implemented by a flight control computer, which is connected to lift-enhancing wing surface position sensors and aileron position sensors for data acquisition and logic processing.

7. The asymmetric fault fusion detection method for augmentation systems as described in claim 1, characterized in that, The method is applicable to the takeoff and landing phases of aircraft and is used to detect asymmetric faults in lift enhancement systems, thereby reducing the false alarm rate caused by sensor malfunctions.

8. A fusion detection system for asymmetric faults in an augmentation system, used to implement the fusion detection method for asymmetric faults in an augmentation system as described in any one of claims 1-7, characterized in that, include: Lift-enhancing wing surface position sensor, used to monitor the position of the left and right lift-enhancing wing surfaces; Aileron position sensor, used to monitor aileron rudder extension; The flight control computer is configured to execute the asymmetric fault fusion detection method for the lift enhancement system as described in claims 1-7, generate asymmetric fault signals and perform logical judgments; An alarm device is used to issue an alarm when an asymmetric fault is detected.

9. A computer-readable storage medium having a computer program stored thereon, the program being executed by a processor to implement the asymmetric fault fusion detection method for an augmentation system as described in any one of claims 1-7.

10. An aircraft flight control system, comprising the lift enhancement system asymmetric fault fusion detection system as described in claim 8, characterized in that, This system is integrated into the aircraft's avionics system to improve the reliability of lift enhancement system missions.

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