An aircraft flap condition monitoring method, device, equipment and storage medium

Abstract

The application discloses an aircraft flap state monitoring method, device and equipment and a storage medium, and the method comprises the following steps: collecting flap system data and aircraft airspeed in the process of aircraft operation; performing automatic flap retraction function monitoring according to hydraulic system pressure data, aircraft airspeed, a flap angle and a flap handle position; performing take-off flap shape overspeed monitoring according to the flap angle and the aircraft airspeed of the aircraft in the take-off stage; performing flap sensor position out-of-tolerance monitoring according to the parameters of the flap angle, FPPU and IPPU; and performing flap hydraulic valve state monitoring according to the flap system fault state and the hydraulic system pressure data. The application realizes comprehensive flap state monitoring, can improve aircraft fault troubleshooting efficiency and accuracy, and guarantees safety.

Description

Technical Field

[0001] This invention relates to the field of aircraft inspection technology, and in particular to a method, apparatus, equipment and storage medium for monitoring the status of aircraft flaps. Background Technology

[0002] Modern commercial aircraft are equipped with trailing edge flap systems, which extend before takeoff and landing to increase lift for the wings. The flap system consists of a control computer, power control components, drive shafts, left and right flaps, and various sensors. The system monitors its operational status through sensor data and issues warning messages in case of malfunction.

[0003] However, the system sensors have a certain probability of failure. When a sensor malfunctions, it outputs a value deviating from the normal range. Maintenance personnel cannot detect and take repair measures until the sensor output value exceeds the set warning range. The flaps automatically retract at overspeed thresholds but do not generate a report. According to the maintenance manual, a series of checks are required after a flap overspeed event before release. Currently, flap overspeed issues rely mainly on crew reports, and maintenance personnel cannot accurately determine whether an overspeed event occurred on each flight segment, easily leading to non-standard releases. Flap system malfunctions generally occur during flight, but maintenance can only be performed on the ground. Ground-based systems cannot fully simulate in-flight conditions, and maintenance personnel cannot know the flap system's status at the time of the malfunction, resulting in low troubleshooting efficiency. Summary of the Invention

[0004] To address the above technical problems, this invention provides a method, device, equipment, and storage medium for monitoring the status of aircraft flaps. By monitoring the automatic flap retraction function, overspeed monitoring of takeoff flap shape, monitoring of flap sensor position deviation, and monitoring of flap hydraulic valve status, comprehensive monitoring of the aircraft flap status is achieved, improving the efficiency and accuracy of fault diagnosis.

[0005] This invention provides a method for monitoring the status of aircraft flaps, including:

[0006] The system collects flap system data and aircraft airspeed during aircraft operation; the flap system data includes: flap angle, flap handle position, parameters of the flap feedback position sensor FPPU (Feed Back Position Pick-Off Unit), and flap instrument position sensor IPPU (Instrumentation Position Pick-Off Unit). The parameters of the Unit, the fault status of the flap system, and the pressure data of the flap hydraulic system;

[0007] The automatic flap retraction function is monitored based on the pressure data, the aircraft airspeed, the flap angle, and the flap handle position.

[0008] Based on the flap angle and airspeed of the aircraft during the takeoff phase, overspeed monitoring of takeoff flap configuration is performed.

[0009] Based on the flap angle, the parameters of the FPPU, and the parameters of the IPPU, the flap sensor position deviation is monitored.

[0010] Based on the fault status of the flap system and the pressure data, monitor the status of the flap hydraulic valve;

[0011] Based on the monitoring of the automatic flap retraction function, the overspeed monitoring of the takeoff flap shape, the monitoring of the flap sensor position deviation, and the monitoring of the flap hydraulic valve status, the flap status monitoring results are obtained for troubleshooting.

[0012] As an improvement to the above solution, the automatic flap retraction function monitoring includes: automatic flap unloading monitoring and automatic flap operation monitoring;

[0013] The monitoring of the automatic flap retraction function based on the pressure data, the aircraft airspeed, the flap angle, and the flap handle position includes:

[0014] Based on the pressure data, the aircraft airspeed, and the flap angle, the automatic flap unloading monitoring is performed;

[0015] Automatic flap operation monitoring is performed based on the pressure data, the aircraft airspeed, the flap angle, and the flap handle position.

[0016] As an improvement to the above solution, the step of automatically monitoring the flap unloading based on the pressure data, the aircraft airspeed, and the flap angle includes:

[0017] If the pressure data is greater than a preset first pressure value, the aircraft airspeed is within a preset first airspeed range, and the flap angle is at a preset first angle, then a 2-bit flap automatic unloading event is generated.

[0018] If the pressure data is greater than the first pressure value, the aircraft airspeed is within the preset second airspeed range, and the flap angle is at the preset second angle, then a 3-bit flap automatic unloading event is generated.

[0019] If the pressure data is greater than a preset first pressure value, the aircraft airspeed is within a preset third airspeed range, and the flap angle is at a preset third angle, then a FULL position flap automatic unloading event is generated.

[0020] As an improvement to the above solution, the automatic flap monitoring based on the pressure data, the aircraft airspeed, the flap angle, and the flap handle position includes:

[0021] If the pressure data is greater than a preset second pressure value, the flap handle position is in a preset position, the aircraft airspeed is not less than a preset first airspeed, and the flap angle is in a preset fourth angle, then an automatic flap operation event is generated.

[0022] As an improvement to the above solution, the step of monitoring takeoff flap configuration overspeed based on the flap angle and airspeed of the aircraft during takeoff includes:

[0023] If the flap angle is greater than zero, the aircraft airspeed is greater than a preset second airspeed, and the aircraft is in the takeoff phase, then a takeoff flap overspeed event is generated.

[0024] As an improvement to the above solution, the step of monitoring the flap sensor position deviation based on the flap angle, the parameters of the FPPU, and the parameters of the IPPU includes:

[0025] If the flap angle is within a preset angle range, then based on the parameters of the FPPU and the IPPU, it is determined whether the position difference of each sensor group is greater than a preset threshold and the duration is greater than a preset duration.

[0026] If the position difference of a sensor group is greater than a preset threshold and the duration is greater than a preset duration, a flap sensor position error event is generated.

[0027] As an improvement to the above solution, the step of monitoring the status of the flap hydraulic valve based on the fault status of the flap system and the pressure data includes:

[0028] When the flap system is in a fault state, according to the pressure data, if the first pressure of the flap hydraulic system at a preset time after the fault is greater than the second pressure of the same flap hydraulic system at the time of the fault, and the first pressure is greater than the third pressure of another flap hydraulic system at the same moment, then a flap hydraulic valve closing event is generated.

[0029] This invention also provides an aircraft flap status monitoring device, comprising:

[0030] The data acquisition module is used to collect flap system data and aircraft airspeed during aircraft operation; the flap system data includes: flap angle, flap handle position, parameters of flap feedback position sensor FPPU, parameters of flap instrument position sensor IPPU, flap system fault status, and pressure data of flap hydraulic system.

[0031] The retraction function monitoring module is used to monitor the automatic flap retraction function based on the pressure data, the aircraft airspeed, the flap angle, and the flap handle position.

[0032] The takeoff overspeed monitoring module is used to monitor takeoff flap configuration overspeed based on the flap angle and airspeed of the aircraft during the takeoff phase.

[0033] The position deviation monitoring module is used to monitor the position deviation of the flap sensor based on the flap angle, the parameters of the FPPU, and the parameters of the IPPU.

[0034] The hydraulic valve monitoring module is used to monitor the status of the flap hydraulic valve based on the fault status of the flap system and the pressure data.

[0035] The flap status monitoring module is used to obtain flap status monitoring results based on the monitoring of the automatic flap retraction function, the overspeed monitoring of the takeoff flap shape, the over-tolerance monitoring of the flap sensor position, and the status monitoring of the flap hydraulic valve, so as to be used for fault diagnosis.

[0036] This invention also provides a computer device, including a processor and a memory, wherein the memory stores a computer program and the computer program is configured to be executed by the processor, and the processor executes the computer program to implement the aircraft flap status monitoring method described in any of the preceding claims.

[0037] This invention also provides a computer-readable storage medium storing a computer program, wherein the computer program, when running, controls the device where the computer-readable storage medium is located to execute the aircraft flap status monitoring method described above.

[0038] Compared to existing technologies, the beneficial effects of the aircraft flap status monitoring method, apparatus, equipment, and storage medium provided by this invention are as follows: By collecting flap system data and aircraft airspeed for each flight segment, it performs monitoring of automatic flap retraction function, takeoff flap overspeed, flap sensor position deviation, and flap hydraulic valve status, thereby achieving comprehensive aircraft flap status monitoring. When a fault occurs in the automatic flap retraction function, it prompts maintenance personnel to troubleshoot; when a flap overspeed event occurs, it prompts maintenance personnel to perform relevant checks to avoid exceeding standards for release; when the performance of the flap sensor deteriorates, it prompts maintenance personnel to replace the sensor in a timely manner to avoid malfunctions; when a flap system fault occurs, it uses pressure fluctuation analysis of the corresponding hydraulic system to determine whether the corresponding hydraulic valve is in the closed state, assisting maintenance personnel in troubleshooting. This invention improves the efficiency and accuracy of fault diagnosis, ensuring aircraft operational safety. Attached Figure Description

[0039] Figure 1 This is a flowchart illustrating an aircraft flap status monitoring method provided in an embodiment of the present invention;

[0040] Figure 2 This is a schematic diagram of a flap system provided in an embodiment of the present invention;

[0041] Figure 3 This is a schematic diagram of an automatic flap unloading monitoring process provided by an embodiment of the present invention;

[0042] Figure 4 This is a schematic diagram of an automatic flap monitoring process provided by an embodiment of the present invention;

[0043] Figure 5 This is a schematic diagram of a takeoff flap configuration overspeed monitoring process provided in an embodiment of the present invention;

[0044] Figure 6 This is a schematic diagram of a process for monitoring the position deviation of a flap sensor according to an embodiment of the present invention;

[0045] Figure 7 This is a schematic diagram of a flap hydraulic system provided in an embodiment of the present invention;

[0046] Figure 8 This is a schematic diagram of a process for monitoring the status of a flap hydraulic valve according to an embodiment of the present invention;

[0047] Figure 9 This is a schematic diagram of the structure of an aircraft flap status monitoring device provided in an embodiment of the present invention;

[0048] Figure 10 This is a schematic diagram of the structure of a computer device provided in an embodiment of the present invention. Detailed Implementation

[0049] The technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of the present invention, and not all embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of the present invention.

[0050] Please see Figure 1 , Figure 1 This is a flowchart illustrating an aircraft flap status monitoring method provided in an embodiment of the present invention. The aircraft flap status monitoring method includes:

[0051] S1: Collect flap system data and aircraft airspeed during aircraft operation; the flap system data includes: flap angle, flap handle position, parameters of flap feedback position sensor FPPU, parameters of flap instrument position sensor IPPU, flap system fault status, and pressure data of flap hydraulic system.

[0052] Specifically, embodiments of the present invention collect and analyze data from aircraft system sensors, and then determine the status of the flap system based on the analysis results. The system sensors include: a flap interconnect strut sensor, a hydraulic system pressure sensor, an airspeed sensor, a flap feedback position sensor assembly (FPPU), an acquisition position sensor assembly (APPU), and a flap instrument position sensor assembly (IPPU).

[0053] Please see Figure 2 , Figure 2 This is a schematic diagram of the flap system. The components include: CONTROL LEVER (control lever); COMMANDSENSOR UNIT (command sensor unit); SFCC1 / SFCC2 (slat / flap control computer 1 / 2); WTB (wingtip brake); APPU (asymmetric position acquisition unit); FLAP TRACK 4SENSOR (flap track 4 sensors); FLAP DISCONNECTSENSORS (flap disconnect sensors); FPPU (flap power unit); IPPU (integrated position acquisition unit); ECAM (electronic centralized aircraft monitoring system); DIF GEAR BOX (differential gearbox); M (Motor); POB (pressure-controlled brake); VALVEBLOCK (valve block); and YELLOW / GREEN (yellow / green channels for the hydraulic system).

[0054] In the flap system, the pilot inputs flap commands via a control stick, instructing the sensor unit to transmit control commands to SFCC1 and SFCC2. The FPPU and IPPU work together to transmit flap power to the differential gearbox and monitor flap position through a series of sensors. The differential gearbox drives the flap deployment and retraction via an electric motor (M). The flap movement is controlled by valve blocks in the yellow and green hydraulic systems to ensure smooth flap movement. During flap deployment or retraction, the POB brakes when a set hydraulic pressure is reached, enabling rapid cessation of flap movement in emergencies. The flap system, based on hydraulic pressure and electric motor drive, is precisely controlled by multiple sensors and a control computer to ensure flap safety during flight.

[0055] In this embodiment of the invention, during aircraft operation, data from the flap system sensors and flap computer signals are collected at regular intervals (typically 1 second) starting from engine startup. The collected data for each flight segment is stored in file format. By analyzing the collected data, it is possible to determine whether any abnormalities have occurred during flight. Furthermore, by setting different judgment logics, different events are generated for different abnormalities to prompt maintenance personnel to take measures for maintenance, thereby ensuring the safe operation of the aircraft.

[0056] The acquired sensor data includes: flap position parameters (i.e., flap angle), flap handle position, parameters of the flap feedback position sensor FPPU, parameters of the flap instrument position sensor IPPU, flap system fault status, and pressure data of the flap hydraulic system.

[0057] The flap position parameter refers to the numerical angle at which the flaps extend. When the flap handle is in position 0, the flap angle is 0 degrees. When the flap handle is in position 1, the flap may have two angles: if the handle moves from 0 to 1, the flap angle may be 8.5 degrees (airspeed less than or equal to 100 knots) or 0 degrees (airspeed greater than 100 knots); if the flap handle moves from FULL, 3, 2 to 1, the flap angle may be 8.5 degrees (airspeed less than 200 knots) or 0 degrees (airspeed greater than or equal to 200 knots); when the flap handle is in position 2, the flap angle is 14.5 degrees; when the flap handle is in position 3, the flap angle is 22.5 degrees; and when the flap handle is in the FULL position, the flap angle is 32 degrees. Airspeed refers to the airspeed value detected by the aircraft's sensors.

[0058] Furthermore, the aircraft flap status monitoring includes four parts: automatic flap retraction function monitoring, takeoff flap shape overspeed monitoring, flap sensor position deviation monitoring, and flap hydraulic valve status monitoring; among them, automatic flap retraction function monitoring includes: automatic flap unloading monitoring and automatic flap operation monitoring.

[0059] S2: Monitor the automatic flap retraction function based on the pressure data, the aircraft airspeed, the flap angle, and the flap handle position.

[0060] As one optional embodiment, the automatic flap retraction function monitoring includes: automatic flap unloading monitoring and automatic flap operation monitoring;

[0061] The monitoring of the automatic flap retraction function based on the pressure data, the aircraft airspeed, the flap angle, and the flap handle position includes:

[0062] Based on the pressure data, the aircraft airspeed, and the flap angle, the automatic flap unloading monitoring is performed;

[0063] Automatic flap operation monitoring is performed based on the pressure data, the aircraft airspeed, the flap angle, and the flap handle position.

[0064] As one optional embodiment, the automatic flap unloading monitoring based on the pressure data, the aircraft airspeed, and the flap angle includes:

[0065] If the pressure data is greater than a preset first pressure value, the aircraft airspeed is within a preset first airspeed range, and the flap angle is at a preset first angle, then a 2-bit flap automatic unloading event is generated.

[0066] If the pressure data is greater than the first pressure value, the aircraft airspeed is within the preset second airspeed range, and the flap angle is at the preset second angle, then a 3-bit flap automatic unloading event is generated.

[0067] If the pressure data is greater than a preset first pressure value, the aircraft airspeed is within a preset third airspeed range, and the flap angle is at a preset third angle, then a FULL position flap automatic unloading event is generated.

[0068] Preferably, the first airspeed range is not less than 198.5 kts, the second airspeed range is less than 198.5 kts and greater than or equal to 188.5 kts, the third airspeed range is less than 188.5 kts and greater than or equal to 182.5 kts, the first angle is 14.5, the second angle is 22.5, and the third angle is 32.5.

[0069] Specifically, the flaps require power from a hydraulic system during extension and retraction. When the flaps extend to a certain angle and reach a preset pressure, the system monitors the pressure level of the hydraulic system through a pressure sensor. If the pressure exceeds or is insufficient to maintain safe operation, the system will trigger an unloading procedure to automatically retract or adjust the flaps to avoid overload or failure of the hydraulic system.

[0070] Please see Figure 3 , Figure 3 This is a flowchart illustrating the automatic flap unloading monitoring process. During flap system operation, SFCC1 controls the yellow hydraulic system, and SFCC2 controls the green hydraulic system. A prerequisite for automatic flap unloading is that at least one of the yellow or green hydraulic systems must be within the normal pressure range. Secondly, it is also related to the current flap position and real-time airspeed: when the airspeed is greater than or equal to 198.5 knots, if the flap position is at 14.5 degrees, a 2-position automatic flap unloading event is triggered; when the airspeed is greater than or equal to 188.5 knots, if the flap position is at 22.5 degrees, a 3-position automatic flap unloading event is triggered; when the airspeed is greater than or equal to 182.5 knots, if the flap position is at 32.5 degrees, a FULL-position automatic flap unloading event is triggered.

[0071] As one optional embodiment, the automatic flap monitoring based on the pressure data, the aircraft airspeed, the flap angle, and the flap handle position includes:

[0072] If the pressure data is greater than a preset second pressure value, the flap handle position is in a preset position, the aircraft airspeed is not less than a preset first airspeed, and the flap angle is in a preset fourth angle, then an automatic flap operation event is generated.

[0073] Preferably, the preset position is 1, the first airspeed is 200 knots, and the fourth angle is 8.5 degrees.

[0074] For details, please refer to Figure 4 , Figure 4 This is a flowchart illustrating the automatic flap monitoring process. The main parameters used in this monitoring include: the pressure of the yellow and green hydraulic systems, the flap handle position, the flap angle, and the aircraft airspeed. Automatic flap actuation is a protective function for the flaps. When the flap handle is in position 1 and the flaps are extended, if the aircraft airspeed is greater than or equal to 200 knots, the flaps will automatically retract to 0 degrees. The prerequisites for automatic flap actuation are that at least one of the yellow and green hydraulic systems has sufficient pressure, the flap handle is in position 1, the flap angle is 8.5 degrees, and the aircraft airspeed is greater than or equal to 200 knots; only then will an automatic flap actuation event be generated.

[0075] S3: Based on the flap angle and airspeed of the aircraft during the takeoff phase, perform overspeed monitoring of the takeoff flap configuration.

[0076] As one optional embodiment, the step of monitoring takeoff flap configuration overspeed based on the flap angle and the aircraft airspeed during the takeoff phase includes:

[0077] If the flap angle is greater than zero, the aircraft airspeed is greater than a preset second airspeed, and the aircraft is in the takeoff phase, then a takeoff flap overspeed event is generated.

[0078] Preferably, the second airspeed is 215 knots.

[0079] Please see Figure 5 , Figure 5 This is a flowchart illustrating the process of overspeed monitoring of takeoff flap configuration.

[0080] Specifically, during takeoff, the aircraft flaps are in the 1+F configuration, at which point the maximum speed is 215 knots. If the flaps fail to retract to the 0-degree position when the aircraft's airspeed exceeds 215 knots, a flap overspeed event is considered to have occurred. According to the AMM manual, if a flap overspeed event occurs, it is necessary to refer to the maintenance manual for inspection before resuming operation.

[0081] S4: Monitor the flap sensor position deviation based on the flap angle, the parameters of the FPPU, and the parameters of the IPPU.

[0082] As one optional embodiment, the step of monitoring the flap sensor position deviation based on the flap angle, the parameters of the FPPU, and the parameters of the IPPU includes:

[0083] If the flap angle is within a preset angle range, then based on the parameters of the FPPU and the IPPU, it is determined whether the position difference of each sensor group is greater than a preset threshold and the duration is greater than a preset duration.

[0084] If the position difference of a sensor group is greater than a preset threshold and the duration is greater than a preset duration, a flap sensor position error event is generated.

[0085] Specifically, the flap shaft sensor mainly includes the FPPU and IPPU. Each FPPU and IPPU has the same part number and operating principle, and both include: a splined input shaft, a spring-loaded locking plate, a reduction gear, a reduction gear housing, two independently operating synchronous transmitters, a synchronizer cover, an electrical connector block, and a cover plate. The flap drive shaft is connected to the splined input shaft of the PPU; when the flap is in the 0 position, the PPU is also set to 0 degrees. When the flap drive shaft rotates, it drives the splined shaft of the PPU to rotate, and the PPU transmitter sends an angle signal. Both the FPPU and IPPU are mounted on the flap drive shaft, so under normal conditions, all PPUs indicate the same angle.

[0086] The parameters of the FPPU include: FPPU1 and FPPU2; FPPU1 is the FPPU feedback position signal (system 1), and its parameters are sourced from SFCC1; FPPU2 is the FPPU feedback position signal (system 2), and its parameters are sourced from SFCC2.

[0087] The parameters of IPPU include: IPPU1L1, IPPU2L1, IPPU1L2, and IPPU2L2; IPPU1L1 is the signal from IPPU module 1 to the FWC1 system, and its parameters are sourced from FWC L1; IPPU2L1 is the signal from IPPU module 2 to the FWC1 system, and its parameters are sourced from FWC L1; IPPU1L2 is the signal from IPPU module 1 to the FWC2 system, and its parameters are sourced from FWC L2; IPPU2L2 is the signal from IPPU module 2 to the FWC2 system, and its parameters are sourced from FWC L2.

[0088] Since the PPU sensor is a device that converts mechanical signals into electrical signals, its failure may gradually develop as the internal components operate. By monitoring whether the sensor's output signal deviates, it is possible to determine whether there is a trend of failure inside the PPU.

[0089] Furthermore, due to different sampling intervals, the values ​​of each PPU may differ during flap movement. To eliminate false inconsistencies caused by flap movement, an inconsistency event is triggered after a PPU exceeds the tolerance by more than 3 degrees for 8 consecutive seconds.

[0090] Please see Figure 6 , Figure 6 This is a flowchart illustrating the flap sensor position tolerance monitoring process. The flap sensor position tolerance monitoring first determines if the flap angle is within the threshold ranges of 0-2, 7-9, 12-16, 20-24, and 30-34. If so, it continues to detect PPU signal tolerance. When the difference between FPPU1 and FPPU2 is greater than 3 degrees for 8 consecutive seconds, an FPPU channel signal tolerance event is generated. When the difference between IPPU1L1 and IPPU2L1 is greater than 3 degrees for 8 consecutive seconds, an IPPU FWC1 signal tolerance event is generated. When the difference between IPPU1L2 and IPPU2L2 is greater than 3 degrees for 8 consecutive seconds, an IPPU... FWC2 signal out-of-tolerance event; when the difference between IPPU1L1 and IPPU1L2 is greater than 3 degrees for 8 consecutive seconds, or the difference between IPPU2L1 and IPPU2L2 is greater than 3 degrees for 8 consecutive seconds, an IPPU signal out-of-tolerance event between FWC1 and FPPU is generated; when the difference between FPPU1 and IPPU1L1 is greater than 3 degrees for 8 consecutive seconds, or the difference between FPPU2 and IPPU2L1 is greater than 3 degrees for 8 consecutive seconds, an IPPU and FPPU signal out-of-tolerance event for FWC1 is generated; when the difference between FPPU1 and IPPU1L2 is greater than 3 degrees for 8 consecutive seconds, or the difference between FPPU2 and IPPU2L2 is greater than 3 degrees for 8 consecutive seconds, an IPPU and FPPU signal out-of-tolerance event for FWC2 is generated.

[0091] S5: Monitor the status of the flap hydraulic valve based on the fault status of the flap system and the pressure data.

[0092] As one optional embodiment, the step of monitoring the status of the flap hydraulic valve based on the flap system fault status and the pressure data includes:

[0093] When the flap system is in a fault state, according to the pressure data, if the first pressure of the flap hydraulic system at a preset time after the fault is greater than the second pressure of the same flap hydraulic system at the time of the fault, and the first pressure is greater than the third pressure of another flap hydraulic system at the same moment, then a flap hydraulic valve closing event is generated.

[0094] For details, please refer to Figure 7 , Figure 7 This is a schematic diagram of the flap hydraulic system. The components are: YELLOW SYSTEM, GREEN SYSTEM, PRESSURE, RETURN, SLATS SYSTEM, VALVE BLOCK, DIFF G / B, and POWER CONTROL UNIT.

[0095] The flap system's power control assembly is driven by two hydraulic systems: the yellow hydraulic system and the green hydraulic system. Each hydraulic system is connected to the hydraulic motor (M) and brake (POB) via a valve block. The valve block controls the opening and closing of the valves via solenoid valves, controlling the flow and direction of the hydraulic oil. This, in turn, controls the rotation direction of the hydraulic motor, driving the transmission shaft to rotate in different directions, thereby realizing the flap system's retraction and extension actions.

[0096] Under normal circumstances, the two hydraulic modules of the power control unit operate simultaneously. Upon receiving a signal to extend or retract the flaps, each hydraulic system controls its respective motor to drive the drive shaft. If one hydraulic system or control module fails, the power control unit can still drive the flap shaft to rotate using only one computer and hydraulic system, although the rotational speed will be reduced.

[0097] Both the yellow and green hydraulic systems operate at around 3000 psi under normal conditions. When the flaps are activated, the hydraulic system pressure drops significantly (around 200 psi) because the hydraulic motor needs to perform work. However, if the valve fails to open due to a computer malfunction or a valve body failure, the hydraulic system pressure will not drop. Therefore, by monitoring the pressure drop of the hydraulic system, the status of the flap hydraulic valve module can be determined.

[0098] For details, please refer to Figure 8 , Figure 8 This is a flowchart illustrating the status monitoring of the flap hydraulic valve.

[0099] When a flap system 1 malfunction occurs, compare the pressure of the yellow hydraulic system 10 seconds after the malfunction with the pressure of the yellow hydraulic system at the time of the malfunction. If the pressure rises, then compare the pressure of the green hydraulic system and the yellow hydraulic system 10 seconds after the malfunction. If the pressure of the yellow hydraulic system is greater than the pressure of the green hydraulic system, then trigger the yellow hydraulic valve closing event.

[0100] When a flap system 2 malfunction occurs, compare the green hydraulic system pressure 10 seconds after the malfunction with the green hydraulic system pressure at the time of the malfunction. If the pressure recovers, compare the pressure of the green hydraulic system and the yellow hydraulic system 10 seconds after the malfunction. If the green hydraulic system pressure is greater than the yellow hydraulic system pressure, then trigger the green hydraulic valve closing event.

[0101] S6: Based on the monitoring of the automatic flap retraction function, the overspeed monitoring of the takeoff flap shape, the monitoring of the flap sensor position deviation, and the monitoring of the flap hydraulic valve status, the flap status monitoring results are obtained for troubleshooting.

[0102] Specifically, since flap overspeed events cannot be monitored through aircraft reports, the relationship between aircraft airspeed and flap angle is monitored. If flap overspeed occurs during takeoff after a flight, a corresponding event is triggered, alerting maintenance personnel to perform appropriate checks. The opening and closing status of hydraulic valves is determined by monitoring the pressure drop in the hydraulic system; this allows for the identification of valve status in the event of a flap system malfunction. This embodiment of the invention collects various parameters of the aircraft flap system and generates a queryable and analyzable file after each flight, providing data support for subsequent troubleshooting.

[0103] This invention allows for flexible setting of sensor performance monitoring thresholds, enabling the screening of sensors with degraded performance without system warnings, thus preventing potential problems. In the event of an anomaly, subscribers can be notified via email or platform notifications, prompting maintenance personnel to take appropriate action. Parameters collected by the flap sensors are recorded in real time and can be used as a basis for flap status assessment during ground troubleshooting. Maintenance personnel can accurately understand the system status at the time of the fault and troubleshoot accordingly. It avoids relying on manual judgment to determine whether a flap overspeed event has occurred, thus preventing out-of-standard releases.

[0104] This invention, through the collection of flap system data and aircraft airspeed for each flight segment, monitors the automatic flap retraction function, takeoff flap overspeed, flap sensor position deviation, and flap hydraulic valve status, thereby achieving comprehensive aircraft flap status monitoring. When an automatic flap retraction function malfunction occurs, maintenance personnel are prompted to troubleshoot; when a flap overspeed event occurs, maintenance personnel are prompted to perform relevant checks to avoid exceeding standard release criteria; when flap sensor performance deteriorates, maintenance personnel are prompted to replace the sensors promptly to prevent further malfunctions; when a flap system malfunction occurs, pressure fluctuation analysis of the corresponding hydraulic system is used to determine whether the corresponding hydraulic valve is in the closed state, assisting maintenance personnel in troubleshooting. This invention improves the efficiency and accuracy of fault diagnosis, ensuring aircraft operational safety. Accordingly, this invention also provides an aircraft flap status monitoring device capable of implementing all the processes of the aircraft flap status monitoring method described in the above embodiments.

[0105] Please see Figure 9 , Figure 9 This is a schematic diagram of the structure of an aircraft flap status monitoring device provided in an embodiment of the present invention. The aircraft flap status monitoring device includes:

[0106] The data acquisition module 901 is used to acquire flap system data and aircraft airspeed during aircraft operation; the flap system data includes: flap angle, flap handle position, parameters of flap feedback position sensor FPPU, parameters of flap instrument position sensor IPPU, flap system fault status, and pressure data of flap hydraulic system.

[0107] The retraction function monitoring module 902 is used to monitor the automatic flap retraction function based on the pressure data, the aircraft airspeed, the flap angle, and the flap handle position.

[0108] The takeoff overspeed monitoring module 903 is used to monitor takeoff flap configuration overspeed based on the flap angle and airspeed of the aircraft during the takeoff phase.

[0109] The position deviation monitoring module 904 is used to monitor the position deviation of the flap sensor based on the flap angle, the parameters of the FPPU, and the parameters of the IPPU.

[0110] The hydraulic valve monitoring module 905 is used to monitor the status of the flap hydraulic valve based on the fault status of the flap system and the pressure data.

[0111] The flap status monitoring module 906 is used to obtain flap status monitoring results based on the monitoring of the automatic flap retraction function, the overspeed monitoring of the takeoff flap shape, the over-tolerance monitoring of the flap sensor position, and the status monitoring of the flap hydraulic valve, so as to be used for fault diagnosis.

[0112] Preferably, the automatic flap retraction function monitoring includes: automatic flap unloading monitoring and automatic flap operation monitoring;

[0113] The recovery function monitoring module 902 is specifically used for:

[0114] Based on the pressure data, the aircraft airspeed, and the flap angle, the automatic flap unloading monitoring is performed;

[0115] Automatic flap operation monitoring is performed based on the pressure data, the aircraft airspeed, the flap angle, and the flap handle position.

[0116] Preferably, the step of monitoring the automatic flap unloading based on the pressure data, the aircraft airspeed, and the flap angle includes:

[0117] If the pressure data is greater than a preset first pressure value, the aircraft airspeed is within a preset first airspeed range, and the flap angle is at a preset first angle, then a 2-bit flap automatic unloading event is generated.

[0118] If the pressure data is greater than the first pressure value, the aircraft airspeed is within the preset second airspeed range, and the flap angle is at the preset second angle, then a 3-bit flap automatic unloading event is generated.

[0119] If the pressure data is greater than a preset first pressure value, the aircraft airspeed is within a preset third airspeed range, and the flap angle is at a preset third angle, then a FULL position flap automatic unloading event is generated.

[0120] Preferably, the step of automatically monitoring the flaps based on the pressure data, the aircraft airspeed, the flap angle, and the flap handle position includes:

[0121] If the pressure data is greater than a preset second pressure value, the flap handle position is in a preset position, the aircraft airspeed is not less than a preset first airspeed, and the flap angle is in a preset fourth angle, then an automatic flap operation event is generated.

[0122] Preferably, the takeoff overspeed monitoring module 903 is specifically used for:

[0123] If the flap angle is greater than zero, the aircraft airspeed is greater than a preset second airspeed, and the aircraft is in the takeoff phase, then a takeoff flap overspeed event is generated.

[0124] Preferably, the position deviation monitoring module 904 is specifically used for:

[0125] If the flap angle is within a preset angle range, then based on the parameters of the FPPU and the IPPU, it is determined whether the position difference of each sensor group is greater than a preset threshold and the duration is greater than a preset duration.

[0126] If the position difference of a sensor group is greater than a preset threshold and the duration is greater than a preset duration, a flap sensor position error event is generated.

[0127] Preferably, the hydraulic valve monitoring module 905 is specifically used for:

[0128] When the flap system is in a fault state, according to the pressure data, if the first pressure of the flap hydraulic system at a preset time after the fault is greater than the second pressure of the same flap hydraulic system at the time of the fault, and the first pressure is greater than the third pressure of another flap hydraulic system at the same moment, then a flap hydraulic valve closing event is generated.

[0129] In specific implementation, the working principle, control process and technical effects of the aircraft flap status monitoring device provided in this embodiment of the invention are the same as those of the aircraft flap status monitoring method in the above embodiments, and will not be repeated here.

[0130] See Figure 10 , Figure 10 This is a structural block diagram of a computer device provided in an embodiment of the present invention. The computer device includes: a processor 101, a memory 102, and a computer program stored in the memory 102 and executable on the processor 101. When the processor 101 executes the computer program, it implements the steps in the above-described aircraft flap status monitoring method embodiment. Alternatively, when the processor 101 executes the computer program, it implements the functions of each module / unit in the above-described device embodiments.

[0131] For example, the computer program may be divided into one or more modules / units, which are stored in the memory 102 and executed by the processor 101 to complete the present invention. The one or more modules / units may be a series of computer program instruction segments capable of performing a specific function, which describe the execution process of the computer program in the computer device.

[0132] The computer device may include, but is not limited to, a processor 101 and a memory 102. Those skilled in the art will understand that the schematic diagram is merely an example of a computer device and does not constitute a limitation on the computer device. It may include more or fewer components than illustrated, or combine certain components, or different components. For example, the computer device may also include input / output devices, network access devices, buses, etc.

[0133] The processor 101 can be a Central Processing Unit (CPU), or other general-purpose processors, digital signal processors (DSPs), application-specific integrated circuits (ASICs), field-programmable gate arrays (FPGAs), or other programmable logic devices, discrete gate or transistor logic devices, discrete hardware components, etc. The general-purpose processor can be a microprocessor or any conventional processor. The processor 101 is the control center of the computer device, connecting various parts of the entire computer device through various interfaces and lines.

[0134] The memory 102 can be used to store the computer programs and / or modules. The processor 101 implements various functions of the computer device by running or executing the computer programs and / or modules stored in the memory 102 and calling the data stored in the memory 102. The memory 102 may mainly include a program storage area and a data storage area. The program storage area may store the operating system, at least one application program required for a function (such as sound playback function, image playback function, etc.), etc.; the data storage area may store data created according to the use of the mobile phone (such as audio data, phonebook, etc.). In addition, the memory 102 may include high-speed random access memory, and may also include non-volatile memory, such as hard disk, memory, plug-in hard disk, smart media card (SMC), secure digital card (SD) card, flash card, at least one disk storage device, flash memory device, or other volatile solid-state storage device.

[0135] Wherein, if the modules / units integrated into the computer device are implemented as software functional units and sold or used as independent products, they can be stored in a computer-readable storage medium. Based on this understanding, all or part of the processes in the methods of the above embodiments of the present invention can also be implemented by a computer program instructing related hardware. The computer program can be stored in a computer-readable storage medium, and when the computer program is executed by the processor 101, it can implement the steps of the various method embodiments described above. Wherein, the computer program includes computer program code, which can be in the form of source code, object code, executable file, or some intermediate form, etc. The computer-readable medium can include: any entity or device capable of carrying the computer program code, recording medium, USB flash drive, portable hard drive, magnetic disk, optical disk, computer memory, read-only memory (ROM), random access memory (RAM), electrical carrier signal, telecommunication signal, and software distribution medium, etc.

[0136] This invention also provides a computer-readable storage medium, which includes a stored computer program, wherein the computer program, when running, controls the device where the computer-readable storage medium is located to execute the aircraft flap status monitoring method described in any of the above embodiments.

[0137] This invention provides a method, apparatus, device, and storage medium for monitoring aircraft flap status. Its advantages include: by collecting flap system data and aircraft airspeed for each flight segment, it monitors the automatic flap retraction function, takeoff flap overspeed, flap sensor position deviation, and flap hydraulic valve status, thereby achieving comprehensive aircraft flap status monitoring. When an automatic flap retraction function malfunction occurs, maintenance personnel are prompted to troubleshoot; when a flap overspeed event occurs, maintenance personnel are prompted to perform relevant checks to avoid exceeding standard release criteria; when flap sensor performance deteriorates, maintenance personnel are prompted to replace the sensors promptly to prevent further malfunctions; when a flap system malfunction occurs, pressure fluctuation analysis of the corresponding hydraulic system is used to determine whether the corresponding hydraulic valve is in the closed state, assisting maintenance personnel in troubleshooting. This invention improves the efficiency and accuracy of fault diagnosis, ensuring aircraft operational safety.

[0138] The above description represents the preferred embodiments of the present invention. It should be noted that those skilled in the art can make various improvements and modifications without departing from the principles of the present invention, and these improvements and modifications are also considered to be within the scope of protection of the present invention.

Claims

1. A method for monitoring the status of aircraft flaps, characterized in that, include: Collect data on the flap system and airspeed of the aircraft during operation; The flap system data includes: flap angle, flap handle position, parameters of flap feedback position sensor FPPU, parameters of flap instrument position sensor IPPU, flap system fault status, and pressure data of flap hydraulic system. The automatic flap retraction function is monitored based on the pressure data, the aircraft airspeed, the flap angle, and the flap handle position. Based on the flap angle and airspeed of the aircraft during the takeoff phase, overspeed monitoring of the takeoff flap configuration is performed. Based on the flap angle, the parameters of the FPPU, and the parameters of the IPPU, the flap sensor position deviation is monitored. Based on the fault status of the flap system and the pressure data, monitor the status of the flap hydraulic valve; Based on the monitoring of the automatic flap retraction function, the overspeed monitoring of the takeoff flap shape, the monitoring of the flap sensor position deviation, and the monitoring of the flap hydraulic valve status, the flap status monitoring results are obtained for troubleshooting. The monitoring of the automatic flap retraction function includes: automatic flap unloading monitoring and automatic flap operation monitoring; The monitoring of the automatic flap retraction function based on the pressure data, the aircraft airspeed, the flap angle, and the flap handle position includes: Based on the pressure data, the aircraft airspeed, and the flap angle, the automatic flap unloading monitoring is performed; Automatic flap monitoring is performed based on the pressure data, the aircraft airspeed, the flap angle, and the flap handle position. The step of monitoring takeoff flap overspeed based on the flap angle and airspeed of the aircraft during takeoff includes: generating a takeoff flap overspeed event if the flap angle is greater than zero, the airspeed of the aircraft is greater than a preset second airspeed, and the aircraft is in the takeoff phase. The step of monitoring the flap sensor position deviation based on the flap angle, the parameters of the FPPU, and the parameters of the IPPU includes: If the flap angle is within a preset angle range, then based on the parameters of the FPPU and the IPPU, it is determined whether the position difference of each sensor group is greater than a preset threshold and the duration is greater than a preset duration. If the position difference of a sensor group is greater than a preset threshold and the duration is greater than a preset duration, a flap sensor position error event is generated. The step of monitoring the status of the flap hydraulic valve based on the flap system fault status and the pressure data includes: when the flap system is in a fault state, if the first pressure of the flap hydraulic system at a preset time after the fault is greater than the second pressure of the same flap hydraulic system at the fault, and the first pressure is greater than the third pressure of another flap hydraulic system at the same moment, then a flap hydraulic valve closing event is generated.

2. The aircraft flap status monitoring method as described in claim 1, characterized in that, The automatic flap unloading monitoring based on the pressure data, the aircraft airspeed, and the flap angle includes: If the pressure data is greater than a preset first pressure value, the aircraft airspeed is within a preset first airspeed range, and the flap angle is at a preset first angle, then a 2-bit flap automatic unloading event is generated. If the pressure data is greater than the first pressure value, the aircraft airspeed is within the preset second airspeed range, and the flap angle is at the preset second angle, then a 3-bit flap automatic unloading event is generated. If the pressure data is greater than a preset first pressure value, the aircraft airspeed is within a preset third airspeed range, and the flap angle is at a preset third angle, then a FULL position flap automatic unloading event is generated.

3. The aircraft flap status monitoring method as described in claim 1, characterized in that, The automatic flap monitoring based on the pressure data, the aircraft airspeed, the flap angle, and the flap handle position includes: If the pressure data is greater than a preset second pressure value, the flap handle position is in a preset position, the aircraft airspeed is not less than a preset first airspeed, and the flap angle is in a preset fourth angle, then an automatic flap operation event is generated.

4. An aircraft flap status monitoring device, characterized in that, The apparatus for implementing the aircraft flap status monitoring method as described in any one of claims 1 to 3 includes: The data acquisition module is used to collect flap system data and aircraft airspeed during aircraft operation; the flap system data includes: flap angle, flap handle position, parameters of flap feedback position sensor FPPU, parameters of flap instrument position sensor IPPU, flap system fault status, and pressure data of flap hydraulic system. The retraction function monitoring module is used to monitor the automatic flap retraction function based on the pressure data, the aircraft airspeed, the flap angle, and the flap handle position. The takeoff overspeed monitoring module is used to monitor takeoff flap configuration overspeed based on the flap angle and airspeed of the aircraft during the takeoff phase. The position deviation monitoring module is used to monitor the position deviation of the flap sensor based on the flap angle, the parameters of the FPPU, and the parameters of the IPPU. The hydraulic valve monitoring module is used to monitor the status of the flap hydraulic valve based on the fault status of the flap system and the pressure data. The flap status monitoring module is used to obtain flap status monitoring results based on the monitoring of the automatic flap retraction function, the overspeed monitoring of the takeoff flap shape, the over-tolerance monitoring of the flap sensor position, and the status monitoring of the flap hydraulic valve, so as to be used for fault diagnosis.

5. A computer device, characterized in that, The system includes a processor and a memory, the memory storing a computer program configured to be executed by the processor, wherein the processor, when executing the computer program, implements the aircraft flap status monitoring method as described in any one of claims 1 to 3.

6. A computer-readable storage medium, characterized in that, The computer-readable storage medium stores a computer program, wherein when the device containing the computer-readable storage medium executes the computer program, it implements the aircraft flap status monitoring method as described in any one of claims 1 to 3.

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