Aircraft flap state monitoring method, device and equipment and storage medium

Abstract

The invention discloses an aircraft flap state monitoring method, device and equipment and a storage medium. The method comprises the steps that flap system data and aircraft airspeed in the aircraft operation process are collected; according to the pressure data of the hydraulic system, the airspeed of the airplane, the flap angle and the flap handle position, the flap automatic withdrawing function is monitored; taking-off flap form overspeed monitoring is carried out according to the flap angle of the airplane in the taking-off stage and the airplane airspeed; flap sensor position out-of-tolerance monitoring is carried out according to the parameters of the flap angle, the FPPU and the IPPU; and according to the flap system fault state and the hydraulic system pressure data, flap hydraulic valve state monitoring is carried out. According to the invention, comprehensive flap state monitoring is realized, the troubleshooting efficiency and accuracy of the aircraft can be improved, and the safety is guaranteed.

Description

Technical Field

[0001] The present invention relates to the technical field of aircraft detection, and in particular to an aircraft flap status monitoring method, device, equipment and storage medium. Background Art

[0002] Modern civil aircraft are equipped with trailing edge flap systems, which are extended before takeoff and landing to increase lift for the aircraft's wings. The flap system consists of a control computer, power control components, drive shafts, left and right flaps, and a variety of sensors. The system monitors the operating status through sensor data and issues warning messages in the event of a fault.

[0003] However, the system sensor has a certain probability of failure. When the sensor fails, it will output a value that deviates from the normal state. Before the value output by the sensor exceeds the set warning range, maintenance personnel cannot know and take maintenance. The flaps will automatically retract at the overspeed threshold, but no report will be generated. According to the requirements of the maintenance manual, after a flap overspeed event occurs, a series of inspections are required before release. The flap system overspeed currently mainly relies on the crew's report. Maintenance personnel cannot accurately know whether an overspeed event has occurred in each flight segment, which easily leads to over-standard release. Flap system failures generally occur during flight, and maintenance work can only be performed on the ground. The state in flight cannot be fully simulated on the ground. Maintenance personnel cannot know the state of the flap system when the failure occurs, and the troubleshooting efficiency is low. Summary of the invention

[0004] In order to solve the above technical problems, the present invention provides a method, device, equipment and storage medium for monitoring the status of aircraft flaps. By monitoring the automatic retraction function of the flaps, monitoring the overspeed of the takeoff flap configuration, monitoring the position of the flap sensor and monitoring the status of the flap hydraulic valve, comprehensive monitoring of the status of the aircraft flaps is achieved, thereby improving the efficiency and accuracy of troubleshooting.

[0005] An embodiment of the present invention provides a method for monitoring an aircraft flap state, comprising:

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

[0007] Monitor the automatic retraction function of the flaps according to the pressure data, the aircraft airspeed, the flap angle, and the flap handle position;

[0008] Performing takeoff flap configuration overspeed monitoring according to the flap angle and the aircraft airspeed of the aircraft during the takeoff phase;

[0009] Perform flap sensor position out-of-tolerance monitoring according to the flap angle, the FPPU parameters, and the IPPU parameters;

[0010] monitoring the state of the flap hydraulic valve according to the flap system fault state and the pressure data;

[0011] Based on the flap automatic retraction function monitoring, the takeoff flap configuration overspeed monitoring, the flap sensor position out-of-tolerance monitoring and the flap hydraulic valve status monitoring, the flap status monitoring result is obtained for troubleshooting.

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

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

[0014] Performing automatic flap unloading monitoring according to the pressure data, the aircraft airspeed and the flap angle;

[0015] The flaps are automatically monitored based on the pressure data, the aircraft airspeed, the flap angle and the flap handle position.

[0016] As an improvement of the above solution, the flap automatic unloading monitoring is performed according to the pressure data, the aircraft airspeed and the flap angle, including:

[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, a 2-position flap automatic unloading event is generated;

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

[0020] As an improvement of the above solution, the automatic flap monitoring according to 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 at a preset position, the aircraft airspeed is not less than a preset first airspeed, and the flap angle is at a preset fourth angle, a flap automatic action event is generated.

[0022] As an improvement of the above solution, the takeoff flap configuration overspeed monitoring is performed according to the flap angle and the aircraft airspeed of the aircraft during the takeoff phase, including:

[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 take-off phase, a take-off flap configuration overspeed event is generated.

[0024] As an improvement of the above solution, the flap sensor position out-of-tolerance monitoring is performed according to the flap angle, the FPPU parameter, and the IPPU parameter, including:

[0025] If the flap angle is within the preset angle range, judging whether the position difference of each sensor group is greater than a preset threshold and the duration is greater than a preset duration according to the parameters of the FPPU and the parameters of the IPPU;

[0026] If there is a position difference of a sensor group that is greater than a preset threshold and lasts longer than a preset duration, a flap sensor position out-of-tolerance event is generated.

[0027] As an improvement of the above solution, the flap hydraulic valve status monitoring is performed according to the flap system fault status and the pressure data, including:

[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 time, a flap hydraulic valve closing event is generated.

[0029] The embodiment of the present invention further provides an aircraft flap status monitoring device, comprising:

[0030] A 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] A retraction function monitoring module, used for monitoring the automatic retraction function of the flaps according to the pressure data, the aircraft airspeed, the flap angle and the flap handle position;

[0032] A takeoff overspeed monitoring module, used for performing takeoff flap configuration overspeed monitoring according to the flap angle and the aircraft airspeed of the aircraft during the takeoff phase;

[0033] A position tolerance monitoring module, used for monitoring the position tolerance of a flap sensor according to the flap angle, the parameters of the FPPU, and the parameters of the IPPU;

[0034] A hydraulic valve monitoring module, used for monitoring the state of the flap hydraulic valve according to the flap system fault state and the pressure data;

[0035] The flap status monitoring module is used to obtain flap status monitoring results for troubleshooting based on the flap automatic retraction function monitoring, the takeoff flap configuration overspeed monitoring, the flap sensor position over-tolerance monitoring and the flap hydraulic valve status monitoring.

[0036] An embodiment of the present invention further provides a computer device, comprising a processor and a memory, wherein a computer program is stored in the memory, and the computer program is configured to be executed by the processor, and when the processor executes the computer program, the aircraft flap status monitoring method described in any one of the above items is implemented.

[0037] An embodiment of the present invention further provides a computer-readable storage medium, wherein the computer-readable storage medium stores a computer program, wherein when the computer program is running, the device where the computer-readable storage medium is located is controlled to execute any of the above-mentioned aircraft flap status monitoring methods.

[0038] Compared with the prior art, the beneficial effects of the aircraft flap status monitoring method, device, equipment and storage medium provided by the embodiments of the present invention are: by collecting flap system data and aircraft airspeed of each flight segment, flap automatic retraction function monitoring, takeoff flap configuration overspeed monitoring, flap sensor position out-of-tolerance monitoring and flap hydraulic valve status monitoring are performed, thereby realizing comprehensive aircraft flap status monitoring. When the flap system automatic retraction function fails, the maintenance personnel are prompted to troubleshoot; when the flap overspeed event occurs, the maintenance personnel are prompted to perform relevant inspections to avoid exceeding the standard release; when the flap sensor performance decreases, the maintenance personnel are prompted to replace the sensor in time to avoid failure; when the flap system fails, the pressure fluctuation analysis of the corresponding hydraulic system is used to determine whether the corresponding hydraulic valve is in a closed state, and the maintenance personnel are assisted in troubleshooting. The embodiments of the present invention improve the efficiency and accuracy of fault detection and ensure the safety of aircraft operation. BRIEF DESCRIPTION OF THE DRAWINGS

[0039] Figure 1 It is a flow chart of a method for monitoring the status of an aircraft flap provided by an embodiment of the present invention;

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

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

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

[0043] Figure 5 It is a schematic diagram of a flow chart of overspeed monitoring of takeoff flap configuration provided by an embodiment of the present invention;

[0044] Figure 6 It is a schematic diagram of a flow chart of flap sensor position out-of-tolerance monitoring provided by an embodiment of the present invention;

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

[0046] Figure 8 It is a schematic diagram of a flow chart of flap hydraulic valve status monitoring provided by an embodiment of the present invention;

[0047] Fig. 9 It is a structural schematic diagram of an aircraft flap status monitoring device provided by an embodiment of the present invention;

[0048] Fig.10 It is a structural schematic diagram of a computer device provided by an embodiment of the present invention. DETAILED DESCRIPTION

[0049] The following will be combined with the drawings in the embodiments of the present invention to clearly and completely describe the technical solutions in the embodiments of the present invention. Obviously, the described embodiments are only part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the present invention.

[0050] See also Figure 1 , Figure 1 1 is a flow chart of a method for monitoring the status of an aircraft flap provided by an embodiment of the present invention. The method for monitoring the status of an aircraft flap comprises:

[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, the embodiment of the present invention collects and analyzes data from aircraft system sensors, and then determines the state of the flap system according to the analysis results. The system sensors include: flap interconnection support sensor, hydraulic system pressure sensor, atmospheric data airspeed sensor, flap feedback position sensor unit (FPPU), acquisition position sensor unit (APPU), and flap instrument position sensor unit (IPPU).

[0053] See also Figure 2 , Figure 2 This is the schematic diagram of the flap system. Among them, CONTROL LEVER, control lever; COMMAND SENSOR UNIT, command sensor unit; SFCC1 / SFCC2, slat / flap control computer 1 / 2; WTB, wing tip brake; APPU, asymmetric position acquisition unit; FLAP TRACK 4SENSOR, flap track 4 sensor; FLAP DISCONNECTSENSORS, flap disconnect sensor; FPPU, flap power unit; IPPU, integrated position acquisition unit; ECAM, electronic centralized aircraft monitoring system; DIF GEAR BOX, differential gear box; M (Motor), electric motor; POB, pressure control brake; VALVEBLOCK, valve block; YELLOW / GREEN, yellow / green (channel of hydraulic system).

[0054] In the flap system, the pilot inputs flap instructions through the control stick, and the command sensor unit transmits the control instructions to SFCC1 and SFCC2; FPPU and IPPU work together to transmit flap power to the differential gearbox and monitor the flap position through a series of sensors; the differential gearbox drives the expansion and retraction of the flaps through the motor (M), and the movement of the flaps is controlled by the valve blocks in the yellow and green hydraulic systems to ensure the smooth movement of the flaps; POB will brake when the set hydraulic pressure is reached during the expansion or retraction of the flaps, and can quickly stop the movement of the flaps in an emergency. The flap system is based on hydraulic pressure and motor drive, and is precisely controlled by multiple sensors and control computers to ensure the safety of the flaps during flight.

[0055] In the embodiment of the present invention, the data of the flap system sensor and the flap computer signal are collected at a certain interval (generally 1 second) from the start of the engine during the operation of the aircraft, and the collected data of each flight segment is stored in the form of a file. By analyzing the collected data, it can be determined whether an abnormal situation occurs during the flight, and then by setting different judgment logics, different events are generated for different abnormal situations to prompt maintenance personnel to take measures for maintenance, thereby ensuring the safety of aircraft operation.

[0056] The acquired sensor data include: flap position parameters (i.e. 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.

[0057] Among them, the flap position parameter refers to the angle value of the flap extension. When the flap handle is in the 0 position, the flap angle is 0 degrees; when the flap handle is in the 1 position, the flap may have two angles. If the handle is from 0 to 1, the flap angle may be 8.5 degrees (airspeed is less than or equal to 100 knots) or 0 degrees (airspeed is greater than 100 knots); if the flap handle is from FULL, 3, 2 to 1, the flap angle may be 8.5 degrees (airspeed is less than 200 knots) or 0 degrees (airspeed is greater than or equal to 200 knots); when the flap handle is in the 2 position, the flap angle is 14.5 degrees; when the flap handle is in the 3 position, the flap angle is 22.5 degrees; when the flap handle is in the FULL position, the flap angle is 32 degrees. Aircraft airspeed refers to the airspeed value detected by the aircraft sensor (Air Speed).

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

[0059] S2: monitoring the automatic retraction function of the flaps according to the pressure data, the aircraft airspeed, the flap angle and the flap handle position.

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

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

[0062] Performing automatic flap unloading monitoring according to the pressure data, the aircraft airspeed and the flap angle;

[0063] The flaps are automatically monitored based on the pressure data, the aircraft airspeed, the flap angle and the flap handle position.

[0064] As one of the optional embodiments, the flap automatic unloading monitoring is performed according to the pressure data, the aircraft airspeed and the flap angle, including:

[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, a 2-position flap automatic unloading event is generated;

[0066] If the pressure data is greater than the first pressure value, the aircraft airspeed is within a preset second airspeed range, and the flap angle is at a preset second angle, a 3-position 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, 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 the hydraulic system during extension and retraction. When the flaps are deployed to a certain angle and reach the preset pressure, the system will monitor the pressure level of the hydraulic system through the pressure sensor. If the pressure exceeds or is insufficient to maintain safe operation, the system will trigger the unloading procedure and automatically retract or adjust the flaps to avoid overload or failure of the hydraulic system.

[0070] See also Figure 3 , Figure 3 The figure is a flow chart of flap automatic unloading monitoring. When the flap system is working, SFCC1 controls the yellow hydraulic system and SFCC2 controls the green hydraulic system. The prerequisite for achieving flap automatic unloading is that at least one of the pressures of the yellow hydraulic system and the green hydraulic system is within the normal range. Secondly, it is also related to the current position of the flap and the real-time airspeed: when the airspeed is greater than or equal to 198.5 knots, if the flap position is 14.5 degrees, the 2-position flap automatic unloading event is triggered; when the airspeed is greater than or equal to 188.5 knots, if the flap position is 22.5 degrees, the 3-position flap automatic unloading event is triggered; when the airspeed is greater than or equal to 182.5 knots, if the flap position is 32.5 degrees, the FULL-position flap automatic unloading event is triggered.

[0071] As one of the optional embodiments, the automatic flap monitoring according to 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 at a preset position, the aircraft airspeed is not less than a preset first airspeed, and the flap angle is at a preset fourth angle, a flap automatic action event is generated.

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

[0074] For details, please refer to Figure 4 , Figure 4 This is a flowchart of flap automatic monitoring. The main parameters used in this monitoring include: yellow hydraulic system and green hydraulic system pressure, flap handle position, flap angle, and aircraft airspeed. Flap automatic actuation is a protection function for 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 prerequisite for flap automatic actuation is that at least one of the yellow hydraulic system and the green hydraulic system has sufficient system 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, then a flap automatic actuation event is generated.

[0075] S3: Perform takeoff flap configuration overspeed monitoring according to the flap angle and the aircraft airspeed of the aircraft during the takeoff phase.

[0076] As one of the optional embodiments, the taking-off flap configuration overspeed monitoring is performed according to the flap angle and the aircraft airspeed of the aircraft during the take-off phase, including:

[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 take-off phase, a take-off flap configuration overspeed event is generated.

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

[0079] See also Figure 5 , Figure 5 It is a flowchart of overspeed monitoring for takeoff flap configuration.

[0080] Specifically, during takeoff, the aircraft flaps are in 1+F configuration, and the maximum speed is 215 knots. If the aircraft flaps are not retracted to the 0 degree position when the airspeed is greater than 215 knots, it is determined that a flap takeoff configuration overspeed event has occurred. According to the requirements of 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: monitoring the flap sensor position out-of-tolerance according to the flap angle, the FPPU parameters, and the IPPU parameters.

[0082] As one of the optional embodiments, the flap sensor position out-of-tolerance monitoring according to the flap angle, the FPPU parameter, and the IPPU parameter includes:

[0083] If the flap angle is within the preset angle range, judging whether the position difference of each sensor group is greater than a preset threshold and the duration is greater than a preset duration according to the parameters of the FPPU and the parameters of the IPPU;

[0084] If there is a position difference of a sensor group that is greater than a preset threshold and lasts longer than a preset duration, a flap sensor position out-of-tolerance event is generated.

[0085] Specifically, the flap shaft sensor mainly includes FPPU and IPPU. The part number and principle of each FPPU and IPPU are the same, and both include: spline input shaft, spring-loaded locking plate, reduction gear, reduction gear housing, two independently working synchronous transmitters, synchronizer cover, electrical connector block and a cover plate. The flap drive shaft is connected to the spline input shaft of PPU. When the flap is in the 0 position, PPU is also set to 0 degrees. When the flap drive shaft rotates, it will drive the spline shaft of PPU to rotate, and the transmitter of PPU will send out an angle signal. Both FPPU and IPPU are installed on the flap drive shaft, so under normal conditions, the angles indicated by all PPUs are the same.

[0086] Among them, the parameters of FPPU include: FPPU1 and FPPU2; FPPU1 is the FPPU feedback position signal (system 1), and its parameter source is SFCC1; FPPU2 is the FPPU feedback position signal (system 2), and its parameter source is SFCC2.

[0087] The parameters of IPPU include: IPPU1L1, IPPU2L1, IPPU1L2, IPPU2L2; IPPU1L1 is the signal from IPPU module 1 to FWC1 system, and its parameter source is FWC L1; IPPU2L1 is the signal from IPPU module 2 to FWC1 system, and its parameter source is FWC L1; IPPU1L2 is the signal from IPPU module 1 to FWC2 system, and its parameter source is FWC L2; IPPU2L2 is the signal from IPPU module 2 to FWC2 system, and its parameter source is 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 work. By monitoring whether the output signal of the sensor has deviations, it can be determined whether there is a failure trend inside the PPU.

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

[0090] See also Figure 6 , Figure 6 The flow chart of flap sensor position out-of-tolerance monitoring. The flap sensor position out-of-tolerance monitoring first determines whether the flap angle is within the threshold range of 0-2, 7-9, 12-16, 20-24, 30-34. If so, continue to detect the PPU signal out-of-tolerance; when the difference between FPPU1 and FPPU2 is greater than 3 degrees for 8 consecutive seconds, an FPPU channel signal out-of-tolerance event is generated; when the difference between IPPU1L1 and IPPU2L1 is greater than 3 degrees for 8 consecutive seconds, an IPPU FWC1 signal out-of-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 IPPUFWC1 and 2 signal out-of-tolerance event 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 of 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 of FWC2 is generated.

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

[0092] As one of the optional embodiments, the flap hydraulic valve status monitoring according to 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 time, a flap hydraulic valve closing event is generated.

[0094] For details, please refer to Figure 7 , Figure 7 This is the schematic diagram of the flap hydraulic system. Among them, YELLOW SYSTEM, yellow hydraulic system; GREEN SYSTEM, green hydraulic system; PRESSURE, pressure; RETURN, return; SLATS SYSTEM, slat system; VALVE BLOCK, valve group; DIFF G / B, differential gearbox; POWER CONTROL UNIT, power control unit.

[0095] The flap system power control component is driven by two hydraulic systems, namely the yellow hydraulic system and the green hydraulic system. Each hydraulic system is connected to the hydraulic motor (M) and the brake (POB) through a valve module (VALVE BLOCK). The valve module controls the on / off and flow direction of the hydraulic oil by controlling the switch of the valve through the solenoid valve, thereby controlling the rotation direction of the hydraulic motor to drive the transmission shaft to rotate in different directions, thereby realizing the retraction and extension action of the flap system.

[0096] Under normal circumstances, the two hydraulic modules of the power control assembly work simultaneously. If a signal to extend or retract the flaps is received, the two hydraulic systems control their respective motors to drive the transmission shafts. If one hydraulic system fails or the control module fails, the power control assembly can also drive the flap shaft to rotate with only one computer and hydraulic system, but the speed will be reduced.

[0097] The normal working pressure of the yellow hydraulic system and the green hydraulic system is about 3000psi. When the flaps are driven, the hydraulic motor needs to work, so the pressure of the hydraulic system will drop significantly (about 200psi). However, if the valve is not opened due to a computer failure or a valve body failure, the pressure of the hydraulic system will not drop. Therefore, by monitoring the pressure drop of the hydraulic system, the status of the flap hydraulic valve module can be judged.

[0098] For details, please refer to Figure 8 , Figure 8 It is a flow chart of flap hydraulic valve status monitoring.

[0099] When flap system 1 fails, the pressure of the yellow hydraulic system 10 seconds after the failure is compared with the pressure of the yellow hydraulic system at the time of the failure. If the pressure rises, the pressure of the green hydraulic system and the yellow hydraulic system are compared at the same time 10 seconds after the failure. If the pressure of the yellow hydraulic system is greater than the pressure of the green hydraulic system, the closing event of the yellow hydraulic valve is triggered;

[0100] When flap system 2 fails, compare the green hydraulic system pressure 10 seconds after the failure with the green hydraulic system pressure at the time of the failure. If the pressure rises, compare the pressures of the green hydraulic system and the yellow hydraulic system 10 seconds after the failure at the same time. If the green hydraulic system pressure is greater than the yellow hydraulic system pressure, the green hydraulic valve closing event is triggered.

[0101] S6: Based on the flap automatic retraction function monitoring, the takeoff flap configuration overspeed monitoring, the flap sensor position over-tolerance monitoring and the flap hydraulic valve status monitoring, a flap status monitoring result is obtained for troubleshooting.

[0102] Specifically, since flap overspeed events cannot be monitored through aircraft reports, by monitoring the relationship between the aircraft airspeed and flap angle, if flap overspeed occurs during takeoff after the flight, a corresponding event is triggered to remind maintenance personnel to perform corresponding inspections. By monitoring the pressure drop of the hydraulic system to determine the switch state of the hydraulic valve, when a flap system fails, the switch state of the hydraulic valve can be determined. The embodiment of the present invention collects various parameters of the aircraft flap system and generates a file that can be queried and analyzed after each flight, providing data support for subsequent troubleshooting.

[0103] The embodiments of the present invention can flexibly set the sensor performance monitoring threshold, and screen the sensors with performance degradation when no warning is issued by the system, so as to take precautions before they occur; after an abnormal event occurs, the subscribers can be informed by email or platform notification, and the maintenance personnel can be reminded to take measures; the parameters collected by the flap sensor will be recorded in real time, and can be used as the basis for flap status judgment during ground troubleshooting. The maintenance personnel can accurately understand the system status when the fault occurs through the parameters and accurately troubleshoot; it does not rely on manual judgment whether a flap overspeed event occurs, and can avoid exceeding the standard release.

[0104] The embodiment of the present invention collects flap system data and aircraft airspeed of each flight segment to monitor the automatic retraction function of the flaps, monitor the overspeed of the takeoff flap configuration, monitor the position of the flap sensor out of tolerance, and monitor the status of the flap hydraulic valve, thereby realizing comprehensive monitoring of the aircraft flap status. When the automatic retraction function of the flap system fails, the maintenance personnel are prompted to troubleshoot; when the flap overspeed event occurs, the maintenance personnel are prompted to perform relevant inspections to avoid over-standard release; when the performance of the flap sensor decreases, the maintenance personnel are prompted to replace the sensor in time to avoid failure; when the flap system fails, the pressure fluctuation analysis of the corresponding hydraulic system is used to determine whether the corresponding hydraulic valve is in a closed state, and the maintenance personnel are assisted in troubleshooting. The embodiment of the present invention improves the efficiency and accuracy of fault detection and ensures the safety of aircraft operation. Accordingly, the present invention also provides an aircraft flap status monitoring device, which can realize all the processes of the aircraft flap status monitoring method in the above embodiment.

[0105] See also Fig. 9 , Fig. 9 1 is a schematic diagram of the structure of an aircraft flap state monitoring device provided by an embodiment of the present invention. The aircraft flap state monitoring device comprises:

[0106] The data acquisition module 901 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;

[0107] A retraction function monitoring module 902 is used to monitor the automatic retraction function of the flaps according to the pressure data, the aircraft airspeed, the flap angle and the flap handle position;

[0108] A takeoff overspeed monitoring module 903 is used to perform takeoff flap configuration overspeed monitoring according to the flap angle and the aircraft airspeed of the aircraft during the takeoff phase;

[0109] A position tolerance monitoring module 904 is used to monitor the position tolerance of the flap sensor according to the flap angle, the parameters of the FPPU, and the parameters of the IPPU;

[0110] A hydraulic valve monitoring module 905, for monitoring the state of the flap hydraulic valve according to the flap system fault state and the pressure data;

[0111] The flap status monitoring module 906 is used to obtain flap status monitoring results for troubleshooting based on the flap automatic retraction function monitoring, the takeoff flap configuration overspeed monitoring, the flap sensor position over-tolerance monitoring and the flap hydraulic valve status monitoring.

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

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

[0114] Performing automatic flap unloading monitoring according to the pressure data, the aircraft airspeed and the flap angle;

[0115] The flaps are automatically monitored based on the pressure data, the aircraft airspeed, the flap angle and the flap handle position.

[0116] Preferably, the flap automatic unloading monitoring is performed according to the pressure data, the aircraft airspeed and the flap angle, including:

[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, a 2-position flap automatic unloading event is generated;

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

[0120] Preferably, the automatic flap monitoring according to the pressure data, the aircraft airspeed, the flap angle and the flap handle position comprises:

[0121] If the pressure data is greater than a preset second pressure value, the flap handle position is at a preset position, the aircraft airspeed is not less than a preset first airspeed, and the flap angle is at a preset fourth angle, a flap automatic action 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 take-off phase, a take-off flap configuration overspeed event is generated.

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

[0125] If the flap angle is within the preset angle range, judging whether the position difference of each sensor group is greater than a preset threshold and the duration is greater than a preset duration according to the parameters of the FPPU and the parameters of the IPPU;

[0126] If there is a position difference of a sensor group that is greater than a preset threshold and lasts longer than a preset duration, a flap sensor position out-of-tolerance 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 time, a flap hydraulic valve closing event is generated.

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

[0130] See also Fig.10 , Fig.10 1 is a block diagram of a computer device provided by an embodiment of the present invention, wherein the computer device comprises: 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, the steps in the above-mentioned aircraft flap status monitoring method embodiment are implemented. Alternatively, when the processor 101 executes the computer program, the functions of each module / unit in the above-mentioned device embodiments are implemented.

[0131] Exemplarily, 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 implement the present invention. The one or more modules / units may be a series of computer program instruction segments capable of implementing specific functions, which are used to 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 appreciate that the schematic diagram is merely an example of a computer device and does not constitute a limitation on the computer device, and may include more or fewer components than shown in the diagram, or may combine certain components, or different components, for example, the computer device may also include an input / output device, a network access device, a bus, etc.

[0133] The processor 101 may be a central processing unit (CPU), or other general-purpose processors, digital signal processors (DSP), application-specific integrated circuits (ASIC), field-programmable gate arrays (FPGA) or other programmable logic devices, discrete gate or transistor logic devices, discrete hardware components, etc. A general-purpose processor may be a microprocessor or any conventional processor, etc. The processor 101 is the control center of the computer device, and uses various interfaces and lines to connect various parts of the entire computer device.

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

[0135] Wherein, if the module / unit integrated in the computer device is implemented in the form of a software functional unit and sold or used as an independent product, it can be stored in a computer-readable storage medium. Based on such an understanding, the present invention implements all or part of the processes in the above-mentioned embodiment method, and can also be completed by instructing the relevant hardware through a computer program. The computer program can be stored in a computer-readable storage medium, and the computer program can implement the steps of the above-mentioned various method embodiments when executed by the processor 101. Wherein, the computer program includes computer program code, and the computer program code can be in source code form, object code form, 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, U disk, mobile hard disk, disk, optical disk, computer memory, read-only memory (ROM, Read-Only Memory), random access memory (RAM, Random Access Memory), electric carrier signal, telecommunication signal and software distribution medium, etc.

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

[0137] The embodiment of the present invention provides a method, device, equipment and storage medium for monitoring the status of aircraft flaps, which has the beneficial effects of: by collecting flap system data and aircraft airspeed of each flight segment, flap automatic retraction function monitoring, takeoff flap configuration overspeed monitoring, flap sensor position over-tolerance monitoring and flap hydraulic valve status monitoring are performed, thereby achieving comprehensive aircraft flap status monitoring. When the flap system automatic retraction function fails, the maintenance personnel are prompted to troubleshoot; when the flap overspeed event occurs, the maintenance personnel are prompted to perform relevant inspections to avoid over-standard release; when the flap sensor performance decreases, the maintenance personnel are prompted to replace the sensor in time to avoid failure; when the flap system fails, the pressure fluctuation analysis of the corresponding hydraulic system is used to determine whether the corresponding hydraulic valve is in a closed state, and the maintenance personnel are assisted in troubleshooting. The embodiment of the present invention improves the efficiency and accuracy of fault detection and ensures the safety of aircraft operation.

[0138] The above is a preferred embodiment of the present invention. It should be pointed out that a person skilled in the art can make several improvements and modifications without departing from the principle of the present invention. 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 an aircraft flap, characterized in that: include: 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; Monitor the automatic retraction function of the flaps according to the pressure data, the aircraft airspeed, the flap angle, and the flap handle position; Performing takeoff flap configuration overspeed monitoring according to the flap angle and the aircraft airspeed of the aircraft during the takeoff phase; Perform flap sensor position out-of-tolerance monitoring according to the flap angle, the FPPU parameters, and the IPPU parameters; monitoring the state of the flap hydraulic valve according to the flap system fault state and the pressure data; Based on the flap automatic retraction function monitoring, the takeoff flap configuration overspeed monitoring, the flap sensor position out-of-tolerance monitoring and the flap hydraulic valve status monitoring, the flap status monitoring result is obtained for troubleshooting.

2. The aircraft flap status monitoring method according to claim 1, characterized in that: The flap automatic retraction function monitoring includes: flap automatic unloading monitoring and flap automatic operation monitoring; The monitoring of the automatic flap retraction function according to the pressure data, the aircraft airspeed, the flap angle and the flap handle position includes: Performing automatic flap unloading monitoring according to the pressure data, the aircraft airspeed and the flap angle; The flaps are automatically monitored based on the pressure data, the aircraft airspeed, the flap angle and the flap handle position.

3. The aircraft flap status monitoring method according to claim 2, characterized in that: The automatic flap unloading monitoring is performed according to the pressure data, the aircraft airspeed and the flap angle, including: 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, a 2-position flap automatic unloading event is generated; If the pressure data is greater than the first pressure value, the aircraft airspeed is within a preset second airspeed range, and the flap angle is at a preset second angle, a 3-position 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, a FULL position flap automatic unloading event is generated.

4. The aircraft flap status monitoring method according to claim 2, characterized in that: The automatic flap monitoring according to the pressure data, the aircraft airspeed, the flap angle and the flap handle position comprises: If the pressure data is greater than a preset second pressure value, the flap handle position is at a preset position, the aircraft airspeed is not less than a preset first airspeed, and the flap angle is at a preset fourth angle, a flap automatic action event is generated.

5. The aircraft flap status monitoring method according to claim 1, characterized in that: The taking-off flap configuration overspeed monitoring is performed according to the flap angle and the aircraft airspeed of the aircraft during the take-off phase, including: If the flap angle is greater than zero, the aircraft airspeed is greater than a preset second airspeed, and the aircraft is in the take-off phase, a take-off flap configuration overspeed event is generated.

6. The aircraft flap status monitoring method according to claim 1, characterized in that: The flap sensor position out-of-tolerance monitoring is performed according to the flap angle, the FPPU parameter, and the IPPU parameter, including: If the flap angle is within the preset angle range, judging whether the position difference of each sensor group is greater than a preset threshold and the duration is greater than a preset duration according to the parameters of the FPPU and the parameters of the IPPU; If there is a position difference of a sensor group that is greater than a preset threshold and lasts longer than a preset duration, a flap sensor position out-of-tolerance event is generated.

7. The aircraft flap status monitoring method according to claim 1, characterized in that: The flap hydraulic valve status monitoring according to the flap system fault status and the pressure data includes: 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 time, a flap hydraulic valve closing event is generated.

8. An aircraft flap status monitoring device, characterized in that: include: Data acquisition module, 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; A retraction function monitoring module, used for monitoring the automatic retraction function of the flaps according to the pressure data, the aircraft airspeed, the flap angle and the flap handle position; A takeoff overspeed monitoring module, used for performing takeoff flap configuration overspeed monitoring according to the flap angle and the aircraft airspeed of the aircraft during the takeoff phase; A position tolerance monitoring module, used for monitoring the position tolerance of a flap sensor according to the flap angle, the parameters of the FPPU, and the parameters of the IPPU; A hydraulic valve monitoring module, used for monitoring the state of the flap hydraulic valve according to the flap system fault state and the pressure data; The flap status monitoring module is used to obtain flap status monitoring results for troubleshooting based on the flap automatic retraction function monitoring, the takeoff flap configuration overspeed monitoring, the flap sensor position over-tolerance monitoring and the flap hydraulic valve status monitoring.

9. A computer device, characterized in that: It comprises a processor and a memory, wherein a computer program is stored in the memory, and the computer program is configured to be executed by the processor, and when the processor executes the computer program, the aircraft flap status monitoring method as described in any one of claims 1 to 7 is implemented.

10. A computer-readable storage medium, characterized in that: The computer-readable storage medium stores a computer program, wherein when the device where the computer-readable storage medium is located executes the computer program, the aircraft flap status monitoring method according to any one of claims 1 to 7 is implemented.

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