A fault component diagnosis method and device based on GPWS alarm and an aircraft

Abstract

The application relates to a GPWS alarm-based fault component diagnosis method, device and aircraft. The GPWS alarm-based fault component diagnosis method comprises the following steps: detecting and resetting the circuit breaker of a GPWC and a weather radar according to a GPWS false alarm; judging whether the reset GPWS is normal; if yes, diagnosing no fault; if no, simultaneously performing weather radar and FWC fault diagnosis on the visual channel and FWC of the current aircraft, and sending a state diagnosis signal of the corresponding component according to the fault diagnosis result; then performing weather radar and FWC fault diagnosis on the auditory channel GPWC in sequence, and sending a state diagnosis signal of the corresponding component according to the fault diagnosis result, and completing all component diagnosis. The GPWS alarm-based fault component diagnosis method has the advantages that when a GPWS false alarm occurs, the weather radar, FWC or GPWC fault component can be more quickly identified and positioned, repeated glide back is avoided, and the efficiency and accuracy of fault diagnosis are significantly improved.

Description

Technical Field

[0001] This invention relates to the field of fault diagnosis of aircraft electronic systems, and in particular to a method, apparatus, aircraft, electronic equipment and computer-readable storage medium for diagnosing faulty components based on GPWS alarms. Background Technology

[0002] During the taxiing process in preparation for takeoff, the crew performs self-checks on various aircraft systems to ensure flight safety. This self-check primarily involves observing the operational status of critical aircraft systems displayed on the Electronic Centralized Aircraft Monitor (ECAM). Based on this status, potential faults are identified and eliminated to ensure safe takeoff and flight. However, some system faults may not be eliminated through simple resets or routine checks. If a system malfunction prevents the aircraft from meeting operational requirements, it must taxi back for maintenance to ensure safety.

[0003] In July 2024, an Airbus aircraft, 1623, was taxiing out of an airport in preparation for takeoff when it displayed the NAV GPWSFAULT and NAV GPWS TERR DET FAULT warnings. After the crew attempted to reset the warnings according to standard procedures, they found that the reset was ineffective. This caused the Enhanced Ground Proximity Warning System (EGPWS) to malfunction, meaning that the aircraft did not meet the Minimum Equipment List (MEL) requirements and could not continue taking off. Therefore, the 1623 aircraft had to taxi back for maintenance.

[0004] The NAV GPWS FAULT and NAV GPWS TERR DET FAULT are false alarms issued by the Ground Proximity Warning Computer (GPWC) in the EGPWS or GPWS. Although these alarms are usually caused by malfunctions in the navigation system or terrain detection function, the EGPWS or GPWS relies on multiple systems, including radio altimeters, navigation sensors, weather radar, flight warning systems (FWS), and terrain databases. Data transmission problems or calculation anomalies in any part of these systems can trigger the alarm.

[0005] Therefore, after the current 1623 aircraft taxis back, maintenance personnel, according to the Troubleshooting Manual (TSM), diagnose the corresponding warning system computers by isolating and analyzing data from the Ground Approach Warning Computer (GPWC), Flight Warning Computer (FWC), and weather radar, in order to identify potentially faulty components for replacement or repair. Since the EGPWS or GPWS involves multiple interactive systems, the troubleshooting process using the TSM is time-consuming. Airbus's troubleshooting method involves checking whether the EGPWC PIN AB / 5D is grounded, and then proceeding step-by-step. For details, please refer to [link / reference]. Figure 1 .

[0006] However, when aircraft 1623 completed its maintenance and taxied back for takeoff, both the NAV GPWS FAULT and NAV GPWS TERR DET FAULT alarms reappeared, forcing the aircraft to taxi back for maintenance again, wasting significant time and resources. Furthermore, the repeated taxiing backs caused panic among passengers on aircraft 1623 due to a lack of understanding of the specific reasons, leading to passenger loss and consequently impacting the airline's reputation. Therefore, existing technologies for troubleshooting EGPWS alarms are inefficient and inaccurate, resulting in frequent aircraft taxiing backs. Summary of the Invention

[0007] Therefore, the purpose of this invention is to provide a fault component diagnosis method based on GPWS alarms.

[0008] A fault component diagnosis method based on GPWS alarms includes the following steps:

[0009] S1. Based on the GPWS error alarm, check and reset the circuit breakers of GPWC and weather radar; and determine whether GPWS returns to normal after reset: if yes, the aircraft is considered to be without fault; if no, execute steps S2A and S2B simultaneously.

[0010] S2A performs visual channel detection and fault diagnosis on the current GPWC of the aircraft, and sends a weather radar status diagnosis signal based on the fault diagnosis results.

[0011] S2B performs FWC detection and fault diagnosis on the current aircraft and sends an FWC status diagnosis signal based on the fault diagnosis results.

[0012] S3. Determine whether the current weather radar status diagnosis signal indicates a fault: if yes, proceed to step S5; if no, proceed to step S4.

[0013] S4. Based on the current status of FWC, perform auditory channel detection and fault diagnosis on the current GPWC of the aircraft, and send a status diagnosis signal from a weather radar based on the fault diagnosis results.

[0014] S5. Based on the current status of the weather radar, perform GPWC self-test and fault diagnosis on the current GPWS of the aircraft, and send a GPWC status diagnosis signal based on the fault diagnosis results to complete the diagnosis of all components.

[0015] The status diagnostic signals of the weather radar, FWC, and GPWC represent the diagnostic results of the weather radar, FWC, and GPWC, respectively. When the diagnostic result indicates that the corresponding component is faulty, the diagnostic process is paused, the corresponding component is replaced first, the status of the corresponding component is updated after replacement, and the diagnostic process continues.

[0016] The fault component diagnosis method based on GPWS alarm described in this invention, compared with the prior art, diagnoses the fault grounding signals of the visual channel, flight warning computer (FWC), auditory channel and ground proximity warning computer (GPWC). Based on the diagnosis results, it can quickly identify the faulty component and replace it first, thereby effectively reducing the risk of multiple skidbacks and significantly improving maintenance efficiency.

[0017] Further, step S2A includes the following sub-steps:

[0018] S2A1: The grounding signal is detected and acquired through the built-in test equipment of GPWC, and the grounding signal is used as the visual channel status information.

[0019] S2A2. Determine the visual channel status information: If any grounding signal exists in the visual channel status information, set the status diagnosis signal of the weather radar to "weather radar has a fault";

[0020] If there is no grounding signal in the visual channel status information, the status diagnosis signal of the weather radar is set to "no fault in the weather radar";

[0021] Step S2B includes the following sub-steps:

[0022] S2B1: Obtain the grounding signal of FWC stall, the grounding signal of FWC self-test abnormality, and the grounding signal of the failure of the subsystem associated with FWC, and use the grounding signal as PWC status information.

[0023] S2B2. Determine the PWC status information: If any grounding signal exists in the FWC status information, then set the FWC status diagnosis signal to "FWC has a fault";

[0024] If there is no grounding signal in the FWC status information, then the FWC status diagnostic signal is set to "FWC fault does not exist".

[0025] Because only the alarm information issued by the weather radar and GPWC exists in the visual channel of the navigation display, and if alarms occur simultaneously, the weather radar will issue a suppression signal to prioritize the display of weather radar-related alarm information in the navigation display. For example, when the weather radar has grounding signals such as WXR1(1SQ1)BUS HAZARD, GPWC(1WZ) or NORADAR1 DATA, the corresponding alarm will be displayed in the navigation display.

[0026] In addition, the FWC has the highest alarm priority in the auditory channel. During the diagnostic process, if the FWC generates any fault signal, the system will issue a corresponding alarm and suppress other low-priority alarm information. Therefore, FWC faults need to be investigated first.

[0027] Based on this, the present invention determines whether a faulty component needs to be replaced by simultaneously diagnosing the highest priority related components in the visual and auditory channels, thereby achieving priority troubleshooting, reducing diagnostic interference, and improving the accuracy and efficiency of fault diagnosis.

[0028] Further, step S4 includes the following sub-steps:

[0029] S41. When the current state of the FWC is that there is no fault or the replacement has been completed, the audio suppression signal in the auditory channel is acquired and used as the auditory channel status information.

[0030] S42. Determine the auditory channel status information: If there is an audio suppression signal in the auditory channel status information, set the status diagnosis signal of the weather radar to "the weather radar is faulty";

[0031] If there is no audio suppression signal in the auditory channel status information, the status diagnosis signal of the weather radar is set to "no fault exists in the weather radar".

[0032] In the auditory channels of an aircraft system, alarms may be issued by the FWC, weather radar, and GPWC. When multiple warning computer ground fault signals occur simultaneously, the FWC with the highest alarm priority will issue a suppression signal to prioritize playing the FWC's fault information.

[0033] Based on this, the present invention determines whether there is an intermittent or latent fault in the weather radar by obtaining an audio suppression signal in the auditory channel after eliminating the fault of the FWC in the aforementioned step S2B. This ensures that the fault of the weather radar will not be missed in the process of detection only in the visual channel, thereby preventing secondary or multiple slipbacks caused by missed detection, and significantly improving the accuracy and reliability of maintenance.

[0034] Further, step S5 includes the following sub-steps:

[0035] If the weather radar is currently in a fault-free state or has been replaced, then a GPWC self-test will be performed, and fault diagnosis will be conducted:

[0036] When the current status of the FWC is no fault or has been replaced, and there is no GPWS error alarm after the GPWC self-test, the status diagnostic signal of the GPWC is set to "GPWC no fault".

[0037] If a GPWS error alarm occurs after the GPWC self-test, the GPWC status diagnostic signal is set to "GPWC has a fault".

[0038] Since the aforementioned steps have fully ruled out faults in the weather radar and FWC, if the GPWS error alarm still exists after the GPWC self-test, it can be directly inferred that there is a fault in the GPWC. The above methods ensure the completeness of the fault diagnosis, ensure that all potential problems are eliminated, and significantly improve maintenance efficiency and flight safety.

[0039] A fault component diagnostic device based on GPWS alarm includes a circuit breaker status diagnostic unit, a visual channel status diagnostic unit, an FWC status diagnostic unit, a weather radar status judgment unit, an auditory channel status diagnostic unit, and a GPWS status diagnostic unit.

[0040] The circuit breaker status diagnostic unit is used to detect and reset the circuit breakers of GPWC and weather radar according to GPWS error alarms; and to determine whether GPWS has returned to normal after reset: if yes, the aircraft is considered to be without fault; if no, the visual channel status diagnostic unit and FWC status diagnostic unit are called at the same time.

[0041] The visual channel status diagnosis unit is used to perform visual channel detection and fault diagnosis on the current GPWC of the aircraft, and send a status diagnosis signal of a weather radar based on the fault diagnosis result.

[0042] The FWC status diagnostic unit is used to perform FWC detection and fault diagnosis on the current aircraft, and send an FWC status diagnostic signal based on the fault diagnosis result.

[0043] The weather radar status judgment unit is used to determine whether the current weather radar status diagnosis signal is faulty: if yes, the GPWS status diagnosis unit is invoked; if no, the auditory channel status diagnosis unit is invoked.

[0044] The auditory channel status diagnosis unit is used to perform auditory channel detection and fault diagnosis on the current GPWC of the aircraft based on the current FWC status, and send a weather radar status diagnosis signal based on the fault diagnosis result.

[0045] The GPWS status diagnostic unit is used to perform GPWC self-test and fault diagnosis on the current aircraft's GPWS according to the current status of the weather radar, and send a GPWC status diagnostic signal according to the fault diagnosis result to complete the diagnosis of all components.

[0046] The status diagnostic signals of the weather radar, FWC, and GPWC represent the diagnostic results of the weather radar, FWC, and GPWC, respectively. When the diagnostic result indicates that the corresponding component is faulty, the diagnostic process is paused, the corresponding component is replaced first, the status of the corresponding component is updated after replacement, and the diagnostic process continues.

[0047] Furthermore, the visual channel status diagnosis unit includes a visual channel status acquisition module and a visual channel weather radar fault diagnosis module.

[0048] The vision channel status acquisition module is used to detect and acquire the grounding signal through the built-in test equipment of GPWC, and use the grounding signal as vision channel status information.

[0049] The weather radar fault diagnosis module of the visual channel is used to determine the status information of the visual channel.

[0050] If any grounding signal is present in the visual channel status information, the status diagnosis signal of the weather radar will be set to "weather radar has a fault".

[0051] If there is no grounding signal in the visual channel status information, the status diagnosis signal of the weather radar is set to "no fault in the weather radar";

[0052] The FWC status diagnostic unit includes an FWC status acquisition module and an FWC fault diagnosis module;

[0053] The FWC status acquisition module is used to acquire the grounding signal of FWC stall, the grounding signal of FWC self-test abnormality, and the grounding signal of the failure of the subsystem associated with FWC, and use the grounding signal as PWC status information.

[0054] The FWC fault diagnosis module is used to determine the PWC status information.

[0055] If any grounding signal exists in the FWC status information, then the FWC status diagnostic signal is set to "FWC has a fault";

[0056] If there is no grounding signal in the FWC status information, then the FWC status diagnostic signal is set to "FWC does not have a fault";

[0057] The fault diagnosis of the GPWS status diagnostic unit is as follows: when the current status of the weather radar is no fault or has been updated to the point of completion of replacement, a GPWC self-test is performed, and the following judgment is made:

[0058] If no GPWS error alarm is detected after the GPWC self-test, the status diagnostic signal of the GPWC is set to "GPWC fault does not exist";

[0059] If a GPWS error alarm occurs after the GPWC self-test, the GPWC status diagnostic signal is set to "GPWC has a fault".

[0060] Furthermore, the auditory channel status diagnosis unit includes an auditory channel status acquisition module and an auditory channel weather radar fault diagnosis module;

[0061] The auditory channel state acquisition module is used to acquire the audio suppression signal in the auditory channel and use it as auditory channel state information;

[0062] The weather radar fault diagnosis module of the auditory channel is used to determine the status information of the auditory channel.

[0063] If an audio suppression signal is present in the auditory channel status information, the status diagnosis signal of the weather radar is set to "the weather radar is faulty";

[0064] If there is no audio suppression signal in the auditory channel status information, the status diagnosis signal of the weather radar is set to "no fault exists in the weather radar".

[0065] An aircraft equipped with an automatic GPWS alarm self-test includes a FWS, weather radar, GPWS, and a fault component diagnostic device;

[0066] The FWS includes FWC, which is used to monitor the operating status of several systems of the aircraft in real time. When a system abnormality occurs, a corresponding fault grounding signal is generated and sent to the GPWS.

[0067] The weather radar is used to monitor weather conditions and provide real-time data on the environment around the aircraft. When an abnormal situation is detected, it generates a corresponding fault grounding signal and sends it to the GPWS.

[0068] The GPWS includes a GPWC, which is used to analyze the ground fault signals of the FWC and the weather radar, and at the same time detect the status of the GPWC itself: when the GPWC detects any fault signal, it triggers a GPWS error alarm and transmits the alarm information to the fault component diagnostic device.

[0069] The fault component diagnostic device is used to receive GPWS error alarms, diagnose the weather radar, FWC, and GPWC based on the GPWS error alarms, and output corresponding status diagnostic signals based on the diagnostic results; the status diagnostic signals are used to indicate whether the corresponding components need to be replaced.

[0070] The fault location device is the fault component diagnosis device based on GPWS alarm described above.

[0071] To better understand and implement this invention, the following detailed description is provided in conjunction with the accompanying drawings. Attached Figure Description

[0072] Figure 1 A simplified flowchart illustrating the troubleshooting process for faulty components in Airbus's GPWS alarm system;

[0073] Figure 2 This is a schematic diagram of the overall structure of the fault component diagnosis device based on GPWS alarm according to the present invention;

[0074] Figure 3 This is a schematic diagram of the overall process of the fault component diagnosis method based on GPWS alarms described in this invention;

[0075] Figure 4 This is a diagram illustrating a delayed triggering example of a GPWC error alarm. Detailed Implementation

[0076] To address the inefficiencies and inaccurate diagnostics of existing technologies for troubleshooting Ground Proximity Warning System (GPWS) alarms, this invention, upon receiving an erroneous alarm from the EGPWS or GPWS, resets the Ground Proximity Warning Computer (GPWC) and weather radar based on their circuit breaker status, and determines whether the GPWS returns to normal after the reset. If not, a visual channel test is performed on the GPWS, and the weather radar is assessed for malfunction based on the results. Simultaneously, the Flight Warning Computer (FWC) of the current aircraft is tested, and the FWC is assessed for malfunction based on the results. Next, an auditory channel test is performed on the GPWC, and the weather radar is assessed for malfunction based on the results. Finally, a GPWS self-test is performed on the current aircraft, and the GPWC is assessed for malfunction based on the self-test results. Accordingly, this invention, by simultaneously detecting the visual channel of the GPWC and the FWC, further detects the auditory channel of the GPWC and the state of the GPWS itself. This enables faster and more accurate identification and diagnosis of whether the weather radar, FWC, or GPWC is faulty when an erroneous alarm occurs in the EGPWS / GPWS, effectively reducing unnecessary component replacements caused by inaccurate diagnosis, thus avoiding repeated slipbacks and significantly improving the efficiency and accuracy of fault diagnosis.

[0077] Based on the above design, this invention proposes a fault component diagnosis method based on GPWS alarms, and a fault component diagnosis device based on GPWS alarms based on this method.

[0078] Please also refer to Figure 2 and Figure 3 , Figure 2 This is a schematic diagram of the overall structure of the fault component diagnosis device based on GPWS alarm described in this invention. Figure 3 This is a schematic diagram of the overall process of the fault component diagnosis method based on GPWS alarms described in this invention.

[0079] The fault component diagnostic device based on GPWS alarm includes a circuit breaker status diagnostic unit 1, a visual channel status diagnostic unit 2A, an FWC status diagnostic unit 2B, a weather radar status judgment unit 3, an auditory channel status diagnostic unit 4, and a GPWS status diagnostic unit 5.

[0080] The circuit breaker status diagnosis unit 1 is used to perform step S1: detect and reset the circuit breakers of GPWC and weather radar according to the GPWS error alarm; and determine whether the GPWS has returned to normal after the reset: if yes, the aircraft is considered to be without fault; if no, steps S2A and S2B are performed simultaneously.

[0081] Specifically, the circuit breaker status diagnosis unit 1 includes a circuit breaker detection module 11 and a circuit breaker reset status judgment module 12.

[0082] The circuit breaker detection module 11 is used to perform step S11: detect the circuit breakers of GPWC and weather radar according to GPWS error alarm, and obtain the current circuit breaker status of GPWC and weather radar.

[0083] Specifically, when a GPWS error alarm occurs, check whether the circuit breakers of the current GPWC and weather radar have tripped to obtain the current circuit breaker status of the GPWC and weather radar.

[0084] The GPWS error alarms are generally displayed by the ECAM, including NAV GPWS FAULT and NAV GPWS TERRDET FAULT alarms. These alarms are usually used to indicate that the EGPWS or GPWS has an anomaly or malfunction. The malfunctions of the EGPWS or GPWS are usually related to the weather radar, FWC and GPWC, while the malfunctions caused by the FWC are usually accompanied by several other error messages.

[0085] Therefore, by checking the circuit breaker status of the GPWC and weather radar, it can be determined whether the EGPWS or GPWS is not working properly due to electrical problems.

[0086] The circuit breaker reset status judgment module 12 is used to execute step S12: reset the circuit breaker according to the status of GPWC and weather radar, and judge whether GPWS has returned to normal: if yes, the aircraft is considered to be without fault, and the current aircraft continues to taxi and prepare for takeoff; if no, the current aircraft is considered to have a fault source and needs to be inspected, and steps S2A and S2B are executed at the same time.

[0087] Specifically, if a circuit breaker trips in either the GPWC or the weather radar circuit breaker status, the corresponding circuit breaker will be reset. If the GPWC circuit breaker cannot be reset, the weather radar circuit breaker will be reset first.

[0088] After the reset operation is completed, a further check is performed to see if any GPWS error alarms still exist:

[0089] If no GPWS error alarm is detected, the GPWS is considered to be fault-free, and the aircraft continues to taxi according to the flight plan, preparing for takeoff.

[0090] If a GPWS error alarm is present, it is assumed that there is a GPWS malfunction, and the aircraft is taxied back to prepare for maintenance and proceed to the next step.

[0091] Since circuit breaker tripping is usually caused by short-term overload, short circuit or transient fault, a reset operation can rule out these temporary or electrical problems. If the system returns to normal after the reset, it can be considered that the problem was caused by a temporary interruption of the electrical system or excessive load, which can be resolved by resetting the circuit breaker. However, if the alarm still exists after the reset, the problem causing the system error may be more complex, so the aircraft needs to taxi back for further diagnosis and troubleshooting of the faulty component.

[0092] The visual channel status diagnosis unit 2A is used to perform step S2A: to perform visual channel detection and fault diagnosis on the current aircraft's GPWC, and to send a weather radar status diagnosis signal based on the fault diagnosis results.

[0093] Specifically, the visual channel status diagnosis unit 2A includes a visual channel status acquisition module 2A1 and a visual channel weather radar fault diagnosis module 2A2.

[0094] The visual channel state acquisition module 2A1 is used to perform step S2A1: perform visual channel detection on the current aircraft's GPWC to obtain visual channel state information.

[0095] Specifically, grounding signals, including WXR1(1SQ1)BUS HAZARD, GPWC(1WZ), and NO RADAR1 DATA, are detected and acquired using the built-in test equipment (BITE) of GPWC, and are used as visual channel status information.

[0096] The visual channel is the line connecting the Electronic Central Airborne Monitoring System (ECAM) to related components, used to transmit information to displays such as the ECAM for alarm visualization. The weather radar uses a HAZARD BUS to ground the visual alarm information. The HAZARD BUS is primarily used to transmit grounding fault information from the weather radar to the ECAM for visual alarm purposes.

[0097] It is important to note that when multiple alarms occur simultaneously, the system will prioritize them. In the auditory channel, the priority is: FWC Stall Warning > Weather Radar Wind Shear Warning (PWS) > Ground Proximity Warning (EGPWC / GPWC). When a high-priority alarm is triggered, the system will issue a suppression signal to suppress the low-priority alarm signal. However, in the visual channel, the priority is simply: Weather Radar Wind Shear Warning > Ground Proximity Warning (EGPWC / GPWC). This is because the Navigation Display (ND) is typically not used to display stall-related alarm information; stall warnings are usually alerted through pilot maneuvers (such as stick shaker or stick pusher) and auditory signals, rather than being displayed on the ND. Therefore, this invention prioritizes troubleshooting weather radar-related faults based on the visual channel's alarm priority.

[0098] The meteorological radar fault diagnosis module 2A2 of the visual channel is used to perform step S2A2: perform fault diagnosis based on the visual channel status information and send a meteorological radar status diagnosis signal.

[0099] Specifically, the fault diagnosis is as follows: if any grounding signal is present in the visual channel status information, the weather radar is marked as needing to be replaced, and the status diagnosis signal of the weather radar is set to "the weather radar is faulty".

[0100] If there is no grounding signal in the visual channel status information, the weather radar is marked as normal, and the status diagnosis signal of the weather radar is set to "no fault in the weather radar".

[0101] When the status diagnosis signal of the weather radar indicates that the weather radar is faulty, the subsequent diagnosis process is suspended, and the maintenance personnel are instructed to replace the components of the weather radar first. After replacement, the status of the weather radar is updated to eliminate the potential interference of component failure on subsequent diagnosis.

[0102] The FWC status diagnostic unit 2B is used to perform step S2B: perform FWC detection and fault diagnosis on the current aircraft, and send an FWC status diagnostic signal based on the fault diagnosis result.

[0103] Specifically, the FWC status diagnosis unit 2B includes an FWC status acquisition module 2B1 and an FWC fault diagnosis module 32.

[0104] The FWC status acquisition module 2B1 is used to perform step S2B1: perform FWC detection on the current aircraft and obtain FWC status information.

[0105] Specifically, the grounding signals of FWC stall, FWC self-test anomalies, and FWC-related subsystem failures are acquired, and these grounding signals are used as PWC status information.

[0106] Since the core function of the Flight Warning Control (FWC) is to centrally manage the aircraft's warning systems, stall signals and FWC self-test signals can quickly confirm whether the system has malfunctioned. Stall warnings typically do not trigger while the aircraft is taxiing on the ground, as stall is usually related to flight speed and aerodynamics. If an FWC stall warning does occur, it can be directly inferred that there is an anomaly or malfunction in the FWC.

[0107] The FWC fault diagnosis module 2B2 is used to perform step S2B2: perform fault diagnosis based on FWC status information and send an FWC status diagnosis signal.

[0108] Specifically, if any grounding signal is present in the FWC status information, the FWC is marked as needing to be replaced, and the FWC status diagnostic signal is set to "FWC has a fault";

[0109] If there is no grounding signal in the FWC status information, the FWC is marked as normal, and the FWC status diagnostic signal is set to "FWC does not have a fault".

[0110] When the FWC status diagnostic signal indicates that the FWC is faulty, the subsequent diagnostic process is suspended, and maintenance personnel are instructed to replace the FWC component first. After replacement, the status of the FWC is updated to eliminate the potential interference of component failure on subsequent diagnosis.

[0111] The weather radar status judgment unit 3 is used to execute step S3: determine whether the current weather radar status diagnosis signal is faulty; if yes, execute step S5; if no, execute step S4.

[0112] Specifically, when the weather radar status diagnosis signal is "weather radar malfunction", it is considered that there is no need to further detect the weather radar status, and step S5 is executed directly;

[0113] If the weather radar status diagnosis signal is "no fault exists in the weather radar", then it is necessary to further check the status of the weather radar and execute step S41.

[0114] By judging the current status diagnostic signal of the weather radar, the repeated testing of components that have already been ruled out can be avoided, thereby improving the efficiency of fault diagnosis.

[0115] The auditory channel status diagnosis unit 4 is used to perform step S4: perform auditory channel detection and fault diagnosis on the current GPWC of the aircraft based on the current FWC status, and send a weather radar status diagnosis signal based on the fault diagnosis result.

[0116] Specifically, the auditory channel status diagnosis unit 4 includes an auditory channel status acquisition module 41 and an auditory channel weather radar fault diagnosis module 42.

[0117] The auditory channel status acquisition module 41 is used to perform step S41: perform auditory channel detection on the current GPWC of the aircraft according to the current FWC status, and obtain auditory channel status information.

[0118] Specifically, when the current state of the FWC is no fault or has been updated to complete replacement, the auditory channel detection is performed: the audio suppression signal in GPWS_AUDIO is obtained and used as the auditory channel status information.

[0119] The auditory channel is the line connecting the voice playback system and related components, used to transmit relevant alarm information to the loudspeaker for playback, thereby playing alarm information by voice to remind the crew; while GPWS_AUDIO is one of the monitoring data in the auditory channel, which is used to represent the audio signal related to GPWS.

[0120] Through research and experience, it is generally accepted that the auditory channel is not involved in the fault diagnosis of weather radar in the standard TSM procedure. However, this invention has found that acquiring the audio suppression signal (AUDIO INHIB) in the auditory channel can effectively diagnose whether there is a fault in the weather radar. In particular, when the WXR1(1SQ1)BUS HAZARD signal of the visual channel is intermittently grounded and not grounded, the fault may be difficult to capture through the visual channel. Therefore, if the audio suppression signal is captured in the auditory channel, it can be determined that there is an anomaly in the weather radar.

[0121] This is because the FWC has already confirmed no fault through preliminary diagnosis (step S2B), or has already been replaced, but the auditory channel still receives an audio suppression signal. This indicates a high-priority alarm in the auditory channel, namely, a fault in the weather radar. Therefore, this invention uses the suppression signal in the auditory channel (e.g., parameter 0.23.1.357.00, decoded as AUDIO INHIB) to diagnose the weather radar's status, effectively compensating for potential diagnostic omissions that might occur if relying solely on the visual channel, and effectively avoiding multiple slippages.

[0122] Since the parameters characterizing the audio suppression signal may have poor readability, they need to be decoded by an AGS (audio decoding system). For example, this invention decodes the parameter 0.23.1.357.00 into AUDIO INHIB to characterize the features of the audio suppression signal.

[0123] It is important to note that because aircraft operate in harsh environments, signal processing may involve delays to prevent abnormal signals caused by momentary errors. Therefore, the GPWC error alarm may appear some time after the audio suppression signal is received, such as... Figure 4 The diagram shows a delayed triggering example of a GPWC error alarm.

[0124] The weather radar fault diagnosis module 42 of the auditory channel is used to perform step S42: perform fault diagnosis based on the auditory channel status information and send a weather radar status diagnosis signal.

[0125] Specifically, if an audio suppression signal is present in the auditory channel status information, the weather radar is marked as needing to be replaced, and the status diagnosis signal of the weather radar is set to "the weather radar is faulty".

[0126] If there is no audio suppression signal in the auditory channel status information, the weather radar is marked as normal, and the status diagnosis signal of the weather radar is set to "no fault in the weather radar".

[0127] When the status diagnosis signal of the weather radar indicates that the weather radar is faulty, the subsequent diagnosis process is suspended, and the maintenance personnel are instructed to replace the components of the weather radar first. After replacement, the status of the weather radar is updated to eliminate the potential interference of component failure on subsequent diagnosis.

[0128] The GPWS status diagnostic unit 5 is used to execute step S5: based on the current status of the weather radar, perform GPWC self-test and fault diagnosis on the current aircraft's GPWS, and send a GPWC status diagnostic signal based on the fault diagnosis result to complete the diagnosis of all components.

[0129] Specifically, when the weather radar is currently in a fault-free state or has been updated and replaced, a GPWC self-test is performed, and fault diagnosis is conducted:

[0130] If no GPWS error alarm is detected after the GPWC self-test, the GPWC is marked as not needing replacement, and the GPWC status diagnostic signal is set to "GPWC fault not present".

[0131] If a GPWS error alarm occurs after the GPWC self-test, the GPWC is marked as needing to be replaced, and the status diagnostic signal of the GPWC is set to "GPWC has a fault".

[0132] When the GPWC status diagnostic signal indicates that the GPWC is faulty, the maintenance personnel are instructed to replace the GPWC component, and the status of the GPWC is updated after the replacement.

[0133] Since the aforementioned steps have ruled out faults and anomalies related to the weather radar and FWC, if GPWS error alarms still persist, it can be reasonably inferred that the GPWC itself is abnormal or faulty. Based on this, through this multi-level fault diagnosis process, the present invention can accurately locate the source of the fault, thereby ensuring timely detection and replacement when a problem occurs with the GPWC, thus avoiding multiple slipbacks and improving maintenance efficiency.

[0134] Compared to existing technologies, this invention, by sequentially checking the faulty grounding signals of the visual channel, Flight Warning Computer (FWC), auditory channel, and Ground Approach Warning Computer (GPWC), can more quickly and accurately pinpoint the faulty components causing GPWS false alarms. This avoids a lengthy troubleshooting process, effectively reducing the risk of multiple taxiing backs and significantly improving maintenance efficiency. Furthermore, this invention ensures that the aircraft can be repaired and restored to normal operation in the shortest possible time, avoiding passenger misunderstandings or unnecessary panic caused by delays in troubleshooting.

[0135] Based on the same inventive concept, this application also provides an electronic device, which can be a server, desktop computing device, or mobile computing device (e.g., laptop computing device, handheld computing device, tablet computer, netbook, etc.). The device includes one or more processors and a memory, wherein the processor is used to execute a program to implement the fault component diagnosis method based on GPWS alarms according to embodiments of the present invention; the memory is used to store computer programs executable by the processor.

[0136] Based on the same inventive concept, this application also provides a computer-readable storage medium corresponding to the aforementioned embodiments of the fault component diagnosis method based on GPWS alarms. The computer-readable storage medium stores a computer program thereon, which, when executed by a processor, implements the steps of the fault component diagnosis method based on GPWS alarms described in any of the above embodiments.

[0137] This application may take the form of a computer program product implemented on one or more storage media (including but not limited to disk storage, CD-ROM, optical storage, etc.) containing program code. Computer storage media include permanent and non-permanent, removable and non-removable media, and information storage can be implemented by any method or technology. Information may be computer-readable instructions, data structures, program modules, or other data. Examples of computer storage media include, but are not limited to: phase-change memory (PRAM), static random access memory (SRAM), dynamic random access memory (DRAM), other types of random access memory (RAM), read-only memory (ROM), electrically erasable programmable read-only memory (EEPROM), flash memory or other memory technologies, CD-ROM, digital versatile optical disc (DVD) or other optical storage, magnetic tape, magnetic disk storage or other magnetic storage devices, or any other non-transfer medium that can be used to store information accessible by a computing device.

[0138] The embodiments described above are merely examples of several implementations of the present invention, and while the descriptions are relatively specific and detailed, they should not be construed as limiting the scope of the invention. It should be noted that those skilled in the art can make various modifications and improvements without departing from the concept of the present invention, and the present invention also intends to include these modifications and variations.

Claims

1. A fault component diagnosis method based on GPWS alarms, characterized in that: S1. Based on the GPWS error alarm, check and reset the circuit breakers of GPWC and weather radar; and determine whether GPWS returns to normal after reset: if yes, the aircraft is considered to be without fault; if no, execute steps S2A and S2B simultaneously. S2A performs visual channel detection and fault diagnosis on the current GPWC of the aircraft, and sends a weather radar status diagnosis signal based on the fault diagnosis results. S2B performs FWC detection and fault diagnosis on the current aircraft and sends an FWC status diagnosis signal based on the fault diagnosis results. S3. Determine whether the current weather radar status diagnosis signal indicates a fault: if yes, proceed to step S5; if no, proceed to step S4. S4. Based on the current status of FWC, perform auditory channel detection and fault diagnosis on the current GPWC of the aircraft, and send a status diagnosis signal from a weather radar based on the fault diagnosis results. S5. Based on the current status of the weather radar, perform GPWC self-test and fault diagnosis on the current GPWS of the aircraft, and send a GPWC status diagnosis signal based on the fault diagnosis results to complete the diagnosis of all components. The status diagnostic signals of the weather radar, FWC, and GPWC represent the diagnostic results of the weather radar, FWC, and GPWC, respectively. When the diagnostic result indicates that the corresponding component is faulty, the diagnostic process is paused, the corresponding component is replaced first, the status of the corresponding component is updated after replacement, and the diagnostic process continues.

2. The fault component diagnosis method based on GPWS alarm according to claim 1, characterized in that, Step S2A includes the following sub-steps: S2A1: The grounding signal is detected and acquired through the built-in test equipment of GPWC, and the grounding signal is used as the visual channel status information. S2A2, Determine the visual channel status information: If any grounding signal exists in the visual channel status information, set the status diagnosis signal of the weather radar to "weather radar has a fault"; If there is no grounding signal in the visual channel status information, the status diagnosis signal of the weather radar is set to "no fault in the weather radar"; Step S2B includes the following sub-steps: S2B1: Obtain the grounding signal of FWC stall, the grounding signal of FWC self-test abnormality, and the grounding signal of the failure of the subsystem associated with FWC, and use the grounding signal as PWC status information. S2B2. Judge the PWC status information: If there is any grounding signal in the FWC status information, then set the FWC status diagnosis signal to "FWC has a fault"; If there is no grounding signal in the FWC status information, then the FWC status diagnostic signal is set to "FWC fault does not exist".

3. The fault component diagnosis method based on GPWS alarm according to claim 2, characterized in that, Step S4 includes the following sub-steps: S41. When the current state of the FWC is that there is no fault or the replacement has been completed, the audio suppression signal in the auditory channel is acquired and used as the auditory channel status information. S42. Determine the auditory channel status information: If there is an audio suppression signal in the auditory channel status information, set the status diagnosis signal of the weather radar to "weather radar has a fault"; If there is no audio suppression signal in the auditory channel status information, the status diagnosis signal of the weather radar is set to "no fault exists in the weather radar".

4. The fault component diagnosis method based on GPWS alarm according to claim 3, characterized in that, Step S5 includes the following sub-steps: If the weather radar is currently in a fault-free state or has been replaced, then a GPWC self-test will be performed, and fault diagnosis will be conducted: When the current status of the FWC is no fault or has been replaced, and there is no GPWS error alarm after the GPWC self-test, the status diagnostic signal of the GPWC is set to "GPWC no fault". If a GPWS error alarm occurs after the GPWC self-test, the status diagnostic signal of the GPWC is set to "GPWC has a fault".

5. A fault component diagnostic device based on GPWS alarm, characterized in that, It includes a circuit breaker status diagnostic unit, a visual channel status diagnostic unit, an FWC status diagnostic unit, a weather radar status judgment unit, an auditory channel status diagnostic unit, and a GPWS status diagnostic unit. The circuit breaker status diagnostic unit is used to detect and reset the circuit breakers of GPWC and weather radar according to GPWS error alarms; and to determine whether GPWS has returned to normal after reset: if yes, the aircraft is considered to be without fault; if no, the visual channel status diagnostic unit and FWC status diagnostic unit are called at the same time. The visual channel status diagnosis unit is used to perform visual channel detection and fault diagnosis on the current GPWC of the aircraft, and send a status diagnosis signal of a weather radar based on the fault diagnosis result. The FWC status diagnostic unit is used to perform FWC detection and fault diagnosis on the current aircraft, and send an FWC status diagnostic signal based on the fault diagnosis result. The weather radar status judgment unit is used to determine whether the current weather radar status diagnosis signal is faulty: if yes, the GPWS status diagnosis unit is invoked; if no, the auditory channel status diagnosis unit is invoked. The auditory channel status diagnosis unit is used to perform auditory channel detection and fault diagnosis on the current GPWC of the aircraft based on the current FWC status, and send a weather radar status diagnosis signal based on the fault diagnosis result. The GPWS status diagnostic unit is used to perform GPWC self-test and fault diagnosis on the current aircraft's GPWS according to the current status of the weather radar, and send a GPWC status diagnostic signal according to the fault diagnosis result to complete the diagnosis of all components. The status diagnostic signals of the weather radar, FWC, and GPWC represent the diagnostic results of the weather radar, FWC, and GPWC, respectively. When the diagnostic result indicates that the corresponding component is faulty, the diagnostic process is paused, the corresponding component is replaced first, the status of the corresponding component is updated after replacement, and the diagnostic process continues.

6. The fault component diagnosis device based on GPWS alarm according to claim 5, characterized in that, The visual channel status diagnosis unit includes a visual channel status acquisition module and a visual channel weather radar fault diagnosis module. The vision channel status acquisition module is used to detect and acquire the grounding signal through the built-in test equipment of GPWC, and use the grounding signal as vision channel status information. The weather radar fault diagnosis module of the visual channel is used to determine the status information of the visual channel. If any grounding signal is present in the visual channel status information, the status diagnosis signal of the weather radar is set to "weather radar has a fault"; If there is no grounding signal in the visual channel status information, the status diagnosis signal of the weather radar is set to "no fault in the weather radar"; The FWC status diagnostic unit includes an FWC status acquisition module and an FWC fault diagnosis module; The FWC status acquisition module is used to acquire the grounding signal of FWC stall, the grounding signal of FWC self-test abnormality, and the grounding signal of the failure of the subsystem associated with FWC, and use the grounding signal as PWC status information. The FWC fault diagnosis module is used to determine the PWC status information. If any grounding signal exists in the FWC status information, then the FWC status diagnostic signal is set to "FWC has a fault"; If there is no grounding signal in the FWC status information, then the FWC status diagnostic signal is set to "FWC does not have a fault"; The fault diagnosis of the GPWS status diagnostic unit is as follows: when the current status of the weather radar is no fault or has been updated to the point of completion of replacement, a GPWC self-test is performed, and the following judgment is made: If no GPWS error alarm is detected after the GPWC self-test, the status diagnostic signal of the GPWC is set to "GPWC fault not present"; If a GPWS error alarm occurs after the GPWC self-test, the status diagnostic signal of the GPWC is set to "GPWC has a fault".

7. The fault component diagnosis device based on GPWS alarm according to claim 6, characterized in that, The auditory channel status diagnosis unit includes an auditory channel status acquisition module and an auditory channel weather radar fault diagnosis module. The auditory channel state acquisition module is used to acquire the audio suppression signal in the auditory channel and use it as auditory channel state information; The weather radar fault diagnosis module of the auditory channel is used to determine the status information of the auditory channel. If an audio suppression signal is present in the auditory channel status information, the status diagnosis signal of the weather radar is set to "weather radar malfunction". If there is no audio suppression signal in the auditory channel status information, the status diagnosis signal of the weather radar is set to "no fault exists in the weather radar".

8. An aircraft equipped with an automatic GPWS alarm self-test, characterized in that, Includes FWS, weather radar, GPWS, and fault component diagnostic devices; The FWS includes FWC, which is used to monitor the operating status of several systems of the aircraft in real time. When a system abnormality occurs, a corresponding fault grounding signal is generated and sent to the GPWS. The weather radar is used to monitor weather conditions and provide real-time data on the environment around the aircraft. When an abnormal situation is detected, it generates a corresponding fault grounding signal and sends it to the GPWS. The GPWS includes a GPWC, which is used to analyze the ground fault signals of the FWC and the weather radar, and at the same time detect the status of the GPWC itself: when the GPWC detects any fault signal, it triggers a GPWS error alarm and transmits the alarm information to the fault component diagnostic device. The fault component diagnostic device is used to receive GPWS error alarms, diagnose the weather radar, FWC, and GPWC based on the GPWS error alarms, and output corresponding status diagnostic signals based on the diagnostic results; the status diagnostic signals are used to indicate whether the corresponding components need to be replaced. The fault location device is the fault component diagnosis device based on GPWS alarm as described in any one of claims 5-7.

9. An electronic device, comprising: A memory, a processor, and a computer program stored in the memory and executable on the processor, characterized in that, when the processor executes the computer program, it implements the fault component diagnosis method based on GPWS alarms as described in any one of claims 1 to 4.

10. A computer-readable storage medium storing computer-executable instructions, characterized in that, When the computer-executable instructions are executed by the processor, they implement the fault component diagnosis method based on GPWS alarms as described in any one of claims 1 to 4.

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