Fault component diagnosis method and device based on GPWS alarm and aviation aircraft

Abstract

The invention relates to a fault component diagnosis method and device based on a GPWS alarm and an aviation aircraft. The fault component diagnosis method based on the GPWS alarm comprises the following steps: detecting a GPWC and a circuit breaker of a weather radar according to the GPWS error alarm, and performing reset operation; judging whether the reset GPWS returns to normal or not; if yes, diagnosing that no fault exists; if not, weather radar and FWC fault diagnosis is carried out on the visual channel and the FWC of the current aircraft at the same time, and state diagnosis signals of corresponding components are sent according to fault diagnosis results; and then meteorological radar and FWC fault diagnosis is carried out on the auditory channel GPWC in sequence, state diagnosis signals of corresponding components are sent according to fault diagnosis results, and diagnosis of all the components is completed. The fault component diagnosis method based on the GPWS alarm has the advantages that meteorological radar, FWC or GPWC fault components can be recognized and positioned more quickly when the GPWS gives an error alarm, repeated sliding back is avoided, and the efficiency and accuracy of fault diagnosis are remarkably improved.

Description

Technical Field

[0001] The present invention relates to the field of fault diagnosis of aircraft electronic systems, and in particular to a method and device for diagnosing faulty components based on GPWS alarms, an aircraft, an electronic device and a computer-readable storage medium. Background Art

[0002] When an aircraft is taxiing to prepare for takeoff, the crew will perform self-inspections on the aircraft's various systems to ensure flight safety. The self-inspection process mainly observes the operating status of the aircraft's key systems displayed in the Electronic Centralized Aircraft Monitor (ECAM), and eliminates potential faults based on the operating status to ensure that the aircraft takes off and remains safe during flight. However, during the self-inspection process, some system faults may not be eliminated by simple reset or routine testing, and when the system faults cause the aircraft to fail to meet the transport limit requirements, the aircraft must be taxied back for maintenance to ensure the safety of the aircraft.

[0003] In July 2024, when an Airbus 1623 aircraft was taxiing out at an airport for takeoff, the NAV GPWSFAULT and NAV GPWS TERR DET FAULT alarms appeared. After the crew tried to reset according to standard procedures, they found that the reset was invalid, resulting in the failure of the Enhanced Ground Proximity Warning System (EGPWS). That is, the current aircraft did not meet the requirements of the Minimum Equipment List (MEL) and could not continue to take off. Therefore, the 1623 aircraft had to taxi back for maintenance.

[0004] Among them, NAV GPWS FAULT and NAV GPWS TERR DET FAULT are false alarms issued by the Ground Proximity Warning Computer (GPWC) in EGPWS or GPWS. Although this alarm is usually caused by a failure in the navigation system or terrain detection function, since EGPWS or GPWS relies on multiple systems, including radio altimeters, navigation sensors, weather radars, flight warning systems (FWS), and terrain databases, etc., any part of these systems may trigger an alarm when there is a data transmission problem or calculation anomaly.

[0005] Based on this, after the current 1623 aircraft slid back, the maintenance personnel diagnosed the computer (Warning Computer) of the corresponding warning system (Warning System) according to the Troubleshooting Manual (TSM), by gradually isolating and analyzing the data of the ground proximity warning computer (GPWC), the flight warning computer (FWC) and the weather radar, so as to find out the potential faulty parts for replacement or repair. However, EGPWS or GPWS involves multiple interactive systems, so it takes a long time for maintenance personnel to conduct troubleshooting and maintenance according to TSM. The troubleshooting and maintenance of Airbus is to determine whether EGPWC PIN AB / 5D is grounded, and then conduct troubleshooting and maintenance step by step. For details, please refer to Figure 1 .

[0006] However, when the 1623 aircraft was overhauled and taxied out again to prepare for takeoff, the NAV GPWS FAULT and NAV GPWS TERR DET FAULT alarms still appeared, forcing the aircraft to taxi back for maintenance again, wasting a lot of time and resources. At the same time, due to the multiple taxiing backs, the passengers on the 1623 aircraft panicked because they did not know the specific reasons, which caused passenger loss and affected the reputation of the airline. Based on this, the existing technology has the problems of inefficiency and inaccurate diagnosis when troubleshooting the EGPWS alarm, resulting in frequent taxiing backs. Summary of the invention

[0007] Based on this, an object of the present invention is to provide a fault component diagnosis method based on GPWS alarm.

[0008] A method for diagnosing a faulty component based on a GPWS alarm comprises the following steps:

[0009] S1. According to the GPWS error alarm, the circuit breakers of the GPWC and the weather radar are detected and reset; and it is determined whether the GPWS after the reset is restored to normal: if so, it is considered that the aircraft has no fault; if not, steps S2A and S2B are executed simultaneously;

[0010] S2A, perform visual channel detection and fault diagnosis on the GPWC of the current aircraft, and send a weather radar status diagnosis signal according to the fault diagnosis result;

[0011] S2B, perform FWC detection and fault diagnosis on the current aircraft, and send a FWC status diagnosis signal according to the fault diagnosis result;

[0012] S3, determine whether the current status diagnosis signal of the weather radar indicates a fault: if so, execute step S5; if not, execute step S4;

[0013] S4. Performing auditory channel detection and fault diagnosis on the GPWC of the current aircraft according to the current state of the FWC, and sending a weather radar state diagnosis signal according to the fault diagnosis result;

[0014] S5. According to the current state of the weather radar, perform GPWC self-check and fault diagnosis on the GPWS of the current aircraft, and send a GPWC state diagnosis signal according to the fault diagnosis result to complete the diagnosis of all components;

[0015] Among them, the status diagnosis signals of the weather radar, FWC and GPWC respectively represent the diagnosis results of the weather radar, FWC and GPWC. When the diagnosis results indicate that there is a fault in the corresponding component, the diagnosis process is suspended, and the corresponding component is replaced first. After replacement, the status of the corresponding component is updated and the diagnosis process continues.

[0016] Compared with the prior art, the faulty component diagnosis method based on GPWS alarm described in the present invention diagnoses the fault grounding signals of the visual channel, the flight warning computer (FWC), the auditory channel and the ground proximity warning computer (GPWC). According to the diagnosis results, the faulty components can be quickly determined and replaced in priority, thereby effectively reducing the risk of multiple slips and significantly improving maintenance efficiency.

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

[0018] S2A1, detect and obtain the ground signal through the built-in test equipment of GPWC, and use the ground signal as the visual channel status information;

[0019] S2A2, judging the visual channel status information: when there is any ground signal in the visual channel status information, setting the status diagnosis signal of the weather radar to "the weather radar is faulty";

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

[0021] The step S2B comprises the following sub-steps:

[0022] S2B1, obtaining the ground signal of FWC stall, the ground signal of FWC self-test abnormality and the ground signal of FWC associated subsystem failure, and using the ground signal as PWC status information;

[0023] S2B2, judging the PWC status information: if there is any ground signal in the FWC status information, setting the FWC status diagnosis signal to "FWC is faulty";

[0024] If there is no ground signal in the FWC status information, the FWC status diagnosis signal is set to "FWC does not have a fault".

[0025] Since only the alarm information from the weather radar and GPWC exists in the visual channel where the navigation display shows the alarm, and once the alarms occur simultaneously, the weather radar will simultaneously send out a suppression signal to give priority to displaying the alarm information related to the weather radar in the navigation display. For example, when the weather radar has a ground signal such as WXR1 (1SQ1) BUS HAZARD, GPWC (1WZ) or NORADAR1 DATA, the corresponding alarm will be displayed in the navigation display.

[0026] In addition, in the auditory channel, FWC has the highest alarm priority. During the diagnosis process, if 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 checked first.

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

[0028] Furthermore, the 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, an audio suppression signal in the auditory channel is obtained and used as auditory channel state information;

[0030] S42, judging the auditory channel state information: when there is an audio suppression signal in the auditory channel state information, setting the state diagnosis signal of the weather radar to "there is a fault in the weather radar";

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

[0032] In the auditory channel of the aircraft system, alarms may be issued by FWC, weather radar and GPWC. When fault grounding signals from multiple warning computers appear simultaneously, the FWC with the highest alarm priority will send an inhibition signal to give priority to playing the FWC fault information.

[0033] Based on this, the present invention obtains an audio suppression signal in the auditory channel to determine whether the weather radar has an intermittent or hidden fault after eliminating the FWC fault in the aforementioned step S2B, thereby ensuring that the weather radar fault will not be missed due to the process of detection only in the visual channel, thereby preventing secondary or multiple slips caused by missed detection, and significantly improving the accuracy and reliability of maintenance.

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

[0035] When the current status of the weather radar is that there is no fault, or it has been updated to complete replacement, the GPWC self-check is performed and the fault diagnosis is performed:

[0036] When the current state of the FWC is that there is no fault, or the replacement has been completed, and when there is no GPWS error alarm after the GPWC self-check, the state diagnosis signal of the GPWC is set to "GPWC does not have a fault";

[0037] When a GPWS error alarm is present after the GPWC self-check, the status diagnosis signal of the GPWC is set to "GPWC failure present".

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

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

[0040] The circuit breaker status diagnosis unit is used to detect and reset the circuit breakers of the GPWC and the weather radar according to the GPWS error alarm; and determine whether the GPWS after the reset is restored to normal: if so, it is considered that the aircraft has no fault; if not, the visual channel status diagnosis unit and the FWC status diagnosis 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 GPWC of the current aircraft, and send a weather radar status diagnosis signal according to the fault diagnosis result;

[0042] The FWC status diagnosis unit is used to perform FWC detection and fault diagnosis on the current aircraft, and send a FWC status diagnosis signal according to the fault diagnosis result;

[0043] The weather radar status judgment unit is used to judge whether the current weather radar status diagnosis signal indicates a fault: if so, the GPWS status diagnosis unit is called; if not, the auditory channel status diagnosis unit is called;

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

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

[0046] Among them, the status diagnosis signals of the weather radar, FWC and GPWC respectively represent the diagnosis results of the weather radar, FWC and GPWC. When the diagnosis results indicate that there is a fault in the corresponding component, the diagnosis process is suspended, and the corresponding component is replaced first. After replacement, the status of the corresponding component is updated and the diagnosis process continues.

[0047] Further, the visual channel state diagnosis unit includes a visual channel state acquisition module and a weather radar fault diagnosis module of the visual channel;

[0048] The visual channel state acquisition module is used to detect and acquire a ground signal through a built-in test device of the GPWC, and use the ground signal as visual channel state information;

[0049] The weather radar fault diagnosis module of the visual channel is used to judge the state information of the visual channel:

[0050] When there is any ground signal in the visual channel status information, the status diagnosis signal of the weather radar is set to "the weather radar is faulty";

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

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

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

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

[0055] If there is any ground signal in the FWC status information, the status diagnosis signal of the FWC is set to "FWC has a fault";

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

[0057] The fault diagnosis of the GPWS status diagnosis unit is as follows: when the current status of the weather radar is that there is no fault, or it has been updated to complete replacement, the GPWC self-check is performed and it is determined that:

[0058] When there is no GPWS error alarm after the GPWC self-check, the status diagnosis signal of the GPWC is set to "GPWC does not have a fault";

[0059] When a GPWS error alarm is present after the GPWC self-check, the status diagnosis signal of the GPWC is set to "GPWC failure present".

[0060] Further, the auditory channel state diagnosis unit includes an auditory channel state acquisition module and a weather radar fault diagnosis module of the auditory channel;

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

[0062] The weather radar fault diagnosis module of the auditory channel is used to judge the state information of the auditory channel:

[0063] When there is an audio suppression signal in the auditory channel status information, the status diagnosis signal of the weather radar is set to "there is a fault in the weather radar";

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

[0065] An aircraft having an automatic GPWS alarm self-check, including a FWS, a weather radar, a GPWS and a fault component diagnosis device;

[0066] The FWS includes an FWC, which is used to monitor the operating status of several systems of the aircraft in real time. When there is a system abnormality, 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 of the aircraft's surroundings. When an abnormal condition is detected, a corresponding fault grounding signal is generated and sent to the GPWS;

[0068] The GPWS includes a GPWC for analyzing the fault grounding signals of the FWC and the weather radar, and detecting 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 diagnosis device;

[0069] The fault component diagnosis device is used to receive the GPWS error alarm, diagnose the weather radar, FWC and GPWC according to the GPWS error alarm, and output a corresponding status diagnosis signal according to the diagnosis result; the status diagnosis signal is used to indicate whether the corresponding component needs to be replaced;

[0070] Wherein, the fault locating device is the above-mentioned fault component diagnosis device based on GPWS alarm.

[0071] For better understanding and implementation, the present invention is described in detail below with reference to the accompanying drawings. BRIEF DESCRIPTION OF THE DRAWINGS

[0072] Figure 1 A simplified flowchart for Airbus to troubleshoot faulty components of GPWS alarms;

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

[0075] Figure 4 Schematic diagram of delayed triggering case of GPWC false alarm. DETAILED DESCRIPTION

[0076] In order to solve the problems of low efficiency and inaccurate diagnosis when troubleshooting the alarm of the Ground Proximity Warning System (GPWS) in the prior art, after receiving the false alarm of EGPWS or GPWS, the present invention resets according to the circuit breaker status of the Ground Proximity Warning Computer (GPWC) and the weather radar, and determines whether the GPWS returns to normal after the reset; if not, the GPWS is visually detected, and whether the weather radar is faulty according to the detection result; at the same time, the Flight Warning Computer (FWC) of the current aircraft is detected, and whether the FWC is faulty according to the detection result; then, the GPWC is auditory detected, and whether the weather radar is faulty is further determined according to the detection result; finally, the GPWS self-check is performed on the current aircraft, and whether the GPWC is faulty according to the self-check result. Accordingly, the present invention further detects the auditory channel of GPWC and the status of GPWS itself after simultaneously detecting the visual channel of GPWC and FWC, so that when an EGPWS / GPWS false alarm occurs, it can more quickly and accurately identify and diagnose whether the weather radar, FWC or GPWC is faulty, effectively reducing unnecessary component replacement caused by inaccurate diagnosis, thereby avoiding repeated slips, and significantly improving the efficiency and accuracy of fault diagnosis.

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

[0078] Please also see Figure 2 and Figure 3 , Figure 2 FIG. 1 is a schematic diagram of the overall structure of the fault component diagnosis device based on GPWS alarm according to the present invention. Figure 3 It is a schematic diagram of the overall flow of the fault component diagnosis method based on GPWS alarm described in the present invention.

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

[0080] The circuit breaker status diagnosis unit 1 is used to execute step S1: detect and reset the circuit breakers of the GPWC and the weather radar according to the GPWS error alarm; and determine whether the GPWS returns to normal after the reset: if so, it is considered that the aircraft has no fault; if not, steps S2A and S2B are executed simultaneously.

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

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

[0083] Specifically, when a GPWS error alarm occurs, it is checked whether the circuit breakers of the current GPWC and the weather radar are tripped to obtain the current circuit breaker states of the GPWC and the weather radar.

[0084] Among them, the GPWS error alarm is generally displayed by ECAM, including NAV GPWS FAULT and NAV GPWS TERRDET FAULT alarms, which are usually used to indicate that an abnormality or failure has occurred in EGPWS or GPWS; and common failures of EGPWS or GPWS are usually related to weather radar, FWC and GPWC, and failures caused by FWC are generally accompanied by multiple other error prompts.

[0085] Based on this, 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 state judgment module 12 is used to execute step S12: reset according to the circuit breaker states of the GPWC and the weather radar, and judge whether the GPWS has returned to normal: if so, it is considered that the aircraft has no fault, and the current aircraft continues to taxi and prepare for takeoff; if not, it is considered that there is a fault source in the current aircraft and maintenance is required, and steps S2A and S2B are executed at the same time;

[0087] Specifically, when a circuit breaker trips in the circuit breaker status of the GPWC and the weather radar, the corresponding circuit breaker is reset; if the circuit breaker of the GPWC cannot be reset, the circuit breaker of the weather radar is reset first.

[0088] After the reset operation is completed, further check whether there is still a GPWS error alarm:

[0089] If there is no GPWS false alarm, the GPWS is considered to be fault-free, allowing the aircraft to continue taxiing according to the flight plan and prepare for takeoff;

[0090] If there is a GPWS false alarm, it is considered that there is a GPWS failure, and the aircraft is rolled back to prepare for maintenance and execute the next step;

[0091] Since the tripping of a circuit breaker is usually caused by a short-term overload, short circuit or instantaneous fault, the reset operation can eliminate these temporary or electrical problems. If the system returns to normal after the reset, it can be considered that the problem is caused by a temporary interruption in the electrical system or excessive load, which can be solved by resetting the circuit breaker. If the alarm still exists after the reset, it is believed that the problem causing the system error may be more complicated, so the aircraft needs to be rolled back for further diagnosis and troubleshooting of the faulty components.

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

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

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

[0095] Specifically, the built-in test equipment (BITE) of GPWC is used to detect and obtain a ground signal, which includes WXR1 (1SQ1) BUS HAZARD, GPWC (1WZ) and NO RADAR1 DATA, and the ground signal is used as the visual channel status information.

[0096] The visual channel is a line connecting the electronic central aviation monitoring system (ECAM) and related components, which is used to transmit information to a display such as ECAM for alarm visualization, while the weather radar realizes the grounding of visual alarm information through the HAZARD BUS. The HAZARD BUS is mainly used to transmit the grounding fault information of the weather radar to the ECAM for visual alarms.

[0097] It should be noted that when multiple alarms appear at the same time, the system will distinguish them according to the priority of the alarms. In the auditory channel, the priority is expressed as: FWC stall alarm> wind shear alarm of weather radar (PWS)> ground proximity alarm (EGPWC / GPWC). When a high-priority alarm is triggered, the system will send an inhibition signal to suppress the low-priority alarm signal. In the alarm priority of the visual channel, the priority is only expressed as: wind shear alarm of weather radar> ground proximity alarm (EGPWC / GPWC). This is because the navigation display (Navigation Display, ND) is usually not used to display stall-related alarm information. Its stall alarm is generally reminded by the pilot's control response (such as Stick Shaker, Stick Pusher) and auditory signals, and does not need to be displayed on the ND. Accordingly, the present invention prioritizes trying to eliminate weather radar-related faults based on the alarm priority of the visual channel.

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

[0099] Specifically, the fault diagnosis is that when there is any ground signal in the visual channel status information, it is marked that the weather radar needs to be replaced, and the status diagnosis signal of the weather radar is set to "the weather radar is faulty".

[0100] When there is no ground 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 "there is no fault in the weather radar".

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

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

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

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

[0105] Specifically, a ground signal of a FWC stall, a ground signal of a FWC self-check abnormality, and a ground signal of a FWC-related subsystem failure are acquired, and the ground signals are used as PWC status information.

[0106] Since the core function of FWC is to centrally manage the aircraft's warning system, the stall signal and FWC self-check signal can quickly confirm whether the system has failed. Among them, the stall alarm is usually not triggered during the taxiing of the aircraft on the ground, because the stall is usually related to the flight speed and aerodynamics. If the FWC stall alarm appears, it can be directly inferred that there is an abnormality or failure in the FWC.

[0107] The FWC fault diagnosis module 2B2 is used to execute step S2B2: perform fault diagnosis according to the FWC status information and send a FWC status diagnosis signal.

[0108] Specifically, if there is any ground signal in the FWC status information, the FWC is marked as needing to be replaced, and the status diagnosis signal of the FWC is set to "FWC is faulty";

[0109] If there is no ground signal in the FWC status information, the FWC is marked as normal, and the status diagnosis signal of the FWC is set to "there is no fault in the FWC".

[0110] When the status diagnosis signal of the FWC indicates that there is a fault in the FWC, the subsequent diagnosis process is suspended, and the maintenance personnel are instructed to replace the components of the FWC first. After the replacement, the status of the FWC is updated to eliminate the potential interference of the component failure on the 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 indicates that a fault exists: if so, execute step S5; if not, execute step S4.

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

[0113] When the status diagnosis signal of the weather radar is "there is no fault in the weather radar", it is necessary to further detect the status of the weather radar and execute step S41.

[0114] By judging the current status diagnostic signal of the weather radar, repeated detection of eliminated components can be avoided, thereby improving the efficiency of troubleshooting.

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

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

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

[0118] Specifically, when the current status of the FWC is that there is no fault, or it 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] Among them, the auditory channel is a line connecting the voice playback system and related components, which is used to transmit relevant alarm information to the loudspeaker for playback, so as to play the alarm information by voice to remind the crew; and 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 found that in the standard process of TSM, the auditory channel is not involved in the fault diagnosis of the weather radar. However, the present invention finds that by obtaining the audio suppression signal (AUDIO INHIB) in the auditory channel, it is possible to effectively diagnose whether the weather radar has a fault, especially when the intermittent fault of the WXR1 (1SQ1) BUS HAZARD signal of the visual channel is sometimes grounded and sometimes not grounded, which may make it difficult to capture the fault through the visual channel. Therefore, if the audio suppression signal is captured in the auditory channel, it can be determined that the weather radar has an abnormality.

[0121] This is because the FWC has confirmed through the previous diagnosis (step S2B) that there is no fault, or has been replaced, but the auditory channel still receives the audio suppression signal, which indicates that there is a high-priority alarm in the auditory channel, that is, the weather radar is faulty. Accordingly, the present invention uses the suppression signal in the auditory channel (such as the parameter 0.23.1.357.00, which is decoded as AUDIO INHIB) to diagnose the status of the weather radar, effectively compensating for the possible diagnosis omission caused by relying solely on the visual channel, and effectively avoiding multiple slip-backs.

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

[0123] It should be noted that since the aircraft needs to operate in harsh environments, a delay may be set in the signal processing process to avoid abnormal signals caused by transient errors. Therefore, the GPWC error alarm may appear after a delay of some time after the audio suppression signal appears, such as Figure 4 Schematic diagram of delayed triggering case of GPWC false alarm shown.

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

[0125] Specifically, when there is an audio suppression signal in the auditory channel status information, it is marked that the weather radar needs to be replaced, and the status diagnosis signal of the weather radar is set to "the weather radar is faulty".

[0126] When 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 "there is no fault in the weather radar".

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

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

[0129] Specifically, when the current status of the weather radar is that there is no fault, or it has been updated to complete replacement, the GPWC self-check is performed and the fault diagnosis is performed:

[0130] When there is no GPWS error alarm after the GPWC self-check, it is marked that the GPWC does not need to be replaced, and the status diagnosis signal of the GPWC is set to "GPWC does not have a fault".

[0131] When there is a GPWS error alarm after the GPWC self-check, it is marked that the GPWC needs to be replaced, and the status diagnosis signal of the GPWC is set to "GPWC is faulty".

[0132] When the status diagnosis signal of the GPWC indicates that there is a fault in the GPWC, the maintenance personnel are instructed to replace components of the GPWC, and the status of the GPWC is updated after the replacement.

[0133] Since the above steps have ruled out faults and anomalies related to weather radar and FWC, if there is still a GPWS error alarm, it can be reasonably inferred that there is an abnormality or fault in the GPWC itself. Based on this, through this multi-level troubleshooting process, the present invention can accurately locate the source of the fault, thereby ensuring that the GPWC can be detected and replaced in time when a problem occurs, thereby avoiding multiple slips and improving maintenance efficiency.

[0134] Compared with the prior art, the present invention can more quickly and accurately lock the relevant faulty components that cause GPWS false alarms by sequentially checking the fault grounding signals of the visual channel, flight warning computer (FWC), auditory channel and ground proximity warning computer (GPWC), avoiding lengthy troubleshooting processes, thereby effectively reducing the risk of multiple slips and significantly improving maintenance efficiency. In addition, the present invention also ensures that the aircraft can complete maintenance and resume normal operation in the shortest time, avoiding misunderstandings or unnecessary panic caused by delays in troubleshooting.

[0135] Based on the same inventive concept, the present application also provides an electronic device, which may be a terminal device such as a server, a desktop computing device or a mobile computing device (e.g., a laptop computing device, a handheld computing device, a tablet computer, a 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 alarm of an embodiment of the present invention; and the memory is used to store a computer program executable by the processor.

[0136] Based on the same inventive concept, the present application also provides a computer-readable storage medium, corresponding to the embodiment of the aforementioned faulty component diagnosis method based on GPWS alarm, wherein the computer-readable storage medium stores a computer program thereon, and when the program is executed by the processor, the steps of the faulty component diagnosis method based on GPWS alarm recorded in any of the above embodiments are implemented.

[0137] The present 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-usable storage media include permanent and non-permanent, removable and non-removable media, and information storage can be achieved by any method or technology. Information can be computer-readable instructions, data structures, modules of programs, 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 technology, read-only compact disk read-only memory (CD-ROM), digital versatile disk (DVD) or other optical storage, magnetic cassettes, tape disk storage or other magnetic storage devices or any other non-transmission medium that can be used to store information that can be accessed by a computing device.

[0138] The above-mentioned embodiments only express several implementation methods of the present invention, and the description is relatively specific and detailed, but it cannot be understood as limiting the scope of the invention patent. It should be pointed out that for ordinary technicians in this field, several modifications and improvements can be made without departing from the concept of the present invention, and the present invention is also intended to include these modifications and modifications.

Claims

1. A method for diagnosing a faulty component based on a GPWS alarm, characterized in that: S1. According to the GPWS error alarm, the circuit breakers of the GPWC and the weather radar are detected and reset; and it is determined whether the GPWS after the reset is restored to normal: if so, it is considered that the aircraft has no fault; if not, steps S2A and S2B are executed simultaneously; S2A, perform visual channel detection and fault diagnosis on the GPWC of the current aircraft, and send a weather radar status diagnosis signal according to the fault diagnosis result; S2B, perform FWC detection and fault diagnosis on the current aircraft, and send a FWC status diagnosis signal according to the fault diagnosis result; S3, determine whether the current status diagnosis signal of the weather radar indicates a fault: if so, execute step S5; if not, execute step S4; S4. Performing auditory channel detection and fault diagnosis on the GPWC of the current aircraft according to the current state of the FWC, and sending a weather radar state diagnosis signal according to the fault diagnosis result; S5. According to the current state of the weather radar, perform GPWC self-check and fault diagnosis on the GPWS of the current aircraft, and send a GPWC state diagnosis signal according to the fault diagnosis result to complete the diagnosis of all components; Among them, the status diagnosis signals of the weather radar, FWC and GPWC respectively represent the diagnosis results of the weather radar, FWC and GPWC. When the diagnosis results indicate that there is a fault in the corresponding component, the diagnosis process is suspended, and the corresponding component is replaced first. After replacement, the status of the corresponding component is updated and the diagnosis process continues.

2. The fault component diagnosis method based on GPWS alarm according to claim 1, characterized in that: The step S2A comprises the following sub-steps: S2A1, detect and obtain the ground signal through the built-in test equipment of GPWC, and use the ground signal as the visual channel status information; S2A2, judging the visual channel status information: when there is any ground signal in the visual channel status information, setting the status diagnosis signal of the weather radar to "the weather radar is faulty"; When there is no ground signal in the visual channel status information, the status diagnosis signal of the weather radar is set to "there is no fault in the weather radar"; The step S2B comprises the following sub-steps: S2B1, obtaining the ground signal of FWC stall, the ground signal of FWC self-test abnormality and the ground signal of FWC associated subsystem failure, and using the ground signal as PWC status information; S2B2, judging the PWC status information: if there is any ground signal in the FWC status information, setting the FWC status diagnosis signal to "FWC fault"; If there is no ground signal in the FWC status information, the status diagnosis signal of the FWC is set to "FWC does not have a fault".

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

4. The fault component diagnosis method based on GPWS alarm according to claim 3 is characterized in that: The step S5 comprises the following sub-steps: When the current status of the weather radar is that there is no fault, or it has been updated to complete replacement, the GPWC self-check is performed and the fault diagnosis is performed: When the current state of the FWC is that there is no fault, or the replacement has been completed, and when there is no GPWS error alarm after the GPWC self-check, the state diagnosis signal of the GPWC is set to "GPWC does not have a fault". When a GPWS error alarm is present after the GPWC self-check, the status diagnosis signal of the GPWC is set to "GPWC fault present".

5. A fault component diagnosis device based on GPWS alarm, characterized in that: It includes a circuit breaker status diagnosis unit, a visual channel status diagnosis unit, a FWC status diagnosis unit, a weather radar status judgment unit, an auditory channel status diagnosis unit and a GPWS status diagnosis unit; The circuit breaker status diagnosis unit is used to detect and reset the circuit breakers of the GPWC and the weather radar according to the GPWS error alarm; and determine whether the GPWS after the reset is restored to normal: if so, it is considered that the aircraft has no fault; if not, the visual channel status diagnosis unit and the FWC status diagnosis 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 GPWC of the current aircraft, and send a weather radar status diagnosis signal according to the fault diagnosis result; The FWC status diagnosis unit is used to perform FWC detection and fault diagnosis on the current aircraft, and send a FWC status diagnosis signal according to the fault diagnosis result; The weather radar status judgment unit is used to judge whether the current weather radar status diagnosis signal indicates a fault: if so, the GPWS status diagnosis unit is called; if not, the auditory channel status diagnosis unit is called; The auditory channel state diagnosis unit is used to perform auditory channel detection and fault diagnosis on the GPWC of the current aircraft according to the current state of the FWC, and send a weather radar state diagnosis signal according to the fault diagnosis result; The GPWS status diagnosis unit is used to perform GPWC self-check and fault diagnosis on the GPWS of the current aircraft according to the current status of the weather radar, and send a GPWC status diagnosis signal according to the fault diagnosis result to complete the diagnosis of all components; Among them, the status diagnosis signals of the weather radar, FWC and GPWC respectively represent the diagnosis results of the weather radar, FWC and GPWC. When the diagnosis results indicate that there is a fault in the corresponding component, the diagnosis process is suspended, and the corresponding component is replaced first. After replacement, the status of the corresponding component is updated and the diagnosis process continues.

6. The fault component diagnosis device based on GPWS alarm according to claim 5, characterized in that: The visual channel state diagnosis unit includes a visual channel state acquisition module and a weather radar fault diagnosis module of the visual channel; The visual channel state acquisition module is used to detect and acquire a ground signal through a built-in test device of the GPWC, and use the ground signal as visual channel state information; The weather radar fault diagnosis module of the visual channel is used to judge the state information of the visual channel: When there is any ground signal in the visual channel status information, the status diagnosis signal of the weather radar is set to "the weather radar is faulty"; When there is no ground signal in the visual channel status information, the status diagnosis signal of the weather radar is set to "there is no fault in the weather radar"; The FWC status diagnosis unit includes a FWC status acquisition module and a FWC fault diagnosis module; The FWC status acquisition module is used to acquire a ground signal of FWC stall, a ground signal of FWC self-test abnormality, and a ground signal of FWC-associated subsystem failure, and use the ground signal as PWC status information; The FWC fault diagnosis module is used to determine the PWC status information: If there is any ground signal in the FWC status information, the status diagnosis signal of the FWC is set to "FWC has a fault"; If there is no ground signal in the FWC status information, the FWC status diagnosis signal is set to "FWC does not have a fault"; The fault diagnosis of the GPWS status diagnosis unit is as follows: when the current status of the weather radar is that there is no fault, or it has been updated to complete replacement, the GPWC self-check is performed and it is determined that: When there is no GPWS error alarm after the GPWC self-check, the status diagnosis signal of the GPWC is set to "GPWC does not have a fault"; When a GPWS error alarm is present after the GPWC self-check, the status diagnosis signal of the GPWC is set to "GPWC fault present".

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

8. An aircraft with automatic GPWS alarm self-check, characterized in that: Includes FWS, weather radar, GPWS and fault component diagnostics; The FWS includes an FWC, which is used to monitor the operating status of several systems of the aircraft in real time. When there is a system abnormality, 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 of the aircraft's surroundings. When an abnormal condition is detected, a corresponding fault grounding signal is generated and sent to the GPWS; The GPWS includes a GPWC for analyzing the fault grounding signals of the FWC and the weather radar, and detecting 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 diagnosis device; The fault component diagnosis device is used to receive the GPWS error alarm, diagnose the weather radar, FWC and GPWC according to the GPWS error alarm, and output a corresponding status diagnosis signal according to the diagnosis result; the status diagnosis signal is used to indicate whether the corresponding component needs to be replaced; Wherein, the fault locating device is a fault component diagnosis device based on GPWS alarm as described in any one of claims 5 to 7 above.

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

10. A computer-readable storage medium storing computer-executable instructions, characterized in that: When the computer executable instructions are executed by a processor, the fault component diagnosis method based on GPWS alarm according to any one of claims 1 to 4 is implemented.

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