A method and system for enhanced diagnosis of faults in an aircraft ground phm system

Abstract

An aircraft ground PHM system fault enhanced diagnosis method and system, wherein in the aircraft ground PHM system fault enhanced diagnosis method, a false alarm suppression step is designed to filter false alarms, and a fuzzy group reduction isolation step is designed to reduce and isolate the fuzzy group, and a case fault diagnosis step is designed after the false alarm suppression step and the fuzzy group reduction isolation step, which can statistically calculate the field maintainable unit probability associated with the fault, sort, thereby effectively guiding the maintenance personnel to carry out maintenance work on the aircraft, and a ground fault diagnosis step is designed, which can comprehensively diagnose the fault, analyze the fault cause, and avoid missing faults.

Description

Technical Field

[0001] The present application belongs to the technical field of aircraft fault diagnosis, and specifically relates to an aircraft ground PHM system fault enhanced diagnosis method and system. Background Art

[0002] Currently, the aircraft ground PHM system collects fault data and uses fault diagnosis models to perform fault diagnosis to determine whether the aircraft has a fault, locate the fault to an off-site repairable and replaceable unit, and guide the crew maintenance personnel to carry out maintenance work on the aircraft.

[0003] In practice, there are situations where the aircraft's ground PHM system is unable to locate the fault to a specific field-repairable and replaceable unit, resulting in a large number of false alarms and fuzzy groups, making it difficult to effectively guide crew maintenance personnel to carry out maintenance work on the aircraft.

[0004] This application is proposed in view of the above-mentioned technical defects. Summary of the Invention

[0005] The purpose of this application is to provide an aircraft ground PHM system fault enhanced diagnosis method and system thereof to overcome or alleviate at least one aspect of the known technical deficiencies.

[0006] The technical solution of this application is:

[0007] On the one hand, a method for enhanced fault diagnosis of an aircraft ground PHM system is provided, comprising:

[0008] False alarm suppression step: Load the false alarm suppression model, and make a false alarm judgment on the fault data based on the false alarm suppression model. If it is a false alarm, a false alarm report is output;

[0009] Fuzzy group reduction and isolation step: Load the fuzzy group reduction and isolation model, perform fuzzy group reduction and isolation analysis on the fault data based on the fuzzy group reduction and isolation model, and output a fuzzy group isolation report if the fault can be isolated to a single field repairable replaceable unit;

[0010] Case fault diagnosis steps: Load the fault case, perform case fault diagnosis on the fault data based on the fault case, statistically calculate the probability of field repairable replaceable units associated with the fault, sort them, and output the case fault diagnosis report;

[0011] Ground fault diagnosis steps: load the ground fault diagnosis model, perform ground fault diagnosis on the aircraft status monitoring data based on the ground fault diagnosis model, analyze the cause of the fault, and output a ground fault diagnosis report.

[0012] Optionally, in the above-mentioned aircraft ground PHM system fault enhanced diagnosis method, the false alarm suppression model is configured with false alarm suppression identification features, false alarm suppression criteria, and false alarm suppression judgment time. In the false alarm suppression step, false alarm judgment is performed on the fault data based on the false alarm suppression model, specifically:

[0013] Read fault data one by one;

[0014] Determine whether there are false alarm suppression identification features in the fault data;

[0015] If there is no false alarm suppression identification feature in the fault data, it is judged not to be a false alarm;

[0016] If there is a false alarm suppression identification feature in the fault data, it is determined whether the fault data meets the false alarm suppression criterion and the duration exceeds the false alarm suppression judgment time. If so, it is determined to be a false alarm; if not, it is determined not to be a false alarm.

[0017] Optionally, in the above-mentioned enhanced fault diagnosis method for the aircraft ground PHM system, the fuzzy group reduction isolation model is configured with fuzzy group reduction isolation identification features, fuzzy group reduction isolation criteria, and fuzzy group reduction isolation judgment time. In the fuzzy group reduction isolation step, fuzzy group reduction isolation analysis is performed on the fault data based on the fuzzy group reduction isolation model, specifically:

[0018] Read fault data one by one;

[0019] Determine whether there are fuzzy group reduction isolation identification features in the fault data;

[0020] If there is no fuzzy group reduction isolation identification feature in the fault data, the fuzzy group reduction isolation analysis is not performed;

[0021] If there is a fuzzy group reduction isolation identification feature in the fault data, it is determined whether the fault data meets the fuzzy group reduction isolation criterion and the duration exceeds the fuzzy group reduction isolation judgment time. If so, a fuzzy group reduction isolation analysis is performed to obtain the field repairable and replaceable unit associated with the fault. If not, the fuzzy group reduction isolation analysis is not performed.

[0022] Optionally, in the above-mentioned enhanced fault diagnosis method for the aircraft ground PHM system, the fault case is configured with a fault identification code, a fault feature vector, and a fault occurrence threshold. In the case fault diagnosis step, ground fault diagnosis is performed on the aircraft status monitoring data based on the ground fault diagnosis model, specifically:

[0023] Read fault data one by one;

[0024] Determine whether there is a fault identification code in the fault data;

[0025] If the fault identification code does not exist in the fault data, it is determined that no case fault has occurred;

[0026] If there is a fault identification code in the fault data, the feature vector of the fault data is extracted and the similarity with the fault feature vector is calculated. If the similarity exceeds the fault occurrence threshold, it is determined that a case fault has occurred. The probability of field repairable and replaceable units associated with the fault is then statistically calculated and sorted. If the similarity is less than the fault occurrence threshold, it is determined that no case fault has occurred.

[0027] Optionally, in the above-mentioned enhanced fault diagnosis method for the aircraft ground PHM system, the ground fault diagnosis model is configured with ground fault judgment criteria and ground fault judgment time. In the ground fault diagnosis step, ground fault diagnosis is performed on the aircraft status monitoring data based on the ground fault diagnosis model, specifically:

[0028] Read aircraft status monitoring data one by one;

[0029] Determine whether the aircraft status monitoring data meets the ground fault judgment criteria and the duration exceeds the ground fault judgment time. If so, it is determined that a ground fault has occurred. If not, it is determined that no ground fault has occurred.

[0030] On the other hand, an aircraft ground PHM system fault enhanced diagnosis system is provided, comprising:

[0031] False alarm suppression module: loads the false alarm suppression model, and based on the false alarm suppression model, performs false alarm judgment on the fault data. If it is a false alarm, a false alarm report is output;

[0032] Fuzzy group reduction isolation module: loads the fuzzy group reduction isolation model and performs fuzzy group reduction isolation analysis on the fault data based on the fuzzy group reduction isolation model. If the fault can be isolated to a single field-repairable replaceable unit, a fuzzy group isolation report is output.

[0033] Case fault diagnosis module: loads fault cases, performs case fault diagnosis on fault data based on the fault cases, statistically calculates the probability of field repairable replaceable units associated with the faults, sorts them, and outputs a case fault diagnosis report;

[0034] Ground fault diagnosis module: loads the ground fault diagnosis model, performs ground fault diagnosis on the aircraft status monitoring data based on the ground fault diagnosis model, analyzes the cause of the fault, and outputs a ground fault diagnosis report.

[0035] Optionally, in the above-mentioned aircraft ground PHM system fault enhancement diagnosis system, the false alarm suppression model is configured with false alarm suppression identification features, false alarm suppression criteria, and false alarm suppression judgment time. The false alarm suppression module performs false alarm judgment on the fault data based on the false alarm suppression model, specifically:

[0036] Read fault data one by one;

[0037] Determine whether there are false alarm suppression identification features in the fault data;

[0038] If there is no false alarm suppression identification feature in the fault data, it is judged not to be a false alarm;

[0039] If there is a false alarm suppression identification feature in the fault data, it is determined whether the fault data meets the false alarm suppression criterion and the duration exceeds the false alarm suppression judgment time. If so, it is determined to be a false alarm; if not, it is determined not to be a false alarm.

[0040] Optionally, in the above-mentioned aircraft ground PHM system fault enhanced diagnosis system, the fuzzy group reduction isolation model is configured with fuzzy group reduction isolation identification features, fuzzy group reduction isolation criteria, and fuzzy group reduction isolation judgment time. In the fuzzy group reduction isolation module, fuzzy group reduction isolation analysis is performed on the fault data based on the fuzzy group reduction isolation model, specifically:

[0041] Read fault data one by one;

[0042] Determine whether there are fuzzy group reduction isolation identification features in the fault data;

[0043] If there is no fuzzy group reduction isolation identification feature in the fault data, the fuzzy group reduction isolation analysis is not performed;

[0044] If there is a fuzzy group reduction isolation identification feature in the fault data, it is determined whether the fault data meets the fuzzy group reduction isolation criterion and the duration exceeds the fuzzy group reduction isolation judgment time. If so, a fuzzy group reduction isolation analysis is performed to obtain the field repairable and replaceable unit associated with the fault. If not, the fuzzy group reduction isolation analysis is not performed.

[0045] Optionally, in the above-mentioned aircraft ground PHM system fault enhanced diagnosis system, the fault case is configured with a fault identification code, a fault feature vector, and a fault occurrence threshold. In the case fault diagnosis module, ground fault diagnosis is performed on the aircraft status monitoring data based on the ground fault diagnosis model, specifically:

[0046] Read fault data one by one;

[0047] Determine whether there is a fault identification code in the fault data;

[0048] If the fault identification code does not exist in the fault data, it is determined that no case fault has occurred;

[0049] If there is a fault identification code in the fault data, the feature vector of the fault data is extracted and the similarity with the fault feature vector is calculated. If the similarity exceeds the fault occurrence threshold, it is determined that a case fault has occurred. The probability of field repairable and replaceable units associated with the fault is then statistically calculated and sorted. If the similarity is less than the fault occurrence threshold, it is determined that no case fault has occurred.

[0050] Optionally, in the above-mentioned aircraft ground PHM system fault enhanced diagnosis system, the ground fault diagnosis model is configured with ground fault judgment criteria and ground fault judgment time. The ground fault diagnosis module performs ground fault diagnosis on the aircraft status monitoring data based on the ground fault diagnosis model, specifically:

[0051] Read aircraft status monitoring data one by one;

[0052] Determine whether the aircraft status monitoring data meets the ground fault judgment criteria and the duration exceeds the ground fault judgment time. If so, it is determined that a ground fault has occurred. If not, it is determined that no ground fault has occurred.

[0053] This application has at least the following beneficial technical effects:

[0054] Provided are an aircraft ground PHM system fault enhancement diagnosis method and system. The method comprises a false alarm suppression step for filtering false alarms, and a fuzzy group reduction and isolation step for reducing and isolating fuzzy groups. Following the false alarm suppression and fuzzy group reduction and isolation steps, a case fault diagnosis step is provided to statistically calculate and rank the probabilities of field repairable and replaceable units associated with the fault, thereby effectively guiding crew maintenance personnel in carrying out aircraft maintenance work. Furthermore, a ground fault diagnosis step is provided to comprehensively diagnose faults, analyze their causes, and avoid missing faults. BRIEF DESCRIPTION OF THE DRAWINGS

[0055] Figure 1 is a schematic diagram of an enhanced fault diagnosis method for an aircraft ground PHM system provided in an embodiment of the present application;

[0056] Figure 2 2 is a schematic diagram of a false alarm suppression step provided in an embodiment of the present application;

[0057] Figure 3 1 is a schematic diagram of the fuzzy group reduction and isolation steps provided in an embodiment of the present application;

[0058] Figure 4 This is a schematic diagram of the steps for diagnosing a fault in a case provided by an embodiment of the present application;

[0059] Figure 5 This is a schematic diagram of the ground fault diagnosis steps provided in the embodiment of the present application.

[0060] In order to better illustrate this embodiment, some contents of the drawings may be omitted or reduced, which is only used for illustrative purposes and should not be construed as limiting this application. DETAILED DESCRIPTION

[0061] To make the technical solution and its advantages of this application more clear, the technical solution of this application will be further described in detail below with reference to the accompanying drawings. It should be understood that the specific embodiments described here are only some of the embodiments of this application and are only used to explain this application, not to limit this application. It should be noted that for ease of description, only the parts relevant to this application are shown in the accompanying drawings, and other relevant parts can refer to the general design.

[0062] In addition, unless otherwise defined, the technical terms or scientific terms used in the description of this application should have the common meanings understood by those skilled in the art in the art to which this application belongs.

[0063] On the one hand, a method for enhancing fault diagnosis of aircraft ground PHM system is provided, such as Figure 1 Shown, including:

[0064] False alarm suppression step: Load the false alarm suppression model, and make a false alarm judgment on the fault data based on the false alarm suppression model. If it is a false alarm, a false alarm report is output;

[0065] Fuzzy group reduction and isolation step: If it is not a false alarm, load the fuzzy group reduction and isolation model, and perform fuzzy group reduction and isolation analysis on the fault data based on the fuzzy group reduction and isolation model. If the fault can be isolated to a single field repairable and replaceable unit, that is, the fuzzy group can be effectively reduced, then output a fuzzy group isolation report;

[0066] Case fault diagnosis steps: When the fault cannot be isolated to a single field-based RRU, that is, when the fuzzy group cannot be effectively reduced, the fault case is loaded, and case fault diagnosis is performed on the fault data based on the fault case. The probability of the field-based RRU associated with the fault is statistically calculated, sorted, and a case fault diagnosis report is output;

[0067] Ground fault diagnosis steps: load the ground fault diagnosis model, perform ground fault diagnosis on the aircraft status monitoring data based on the ground fault diagnosis model, analyze the cause of the fault, and output a ground fault diagnosis report.

[0068] The aircraft ground PHM system fault enhanced diagnosis method disclosed in the above embodiment is designed with a false alarm suppression step for filtering false alarms, and a fuzzy group reduction and isolation step for reducing and isolating fuzzy groups. Furthermore, after the false alarm suppression step and the fuzzy group reduction and isolation step, a case fault diagnosis step is designed to statistically calculate the probabilities of field repairable and replaceable units associated with the fault and sort them, thereby effectively guiding crew maintenance personnel in performing aircraft maintenance work. Furthermore, a ground fault diagnosis step is designed to comprehensively diagnose faults, analyze the causes of the faults, and avoid missing faults.

[0069] In the aircraft ground PHM system fault enhanced diagnosis method disclosed in the above embodiment, when outputting the corresponding report, maintenance suggestions and troubleshooting procedures can be output at the same time, thereby more efficiently guiding the crew maintenance personnel to perform maintenance work on the aircraft.

[0070] In some optional embodiments, there may be multiple false alarm suppression models, which are configured with false alarm suppression identification features, false alarm suppression criteria and false alarm suppression judgment time. In the false alarm suppression step, false alarm judgment is performed on the fault data based on the false alarm suppression model, specifically as follows: Figure 2 Shown, including:

[0071] Read fault data one by one;

[0072] Determine whether there are false alarm suppression identification features in the fault data;

[0073] If there is no false alarm suppression identification feature in the fault data, it is judged not to be a false alarm;

[0074] If there is a false alarm suppression identification feature in the fault data, it is determined whether the fault data meets the false alarm suppression criterion and the duration exceeds the false alarm suppression judgment time. If so, it is determined to be a false alarm; if not, it is determined not to be a false alarm.

[0075] In some optional embodiments, there may be multiple fuzzy group reduction isolation models, which are configured with fuzzy group reduction isolation identification features, fuzzy group reduction isolation criteria and fuzzy group reduction isolation judgment time. In the fuzzy group reduction isolation step, fuzzy group reduction isolation analysis is performed on the fault data based on the fuzzy group reduction isolation model, specifically as follows: Figure 3 Shown, including:

[0076] Read fault data one by one;

[0077] Determine whether there are fuzzy group reduction isolation identification features in the fault data;

[0078] If there is no fuzzy group reduction isolation identification feature in the fault data, the fuzzy group reduction isolation analysis is not performed;

[0079] If there is a fuzzy group reduction isolation identification feature in the fault data, it is determined whether the fault data meets the fuzzy group reduction isolation criterion and the duration exceeds the fuzzy group reduction isolation judgment time. If so, a fuzzy group reduction isolation analysis is performed to obtain the field repairable and replaceable unit associated with the fault. If not, the fuzzy group reduction isolation analysis is not performed.

[0080] In some optional embodiments, there may be multiple fault cases, which are configured with fault identification codes, fault feature vectors, and fault occurrence thresholds. In the case fault diagnosis step, ground fault diagnosis is performed on the aircraft status monitoring data based on the ground fault diagnosis model, specifically as follows: Figure 4 Shown, including:

[0081] Read fault data one by one;

[0082] Determine whether there is a fault identification code in the fault data;

[0083] If the fault identification code does not exist in the fault data, it is determined that no case fault has occurred;

[0084] If there is a fault identification code in the fault data, the feature vector of the fault data is extracted and the similarity with the fault feature vector is calculated. If the similarity exceeds the fault occurrence threshold, it is determined that a case fault has occurred. The probability of field repairable and replaceable units associated with the fault is then statistically calculated and sorted. If the similarity is less than the fault occurrence threshold, it is determined that no case fault has occurred.

[0085] In some optional embodiments, there may be multiple ground fault diagnosis models, which are configured with ground fault judgment criteria and ground fault judgment time. In the ground fault diagnosis step, ground fault diagnosis is performed on the aircraft status monitoring data based on the ground fault diagnosis model, specifically as follows: Figure 5 Shown, including:

[0086] Read aircraft status monitoring data one by one, specifically at a time interval of 1 second;

[0087] Determine whether the aircraft status monitoring data meets the ground fault judgment criteria and the duration exceeds the ground fault judgment time. If so, it is determined that a ground fault has occurred. If not, it is determined that no ground fault has occurred.

[0088] On the other hand, an aircraft ground PHM system fault enhanced diagnosis system is provided, comprising:

[0089] False alarm suppression module: loads the false alarm suppression model, and based on the false alarm suppression model, performs false alarm judgment on the fault data. If it is a false alarm, a false alarm report is output;

[0090] Fuzzy group reduction isolation module: loads the fuzzy group reduction isolation model and performs fuzzy group reduction isolation analysis on the fault data based on the fuzzy group reduction isolation model. If the fault can be isolated to a single field-repairable replaceable unit, a fuzzy group isolation report is output.

[0091] Case fault diagnosis module: loads fault cases, performs case fault diagnosis on fault data based on the fault cases, statistically calculates the probability of field repairable replaceable units associated with the faults, sorts them, and outputs a case fault diagnosis report;

[0092] Ground fault diagnosis module: loads the ground fault diagnosis model, performs ground fault diagnosis on the aircraft status monitoring data based on the ground fault diagnosis model, analyzes the cause of the fault, and outputs a ground fault diagnosis report.

[0093] In some optional embodiments, in the aircraft ground PHM system fault enhancement diagnosis system, the false alarm suppression model is configured with false alarm suppression identification features, false alarm suppression criteria, and false alarm suppression judgment time. The false alarm suppression module performs false alarm judgment on the fault data based on the false alarm suppression model, specifically:

[0094] Read fault data one by one;

[0095] Determine whether there are false alarm suppression identification features in the fault data;

[0096] If there is no false alarm suppression identification feature in the fault data, it is judged not to be a false alarm;

[0097] If there is a false alarm suppression identification feature in the fault data, it is determined whether the fault data meets the false alarm suppression criterion and the duration exceeds the false alarm suppression judgment time. If so, it is determined to be a false alarm; if not, it is determined not to be a false alarm.

[0098] In some optional embodiments, in the aircraft ground PHM system fault enhanced diagnosis system, the fuzzy group reduction isolation model is configured with fuzzy group reduction isolation identification features, fuzzy group reduction isolation criteria, and fuzzy group reduction isolation judgment time. The fuzzy group reduction isolation module performs fuzzy group reduction isolation analysis on the fault data based on the fuzzy group reduction isolation model, specifically:

[0099] Read fault data one by one;

[0100] Determine whether there are fuzzy group reduction isolation identification features in the fault data;

[0101] If there is no fuzzy group reduction isolation identification feature in the fault data, the fuzzy group reduction isolation analysis is not performed;

[0102] If there is a fuzzy group reduction isolation identification feature in the fault data, it is determined whether the fault data meets the fuzzy group reduction isolation criterion and the duration exceeds the fuzzy group reduction isolation judgment time. If so, a fuzzy group reduction isolation analysis is performed to obtain the field repairable and replaceable unit associated with the fault. If not, the fuzzy group reduction isolation analysis is not performed.

[0103] In some optional embodiments, in the aircraft ground PHM system fault enhanced diagnosis system, the fault case is configured with a fault identification code, a fault feature vector, and a fault occurrence threshold. In the case fault diagnosis module, ground fault diagnosis is performed on the aircraft status monitoring data based on a ground fault diagnosis model, specifically:

[0104] Read fault data one by one;

[0105] Determine whether there is a fault identification code in the fault data;

[0106] If the fault identification code does not exist in the fault data, it is determined that no case fault has occurred;

[0107] If there is a fault identification code in the fault data, the feature vector of the fault data is extracted and the similarity with the fault feature vector is calculated. If the similarity exceeds the fault occurrence threshold, it is determined that a case fault has occurred. The probability of field repairable and replaceable units associated with the fault is then statistically calculated and sorted. If the similarity is less than the fault occurrence threshold, it is determined that no case fault has occurred.

[0108] In some optional embodiments, in the aircraft ground PHM system fault enhanced diagnosis system, the ground fault diagnosis model is configured with ground fault judgment criteria and ground fault judgment time. The ground fault diagnosis module performs ground fault diagnosis on the aircraft status monitoring data based on the ground fault diagnosis model, specifically:

[0109] Read aircraft status monitoring data one by one;

[0110] Determine whether the aircraft status monitoring data meets the ground fault judgment criteria and the duration exceeds the ground fault judgment time. If so, it is determined that a ground fault has occurred. If not, it is determined that no ground fault has occurred.

[0111] The aircraft ground PHM system fault enhanced diagnosis system disclosed in the above embodiment corresponds to the aircraft ground PHM system fault enhanced diagnosis method disclosed in the above embodiment. The description is relatively simple. For specific related details, please refer to the relevant description of the aircraft ground PHM system fault enhanced diagnosis method. Its technical effects can also refer to the technical effects of the relevant part of the aircraft ground PHM system fault enhanced diagnosis method, and will not be repeated here.

[0112] In addition, technicians in the field should also be able to realize that the various modules of the device disclosed in the embodiments of the present application can be implemented by electronic hardware, computer software, or a combination of the two. In order to clearly illustrate the interchangeability of hardware and software, this application generally describes them according to their functions. Whether these functions are performed in hardware or software depends on the specific application and design constraints of the technical solution. Technicians in the field can choose to adopt different methods to implement the described functions for each specific application and its actual constraints, but such implementation should not be considered to be beyond the scope of this application.

[0113] The various embodiments in the specification are described in a progressive manner, and each embodiment focuses on the differences from other embodiments. The same or similar parts between the various embodiments can be referenced to each other. In the absence of conflict, the embodiments in this application and the technical features in the embodiments can be combined with each other to obtain new embodiments.

[0114] So far, the technical solution of the present application has been described in conjunction with the preferred embodiments shown in the accompanying drawings. Those skilled in the art should understand that the scope of protection of the present application is obviously not limited to these specific embodiments. Without departing from the principles of the present application, those skilled in the art can make equivalent changes or replacements to the relevant technical features, and the technical solutions after these changes or replacements will fall within the scope of protection of the present application.

Claims

1. An enhanced fault diagnosis method for an aircraft ground PHM system, characterized in that: include: False alarm suppression step: in step 1, a false alarm suppression model is loaded, and a false alarm judgment is performed on the fault data based on the false alarm suppression model. If it is a false alarm, a false alarm report is output; Fuzzy group reduction and isolation step: This is step 2, loading the fuzzy group reduction and isolation model, and performing fuzzy group reduction and isolation analysis on the fault data based on the fuzzy group reduction and isolation model. If the fault can be isolated to a single field repairable replaceable unit, a fuzzy group isolation report is output; Case fault diagnosis step: This is step 3, loading the fault case, performing case fault diagnosis on the fault data based on the fault case, statistically calculating the probability of field repairable replaceable units associated with the fault, sorting them, and outputting a case fault diagnosis report; Ground fault diagnosis step: This is step 4, loading the ground fault diagnosis model, performing ground fault diagnosis on the aircraft status monitoring data based on the ground fault diagnosis model, analyzing the fault cause, and outputting a ground fault diagnosis report; The fault case is configured with a fault identification code, a fault feature vector, and a fault occurrence threshold. In the case fault diagnosis step, ground fault diagnosis is performed on the aircraft status monitoring data based on the ground fault diagnosis model. Specifically: Read fault data one by one; Determine whether there is a fault identification code in the fault data; If the fault identification code does not exist in the fault data, it is determined that no case fault has occurred; If there is a fault identification code in the fault data, the feature vector of the fault data is extracted and the similarity with the fault feature vector is calculated. If the similarity exceeds the fault occurrence threshold, it is determined that a case fault has occurred. The probability of field repairable and replaceable units associated with the fault is then statistically calculated and sorted. If the similarity is less than the fault occurrence threshold, it is determined that no case fault has occurred.

2. The aircraft ground PHM system fault enhanced diagnosis method according to claim 1, characterized in that: The false alarm suppression model is configured with false alarm suppression identification features, false alarm suppression criteria, and false alarm suppression judgment time. In the false alarm suppression step, false alarm judgment is performed on the fault data based on the false alarm suppression model, specifically: Read fault data one by one; Determine whether there are false alarm suppression identification features in the fault data; If there is no false alarm suppression identification feature in the fault data, it is judged not to be a false alarm; If there is a false alarm suppression identification feature in the fault data, it is determined whether the fault data meets the false alarm suppression criterion and the duration exceeds the false alarm suppression judgment time. If so, it is determined to be a false alarm; if not, it is determined not to be a false alarm.

3. The aircraft ground PHM system fault enhanced diagnosis method according to claim 1, characterized in that: The fuzzy group reduction isolation model is configured with fuzzy group reduction isolation identification features, fuzzy group reduction isolation criteria, and fuzzy group reduction isolation judgment time. In the fuzzy group reduction isolation step, fuzzy group reduction isolation analysis is performed on the fault data based on the fuzzy group reduction isolation model. Specifically, Read fault data one by one; Determine whether there are fuzzy group reduction isolation identification features in the fault data; If there is no fuzzy group reduction isolation identification feature in the fault data, the fuzzy group reduction isolation analysis is not performed; If there is a fuzzy group reduction isolation identification feature in the fault data, it is determined whether the fault data meets the fuzzy group reduction isolation criterion and the duration exceeds the fuzzy group reduction isolation judgment time. If so, a fuzzy group reduction isolation analysis is performed to obtain the field repairable and replaceable unit associated with the fault. If not, the fuzzy group reduction isolation analysis is not performed.

4. The aircraft ground PHM system fault enhanced diagnosis method according to claim 1, characterized in that: The ground fault diagnosis model is configured with ground fault judgment criteria and ground fault judgment time. In the ground fault diagnosis step, ground fault diagnosis is performed on the aircraft status monitoring data based on the ground fault diagnosis model. Specifically: Read aircraft status monitoring data one by one; Determine whether the aircraft status monitoring data meets the ground fault judgment criteria and the duration exceeds the ground fault judgment time. If so, it is determined that a ground fault has occurred. If not, it is determined that no ground fault has occurred.

5. An aircraft ground PHM system fault enhanced diagnosis system, characterized by: include: False alarm suppression module: loads the false alarm suppression model, and based on the false alarm suppression model, performs false alarm judgment on the fault data. If it is a false alarm, a false alarm report is output; Fuzzy group reduction isolation module: loads the fuzzy group reduction isolation model and performs fuzzy group reduction isolation analysis on the fault data based on the fuzzy group reduction isolation model. If the fault can be isolated to a single field-repairable replaceable unit, a fuzzy group isolation report is output. Case fault diagnosis module: loads fault cases, performs case fault diagnosis on fault data based on the fault cases, statistically calculates the probability of field repairable replaceable units associated with the faults, sorts them, and outputs a case fault diagnosis report; Ground fault diagnosis module: loads the ground fault diagnosis model, performs ground fault diagnosis on aircraft status monitoring data based on the ground fault diagnosis model, analyzes the fault cause, and outputs a ground fault diagnosis report; The fault case is configured with a fault identification code, fault feature vector, and fault occurrence threshold. In the case fault diagnosis module, ground fault diagnosis is performed on the aircraft status monitoring data based on the ground fault diagnosis model. Specifically: Read fault data one by one; Determine whether there is a fault identification code in the fault data; If the fault identification code does not exist in the fault data, it is determined that no case fault has occurred; If there is a fault identification code in the fault data, the feature vector of the fault data is extracted and the similarity with the fault feature vector is calculated. If the similarity exceeds the fault occurrence threshold, it is determined that a case fault has occurred. The probability of field repairable and replaceable units associated with the fault is then statistically calculated and sorted. If the similarity is less than the fault occurrence threshold, it is determined that no case fault has occurred.

6. The aircraft ground PHM system fault enhanced diagnosis system according to claim 5, characterized in that: The false alarm suppression model is configured with false alarm suppression identification features, false alarm suppression criteria, and false alarm suppression judgment time. In the false alarm suppression module, false alarm judgment is performed on the fault data based on the false alarm suppression model. Specifically: Read fault data one by one; Determine whether there are false alarm suppression identification features in the fault data; If there is no false alarm suppression identification feature in the fault data, it is judged not to be a false alarm; If there is a false alarm suppression identification feature in the fault data, it is determined whether the fault data meets the false alarm suppression criterion and the duration exceeds the false alarm suppression judgment time. If so, it is determined to be a false alarm; if not, it is determined not to be a false alarm.

7. The aircraft ground PHM system fault enhanced diagnosis system according to claim 5, characterized in that: The fuzzy group reduction isolation model is configured with fuzzy group reduction isolation identification features, fuzzy group reduction isolation criteria, and fuzzy group reduction isolation judgment time. In the fuzzy group reduction isolation module, fuzzy group reduction isolation analysis is performed on the fault data based on the fuzzy group reduction isolation model. Specifically: Read fault data one by one; Determine whether there are fuzzy group reduction isolation identification features in the fault data; If there is no fuzzy group reduction isolation identification feature in the fault data, the fuzzy group reduction isolation analysis is not performed; If there is a fuzzy group reduction isolation identification feature in the fault data, it is determined whether the fault data meets the fuzzy group reduction isolation criterion and the duration exceeds the fuzzy group reduction isolation judgment time. If so, a fuzzy group reduction isolation analysis is performed to obtain the field repairable and replaceable unit associated with the fault. If not, the fuzzy group reduction isolation analysis is not performed.

8. The aircraft ground PHM system fault enhanced diagnosis system according to claim 5, characterized in that: The ground fault diagnosis model is configured with ground fault judgment criteria and ground fault judgment time. In the ground fault diagnosis module, based on the ground fault diagnosis model, ground fault diagnosis is performed on the aircraft status monitoring data. Specifically: Read aircraft status monitoring data one by one; Determine whether the aircraft status monitoring data meets the ground fault judgment criteria and the duration exceeds the ground fault judgment time. If so, it is determined that a ground fault has occurred. If not, it is determined that no ground fault has occurred.

Images