Aircraft system-level fault state combined judgment method and device

Abstract

The invention provides an aircraft system-level fault state joint judgment method and device, and belongs to the overall technical field of electromechanical systems in the aviation technology, and the method comprises the steps: searching a corresponding fault code from a first corresponding relation when a fault is monitored; searching a fault incidence matrix corresponding to the fault code from a second corresponding relation, wherein the fault incidence matrix records data cache addresses of system state information, alarm information, parameter information, operation information and associated fault information of the fault; acquiring corresponding system state information, alarm information, parameter information, operation information and associated fault information based on the fault incidence matrix; fault judgment is carried out based on the system state information, the alarm information, the parameter information, the operation information and the associated fault information; according to the method, combined judgment is carried out on complex fault logic caused by aircraft high-level interaction, so that the accuracy and the isolation rate of fault diagnosis are improved, the false alarm rate is reduced, and meanwhile auxiliary judgment of a unit is achieved.

Description

Technical Field

[0001] The present invention belongs to the general technical field of aviation technology electromechanical systems, and in particular relates to a method and device for jointly determining a fault state at the system level of an aircraft. Background Art

[0002] The comprehensive scope of aircraft electromechanical systems generally includes hydraulics, landing gear control, fuel, fire protection, environmental control, anti-icing, oxygen, power supply, lighting and other systems. Due to the wide range of electromechanical systems, many signals, many types of buses and hard lines, and extremely complex transmission topology levels, aircraft electromechanical system fault diagnosis is the most difficult.

[0003] At present, the fault diagnosis of aircraft electromechanical systems is generally carried out through information collection and logical judgment by the electromechanical integrated management system, and the system's complex fault logic is almost 100% dependent on the electromechanical integrated management system. Traditional electromechanical fault diagnosis generally uses corresponding sensors and feedback devices to make functional judgments, and its comprehensive information is limited. When the sensor fails or the transmission path of the electromechanical integrated system itself fails, misjudgment of faults, false alarms, and false alarms will occur. Furthermore, in the face of relatively top-level system-level faults, it is difficult for the system to make accurate isolation and suppression of related alarms, resulting in concentrated explosive display of fault alarms, which brings serious psychological burden to the crew. Summary of the invention

[0004] In order to solve the problem of complex, critical and high false alarm rate of top-level alarms in the current aircraft electromechanical system in the prior art, the present invention provides a method and device for joint determination of aircraft system-level fault status, which retrieves the associated faults and status parameters of the fault by searching the associated matrix, thereby performing comprehensive diagnosis of the fault and realizing associated alarm suppression. The technical solution is as follows:

[0005] In a first aspect, a method for jointly determining a fault state of an aircraft system level is provided, which is used in an electromechanical integrated management system, and the method comprises:

[0006] Step 1: When a fault is detected, a corresponding fault code is searched from a preset first corresponding relationship; the first corresponding relationship records the corresponding relationship between multiple faults and the fault code of each fault; the fault code is used to uniquely identify the fault;

[0007] Step 2: Find the fault association matrix corresponding to the fault code from the preset second corresponding relationship. The second corresponding relationship records the corresponding relationship between the fault code and the fault association matrix. The fault code and the fault association matrix can be a one-to-one relationship or a many-to-one relationship. The fault association matrix records the data cache address of the system status information, alarm information, parameter information, operation information, and associated fault information of the fault;

[0008] Step 3: Obtain corresponding system status information, alarm information, parameter information, operation information, and associated fault information based on the fault association matrix;

[0009] Step 4: Perform fault determination based on system status information, alarm information, parameter information, operation information, and associated fault information.

[0010] Furthermore, the method further comprises:

[0011] Step 5: Determine the corresponding fault handling solution according to the fault determination result;

[0012] Step 6: Send the fault handling plan to the integrated display system so that the driver can understand the fault handling plan in time.

[0013] Furthermore, the method further comprises:

[0014] Step 7: Based on the associated fault information, hide the fault information of the associated fault displayed by the integrated display system, and suppress the warning information of the associated fault. The associated fault is a minor fault that is related to the current fault but does not affect flight safety.

[0015] In one achievable manner, when suppressing the alarm information of the associated fault, the alarm unit is prohibited from sending out an optical alarm signal or a voice alarm signal.

[0016] In a second aspect, a device for jointly determining a fault state of an aircraft system level is provided, which is used in an electromechanical integrated management system, and the device comprises:

[0017] A monitoring module, used for searching a corresponding fault code from a preset first corresponding relationship when a fault is detected; the first corresponding relationship records a corresponding relationship between a plurality of faults and a fault code of each fault; the fault code is used to uniquely identify the fault;

[0018] A search module is used to search for a fault association matrix corresponding to a fault code from a preset second correspondence relationship, wherein the second correspondence relationship records the correspondence between the fault code and the fault association matrix, wherein the fault code and the fault association matrix may be a one-to-one relationship or a many-to-one relationship, and wherein the fault association matrix records the data cache address of the system status information, alarm information, parameter information, operation information, and associated fault information of the fault;

[0019] An acquisition module is used to acquire corresponding system status information, alarm information, parameter information, operation information, and associated fault information based on the fault association matrix;

[0020] The determination module is used to perform fault determination based on system status information, alarm information, parameter information, operation information, and associated fault information.

[0021] Furthermore, the device also includes:

[0022] A determination module is used to determine a corresponding fault handling solution according to the fault determination result;

[0023] The sending module is used to send the fault handling plan to the integrated display system so that the driver can understand the fault handling plan in time.

[0024] Furthermore, the device also includes:

[0025] The suppression module is used to hide the fault information of the associated fault displayed by the integrated display system based on the associated fault information, and to suppress the warning information of the associated fault. The associated fault is a minor fault that is related to the current fault but does not affect flight safety.

[0026] In one achievable manner, the suppression module is used to prohibit the alarm unit from sending out a light alarm signal or a voice alarm signal.

[0027] In a third aspect, there is provided an aircraft system-level fault status joint determination device, comprising a processor and a memory, wherein the processor is configured to execute instructions stored in the memory, and the processor implements the aircraft system-level fault status joint determination method described in any one of the first aspects by executing the instructions.

[0028] In a fourth aspect, a computer-readable storage medium is provided, wherein instructions are stored in the computer-readable storage medium. When the instructions are executed on a processing component of a computer, the processing component executes the aircraft system-level fault status joint determination method as described in any one of the first aspects.

[0029] In a fifth aspect, a computer program product comprising instructions is provided, which, when executed on a computer, enables the computer to execute the aircraft system-level fault status joint determination method as described in any one of the first aspects.

[0030] The beneficial effects of the present invention are at least:

[0031] The present invention provides a method for solving the high false alarm rate of complex, critical and top-level alarms and the suppression of comprehensive alarms. By designing fault triggering criteria, correlation matrix and fault auxiliary criteria, the joint judgment of the fault state is realized. The method can be continuously matured and expanded according to the specific actual situation, and the information suppression, alarm suppression and feedback suppression of the associated faults can be realized, the flight crew can be assisted in decision-making and judgment, and the key parameters can be associated and integrated. BRIEF DESCRIPTION OF THE DRAWINGS

[0032] Figure 1 A flow chart of a method for jointly determining a fault status of an aircraft system level provided by an embodiment of the present invention. DETAILED DESCRIPTION

[0033] In order to make the purpose, technical solution and advantages of the embodiments of the present invention clearer, the technical solution in the embodiments of the present invention will be clearly and completely described below in conjunction with the drawings in the embodiments of the present invention. Obviously, the described embodiments are part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without making creative work are within the scope of protection of the present invention.

[0034] The features and illustrative embodiments of various aspects of the present invention will be described in detail below. In the detailed description below, many specific details are proposed to provide a comprehensive understanding of the present invention. However, it is obvious to those skilled in the art that the present invention can be implemented without the need for some of these specific details. The following description of the embodiments is only to provide a better understanding of the present invention by illustrating examples of the present invention. The present invention is by no means limited to any specific settings and methods proposed below, but covers any improvements, replacements and modifications of structures, methods, devices without departing from the spirit of the present invention. In the accompanying drawings and the following description, known structures and technologies are not shown to avoid unnecessary ambiguity in the present invention.

[0035] It should be noted that, in the absence of conflict, the embodiments of the present invention and the features in the embodiments can be combined with each other, and the embodiments can refer to and quote each other. The present invention will be described in detail below with reference to the accompanying drawings and in combination with the embodiments.

[0036] The present invention is described in detail below with reference to the accompanying drawings and specific embodiments.

[0037] Since an aircraft is a highly cohesive and complex system, all energy for the electromechanical system comes from the secondary energy of the engine. Therefore, the electromechanical systems of the aircraft are interconnected. For many complex faults, such as power system failure, hydraulic system failure and other key top-level faults, there are many factors involved, which are intertwined with each other. For example, the generator's power generation frequency can be used to determine the working status of the hydraulic system's hydraulic pump to isolate the fault of the hydraulic source, and the fuel consumption can also be used to comprehensively determine the level and capacity of the oil supply.

[0038] The present invention proposes a method for diagnosing the fault of an aircraft electromechanical system in an integrated management manner, by formulating rules, establishing label identification, establishing fault connections in software in a passive form, and making a linkage comprehensive judgment with key data of different systems, and by identifying alarms, assisting judgments, and associating conditions to integrate the accuracy and criticality of alarms, assisting pilots to observe key information of the system in a timely manner, thereby solving the problem of accurate positioning when key alarms occur, suppressing unnecessary correlation alarms, improving the accuracy of alarms, and reducing the false alarm rate.

[0039] An embodiment of the present invention provides a method for jointly determining a fault state of an aircraft system level, which is used in an electromechanical integrated management system. The method includes:

[0040] Step 1: When a fault is detected, a corresponding fault code is searched from a preset first corresponding relationship; the first corresponding relationship records the corresponding relationship between multiple faults and the fault code of each fault; the fault code is used to uniquely identify the fault;

[0041] Step 2: searching for a fault association matrix corresponding to the fault code from a preset second correspondence, wherein the second correspondence records the correspondence between the fault code and the fault association matrix, and the fault association matrix records the data cache address of the system status information, alarm information, parameter information, operation information, and associated fault information of the fault;

[0042] Step 3: Obtain corresponding system status information, alarm information, parameter information, operation information, and associated fault information based on the fault association matrix;

[0043] Step 4: Perform fault determination based on system status information, alarm information, parameter information, operation information, and associated fault information.

[0044] In one embodiment, the method further comprises:

[0045] Step 5: Determine the corresponding fault handling solution according to the fault determination result;

[0046] Step 6: Send the troubleshooting solution to the integrated display system.

[0047] In the related art, when facing a relatively top-level system-level fault, it is difficult for the system to accurately isolate and suppress related alarms, resulting in concentrated and explosive display of fault alarms, which brings serious psychological burden to the unit. To solve this problem, in one embodiment, the method further includes:

[0048] Step 7: Based on the associated fault information, the fault information of the associated fault displayed by the integrated display system is hidden, and the warning information of the associated fault is suppressed. The associated fault is a minor fault that is related to the current fault but does not affect flight safety. When suppressing the warning information of the associated fault, the warning unit is prohibited from emitting a light warning signal or a voice warning signal. For example, the corresponding warning light can be controlled not to emit light, or the corresponding alarm can be controlled not to emit an alarm prompt voice. In this way, key information can be retained to prevent the pilot from being disturbed by other factors, thereby solving the problem of suppressing related alarms of the aircraft's electromechanical system.

[0049] In another embodiment, the method of the present invention is implemented as follows:

[0050] 1) When a fault occurs on the aircraft, the electromechanical integrated management system detects the fault and triggers the relevant fault judgment logic. At the same time, when the fault monitoring detects the fault trigger, the relevant fault code is retrieved.

[0051] 2) Query the fault association matrix of the fault through the fault code. Through the fault association matrix, find the relevant status data of the fault in the data storage buffer pool, and call the auxiliary judgment logic related to the fault.

[0052] 3) When the fault triggering criteria are met, the associated faults and state parameters of the fault are retrieved by searching the associated matrix, so as to perform a comprehensive diagnosis of the fault.

[0053] 4) According to the auxiliary judgment criteria cited by the fault correlation matrix, make auxiliary judgments on the fault status, send the judgment results and related judgment criteria, and make fault handling suggestions.

[0054] 5) During the fault handling suggestion process, a comprehensive judgment will be made based on the on-site status, current status, auxiliary criteria, and parameters, status, and information related to the auxiliary criteria. Information suppression, alarm suppression, and feedback suppression will be performed on the associated faults associated with the fault.

[0055] 6) The comprehensive displayed information is transmitted to the crew. This information indicates the work content required for manual review after the fault occurs, as well as relevant disposal suggestions.

[0056] 7) In order to ensure the timeliness of fault detection, the direct judgment of the fault triggering is sent to the unit for display as the original fault alarm at the same time as the fault occurs.

[0057] 8) The crew uses the original fault information and handling suggestion information to perform manual logical judgment, reduce the crew's psychological pressure, and help the crew to confirm and handle the fault in a timely and effective manner.

[0058] An embodiment of the present invention further provides an aircraft system-level fault state joint determination device for use in an electromechanical integrated management system, the device comprising:

[0059] A monitoring module, used for searching a corresponding fault code from a preset first corresponding relationship when a fault is detected; the first corresponding relationship records a corresponding relationship between a plurality of faults and a fault code of each fault; the fault code is used to uniquely identify the fault;

[0060] A search module is used to search for a fault association matrix corresponding to a fault code from a preset second correspondence relationship, wherein the second correspondence relationship records the correspondence between the fault code and the fault association matrix, wherein the fault code and the fault association matrix may be a one-to-one relationship or a many-to-one relationship, and wherein the fault association matrix records the data cache address of the system status information, alarm information, parameter information, operation information, and associated fault information of the fault;

[0061] An acquisition module is used to acquire corresponding system status information, alarm information, parameter information, operation information, and associated fault information based on the fault association matrix;

[0062] The determination module is used to perform fault determination based on system status information, alarm information, parameter information, operation information, and associated fault information.

[0063] Furthermore, the device also includes:

[0064] A determination module is used to determine a corresponding fault handling solution according to the fault determination result;

[0065] The sending module is used to send the fault handling plan to the integrated display system so that the driver can understand the fault handling plan in time.

[0066] Furthermore, the device also includes:

[0067] The suppression module is used to hide the fault information of the associated fault displayed by the integrated display system based on the associated fault information, and to suppress the warning information of the associated fault. The associated fault is a minor fault that is related to the current fault but does not affect flight safety.

[0068] In one achievable manner, the suppression module is used to prohibit the alarm unit from sending out a light alarm signal or a voice alarm signal.

[0069] The specific execution process of each module in the present invention can refer to the specific process of the relevant steps of the above method, which will not be repeated here.

[0070] An embodiment of the present invention further provides an aircraft system-level fault status joint determination device, comprising a processor and a memory, wherein the processor is configured to execute instructions stored in the memory, and the processor implements the aircraft system-level fault status joint determination method described in the embodiment of the present invention by executing the instructions.

[0071] An embodiment of the present invention further provides a computer-readable storage medium, wherein the computer-readable storage medium stores instructions, and when the instructions are executed on a processing component of a computer, the processing component executes the aircraft system-level fault status joint determination method described in an embodiment of the present invention.

[0072] An embodiment of the present invention further provides a computer program product comprising instructions, and when the computer program product is run on a computer, the computer is enabled to execute the aircraft system-level fault state joint determination method described in the embodiment of the present invention.

[0073] The above only expresses the implementation mode of the present invention, and its description is relatively specific and detailed, but it cannot be understood as limiting the scope of the 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, which all belong to the protection scope of the present invention. In addition, the parts not detailed in the present invention are all conventional technologies.

Claims

1. A method for jointly determining aircraft system-level fault status, characterized in that: For use in an electromechanical integrated management system, the method comprises: Step 1: When a fault is detected, a corresponding fault code is searched from a preset first corresponding relationship; the first corresponding relationship records the corresponding relationship between multiple faults and the fault code of each fault; the fault code is used to uniquely identify the fault; Step 2: searching for a fault association matrix corresponding to the fault code from a preset second correspondence, wherein the second correspondence records the correspondence between the fault code and the fault association matrix, and the fault association matrix records the data cache address of the system status information, alarm information, parameter information, operation information, and associated fault information of the fault; Step 3: Obtain corresponding system status information, alarm information, parameter information, operation information, and associated fault information based on the fault association matrix; Step 4: Perform fault determination based on system status information, alarm information, parameter information, operation information, and associated fault information.

2. The method according to claim 1, characterized in that The method further comprises: Step 5: Determine the corresponding fault handling solution according to the fault determination result; Step 6: Send the troubleshooting solution to the integrated display system.

3. The method according to claim 2, characterized in that The method further comprises: Step 7: Based on the associated fault information, hide the fault information of the associated fault displayed by the integrated display system, and suppress the warning information of the associated fault. The associated fault is a minor fault that is related to the current fault but does not affect flight safety.

4. The method according to claim 3, characterized in that When suppressing the alarm information of the associated fault, the alarm unit is prohibited from sending out an optical alarm signal or a voice alarm signal.

5. A device for jointly determining the fault status of an aircraft system, characterized in that: Used in an integrated electromechanical management system, the device comprises: A monitoring module, used for searching a corresponding fault code from a preset first corresponding relationship when a fault is detected; the first corresponding relationship records a corresponding relationship between a plurality of faults and a fault code of each fault; the fault code is used to uniquely identify the fault; A search module is used to search for a fault association matrix corresponding to a fault code from a preset second correspondence relationship, wherein the second correspondence relationship records the correspondence between the fault code and the fault association matrix, and the fault association matrix records the data cache address of the system status information, alarm information, parameter information, operation information, and associated fault information of the fault; An acquisition module is used to acquire corresponding system status information, alarm information, parameter information, operation information, and associated fault information based on the fault association matrix; The determination module is used to perform fault determination based on system status information, alarm information, parameter information, operation information, and associated fault information.

6. The device according to claim 5, characterized in that The device also includes: A determination module is used to determine a corresponding fault handling solution according to the fault determination result; The sending module is used to send the fault handling solution to the integrated display system.

7. The device according to claim 6, characterized in that The device also includes: The suppression module is used to hide the fault information of the associated fault displayed by the integrated display system based on the associated fault information, and to suppress the warning information of the associated fault. The associated fault is a minor fault that is related to the current fault but does not affect flight safety.

8. The device according to claim 7, characterized in that The suppression module is used to prohibit the alarm unit from sending out an optical alarm signal or a voice alarm signal.

9. An aircraft system-level fault state joint determination device, characterized in that: The method comprises a processor and a memory, wherein the processor is configured to execute instructions stored in the memory, and the processor implements the method according to any one of claims 1 to 4 by executing the instructions.

10. A computer-readable storage medium, characterized in that: The computer-readable storage medium stores instructions, and when the instructions are executed on a processing component of a computer, the processing component is caused to execute the method according to any one of claims 1 to 4.

Images