Rapid positioning method for software exception of aviation airborne display system

Abstract

The invention provides an aviation airborne display system software exception rapid positioning method, and belongs to the technical field of avionics, and the method comprises the steps: exporting a bus record file and a video record file of a flight sortie where a fault occurs from airplane recording equipment; determining the moment when the fault occurs as a first moment through the video recording file; analyzing the bus record file to obtain a bus data record database; sending data in the bus data recording database in a preset time period before and after the first moment to the tested product; the running state of the tested product is observed, and if no fault occurs, the preset time period is adjusted; and sending the data in the bus data recording database adjusted in the preset time period to the tested product, and observing the running state of the tested product until the fault which is the same as the fault at the first moment occurs. Through the processing scheme provided by the invention, the software fault positioning efficiency and accuracy of the airborne display system are improved.

Description

Technical Field

[0001] The present application relates to the field of avionics technology, and in particular to a method for quickly locating software anomalies in an aviation airborne display system. Background Art

[0002] As an important human-machine interaction device on board, the aircraft display provides the operator with real-time flight parameters and the status of each onboard equipment system. It also provides parameter setting functions and switches the working mode of system equipment. Most of the display system product functions are completed by software, and any problems found need to be quickly diagnosed and solved.

[0003] The aviation display system adopts ARI NC429, FC-AE and other aviation airborne buses. The system also contains a dedicated recording device that can record data and video information during system operation.

[0004] At present, when a display screen fails, the main method is to have a preliminary understanding of the phenomenon at the time of the failure through the recorded video at the time of the failure, and then use the form of a fault tree to sort out the possible fault branches. Then, combined with the flight record data, the code with possible defects is analyzed through code walkthrough, and then verified after the modification is completed. With the continuous increase in the amount of onboard data, the scale of display system software has also increased dramatically. Since the software is internally opaque during operation and the external manifestations are complex and diverse when a failure occurs, software fault diagnosis is difficult. At present, the efficiency of fault analysis through the original method is low, and the data recorded by the system cannot be fully utilized. Therefore, it is necessary to implement a method for fault diagnosis of aviation airborne display system software to quickly locate the problem. Summary of the invention

[0005] In view of this, an embodiment of the present application provides a method for quickly locating software anomalies in an aviation airborne display system, which at least partially solves the problem of difficulty in diagnosing airborne software faults in the prior art. In the original fault diagnosis method, the recorded data on the aircraft is usually in the form of static files, which are manually searched one by one, and then the working state entered by the device after receiving the data is determined.

[0006] The present application provides a method for quickly locating software anomalies of an aviation airborne display system, the method comprising:

[0007] Export the bus record file and video record file of the flight where the failure occurred from the aircraft recording device;

[0008] Determine the time when the fault occurs as the first time through the video recording file;

[0009] Parsing the bus record file to obtain a bus data record database;

[0010] Sending the data of a preset time period before and after the first moment in the bus data record database to the product under test;

[0011] Observe the operating status of the tested product, and if no fault occurs, adjust the preset time period;

[0012] The data in the bus data recording database adjusted for the preset time period is sent to the product under test, and the running status of the product under test is observed until the same fault as at the first moment occurs.

[0013] According to a specific implementation of the embodiment of the present application, the method further includes:

[0014] When a fault occurs, monitoring information is added to the onboard display software to confirm the internal data status in order to resolve the software fault defect.

[0015] According to a specific implementation of the embodiment of the present application, parsing the bus record file to obtain a bus data record database includes:

[0016] Parse the bus record file to obtain each time scale of the bus record file, the duration of two adjacent time scales is T, and record the starting position of each time scale in the bus record file. The first time scale of the bus record file is T0, and the last time scale of the bus record file is T n , forming the bus data record database.

[0017] According to a specific implementation method of an embodiment of the present application, the initial moment of the preset time period before and after the first moment is Te-T×m, and the end moment is Te-T×n, where Te is the first moment, and m and n are arbitrary integers.

[0018] According to a specific implementation of the embodiment of the present application, the adjusting the preset time period includes:

[0019] The preset time period is adjusted by increasing m.

[0020] Beneficial effects:

[0021] The method for quickly locating software anomalies in an aviation airborne display system in the embodiment of the present application can record data through the airborne bus, reproduce all states including the fault state, and determine the external input state at the time of the fault in combination with the video record at the time of the fault. The software processing branch corresponding to the fault generated inside the software can then be determined, and the software fault defect can be resolved, thereby improving the efficiency and accuracy of locating software faults in the airborne display system. BRIEF DESCRIPTION OF THE DRAWINGS

[0022] In order to more clearly illustrate the technical solutions of the embodiments of the present application, the drawings required for use in the embodiments will be briefly introduced below. Obviously, the drawings described below are only some embodiments of the present application. For ordinary technicians in this field, other drawings can be obtained based on these drawings without paying creative work.

[0023] Figure 1 The present invention is a flowchart of a method for quickly locating software anomalies of an aviation airborne display system according to an embodiment of the present invention. DETAILED DESCRIPTION

[0024] The embodiments of the present application are described in detail below with reference to the accompanying drawings.

[0025] The following describes the implementation methods of the present application through specific examples, and those skilled in the art can easily understand other advantages and effects of the present application from the contents disclosed in this specification. Obviously, the described embodiments are only a part of the embodiments of the present application, rather than all the embodiments. The present application can also be implemented or applied through other different specific implementation methods, and the details in this specification can also be modified or changed in various ways based on different viewpoints and applications without departing from the spirit of the present application. It should be noted that, in the absence of conflict, the following embodiments and the features in the embodiments can be combined with each other. Based on the embodiments in the present application, all other embodiments obtained by ordinary technicians in the field without making creative work belong to the scope of protection of the present application.

[0026] It should be noted that various aspects of the embodiments within the scope of the appended claims are described below. It should be apparent that the aspects described herein can be embodied in a wide variety of forms, and any specific structure and / or function described herein is merely illustrative. Based on the present application, it should be understood by those skilled in the art that an aspect described herein can be implemented independently of any other aspect, and two or more of these aspects can be combined in various ways. For example, any number of aspects described herein can be used to implement the device and / or practice the method. In addition, other structures and / or functionalities other than one or more of the aspects described herein can be used to implement this device and / or practice this method.

[0027] It should also be noted that the illustrations provided in the following embodiments are only schematic illustrations of the basic concept of the present application. The illustrations only show the components related to the present application rather than being drawn according to the number, shape and size of the components in actual implementation. In actual implementation, the type, quantity and proportion of each component may be changed arbitrarily, and the component layout may also be more complicated.

[0028] Additionally, in the following description, specific details are provided to facilitate a thorough understanding of the examples. However, it will be understood by those skilled in the art that the aspects described may be practiced without these specific details.

[0029] The embodiment of the present application provides a method for quickly locating software anomalies in an aviation airborne display system. Based on the airborne data recording device, the data in the recording card is read, the data packet is encapsulated, and the data is injected into the product frame by frame again according to the original bus form and with the help of the product's communication test environment, so as to reproduce the complete dynamic operation process of the software. Figure 1 Described in detail, the method comprises the following steps:

[0030] Export the bus record file and video record file of the flight where the failure occurred from the aircraft recording device;

[0031] Determine the time when the fault occurs as the first time through the video recording file;

[0032] Parsing the bus record file to obtain a bus data record database;

[0033] Sending the data of a preset time period before and after the first moment in the bus data record database to the product under test;

[0034] Observe the operating status of the tested product, and if no fault occurs, adjust the preset time period;

[0035] The data in the bus data recording database adjusted for the preset time period is sent to the product under test, and the running status of the product under test is observed until the same fault as at the first moment occurs.

[0036] Furthermore, the method further comprises:

[0037] When a fault occurs, monitoring information is added to the onboard display software to confirm the internal data status in order to resolve the software fault defect.

[0038] Further, the bus record file is parsed to obtain a bus data record database, including:

[0039] Parse the bus record file to obtain each time scale of the bus record file, the duration of two adjacent time scales is T, and record the starting position of each time scale in the bus record file. The first time scale of the bus record file is T0, and the last time scale of the bus record file is T n , forming the bus data record database.

[0040] Specifically, when recording data on the machine, the time information is recorded in front of the data frame. One or more data frames share a time, and this time is used as the time scale information. A bus record file forms a database, and the database is divided into several sub-items according to each time scale.

[0041] Furthermore, the initial moment of the preset time period before and after the first moment is Te-T×m, and the end moment is Te-T×n, wherein Te is the first moment, and m and n are arbitrary integers.

[0042] Furthermore, the adjusting the preset time period includes:

[0043] The preset time period is adjusted by increasing m.

[0044] The method of the present application is described below with specific steps, using bus test equipment and the product under test to transform the original test environment. The following steps are included:

[0045] 1. Export the optical fiber bus record data and video record files of the flight where the failure occurred from the aircraft recording equipment;

[0046] 2. Retrieve the data frame start marks such as 0xBCB55656, 0xBCB53636, 0xBC95D5D5 in the bus record data, read the single frame data content, parse the record data, obtain the time scale of the record file, take 1 minute as the time scale, record the starting position of each time scale in the file, and form a bus data record database. The first time in the record file is T0 and the last time is T n ;

[0047] 3. Connect the product under test to the bus simulation test equipment and power it on to normal operation;

[0048] 4. Determine the time when the fault occurs through the video recording file;

[0049] 5. Set the start time of sending the power supply of the product under test in step 4 to Te-5min to Te+1min through the parsed database. After that, the test equipment parses the data and sends it to the product.

[0050] 7. Observe the running status of the product. If no fault occurs, power on and off the product again and adjust the time from Te-10min to Te+1min. Repeat the operation until the same fault as the one recorded in the video occurs.

[0051] 8. If the development time is adjusted to T0 and the fault still does not occur, the fault is not related to the external bus data;

[0052] 9. If a fault occurs, add monitoring information to the software to further confirm the internal data status and resolve the software fault defect.

[0053] During specific implementation, for adding monitoring information, you can add plug-in code according to the software running process, gradually find a line of code corresponding to the exception, and then analyze the line of code to solve the fault defect.

[0054] The embodiment provided by the present invention can record data through the onboard bus, reproduce all states including the fault state, and determine the external input state at the time of the fault in combination with the video record at the time of the fault, thereby determining the software processing branch corresponding to the fault generated inside the software and resolving it.

[0055] The above is only a specific implementation of the present application, but the protection scope of the present application is not limited thereto. Any changes or substitutions that can be easily thought of by a person skilled in the art within the technical scope disclosed in the present application should be included in the protection scope of the present application. Therefore, the protection scope of the present application shall be based on the protection scope of the claims.

Claims

1. A method for quickly locating software anomalies in an aviation airborne display system, characterized in that: The method comprises: Export the bus record file and video record file of the flight where the failure occurred from the aircraft recording device; Determine the time when the fault occurs as the first time through the video recording file; Parsing the bus record file to obtain a bus data record database; Sending the data of a preset time period before and after the first moment in the bus data record database to the product under test; Observe the operating status of the tested product, and if no fault occurs, adjust the preset time period; The data in the bus data recording database adjusted for the preset time period is sent to the product under test, and the running status of the product under test is observed until the same fault as at the first moment occurs.

2. The method for quickly locating software anomalies of an aviation airborne display system according to claim 1, characterized in that: The method further comprises: When a fault occurs, monitoring information is added to the onboard display software to confirm the internal data status in order to resolve the software fault defect.

3. The method for quickly locating software anomalies of an aviation airborne display system according to claim 1, characterized in that: The step of parsing the bus record file to obtain a bus data record database includes: Parse the bus record file to obtain each time scale of the bus record file, the duration of two adjacent time scales is T, and record the starting position of each time scale in the bus record file. The first time scale of the bus record file is T0, and the last time scale of the bus record file is T n , forming the bus data record database.

4. The method for quickly locating software anomalies of an aviation airborne display system according to claim 3, characterized in that: The initial moment of the preset time period before and after the first moment is Te-T×m, and the end moment is Te-T×n, where Te is the first moment, and m and n are arbitrary integers.

5. The method for quickly locating software anomalies of an aviation airborne display system according to claim 4, characterized in that: The adjusting the preset time period includes: The preset time period is adjusted by increasing m.

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