CN115905015A - Reliability testing system and method - Google Patents
Reliability testing system and method Download PDFInfo
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Abstract
The invention provides a reliability test system and a method, wherein the reliability test system comprises: the fault injection testing module is used for acquiring a trigger result of a fault injection testing control in the reliability testing interface and performing fault injection operation based on the trigger result of the fault injection testing control; the periodic message frame loss monitoring module is used for acquiring a triggering result of a periodic message frame loss monitoring control in the reliability test interface and carrying out periodic message frame loss monitoring operation based on the triggering result of the periodic message frame loss control; and the bus load rate monitoring module is used for acquiring the trigger result of the bus load rate monitoring control in the reliability test interface and carrying out bus load rate monitoring operation based on the trigger result of the bus load rate monitoring control. The invention can test the reliability of the aerospace system software with higher test efficiency and test quality, thereby correcting errors which have large influence on the reliability in time based on the test result and improving the reliability and robustness of the aerospace system equipment software.
Description
Technical Field
The invention relates to the technical field of aerospace system software reliability testing, in particular to a reliability testing system and method.
Background
Software reliability testing requires that multiple tests are performed aiming at functions which are used by users frequently and are easy to make mistakes, and errors which have large influence on reliability are found and corrected by concentrated force. In the current reliability testing process of the aerospace system software, testers mainly carry out case design and execution according to respective testing experiences, a systematic testing tool is lacked for standard guidance, the testing efficiency is low, and the testing quality is difficult to ensure.
Disclosure of Invention
The invention mainly aims to provide a reliability test system and a reliability test method, and aims to solve the technical problems that in the current reliability test process of aerospace system software, testers mainly carry out case design and execution according to respective test experiences, a systematic test tool is lacked for standard guidance, the test efficiency is low, and the test quality is difficult to ensure.
In a first aspect, the present invention provides a reliability testing system, comprising:
the fault injection testing module is used for acquiring a trigger result of a fault injection testing control in the reliability testing interface and performing fault injection operation based on the trigger result of the fault injection testing control;
the periodic message frame loss monitoring module is used for acquiring a triggering result of a periodic message frame loss monitoring control in the reliability test interface and carrying out periodic message frame loss monitoring operation based on the triggering result of the periodic message frame loss control;
and the bus load rate monitoring module is used for acquiring a trigger result of the bus load rate monitoring control in the reliability test interface and carrying out bus load rate monitoring operation based on the trigger result of the bus load rate monitoring control.
Optionally, the fault injection operation corresponding to the fault injection testing module includes injecting an exception message, performing super-threshold transmission on a parameter with amplitude limitation, and performing a test according to an error flow sequence, where the exception message includes a message with correct ID data, a message with CRC check and sending an erroneous CRC, and a message with a multiple-frame delivery sequence error.
Optionally, the periodic message frame loss monitoring operation corresponding to the periodic message frame loss monitoring module includes frame counting real-time monitoring of the periodic message, continuous frame loss quantity real-time monitoring of the periodic message, total frame loss quantity real-time monitoring in the whole test flow, and continuous frame loss time marking of the periodic message.
Optionally, the bus load rate monitoring operation corresponding to the bus load rate monitoring module includes real-time monitoring of the current load rate and the peak load rate of the bus, display of a bus load rate curve, and injection of an invalid bus message.
Optionally, the reliability testing system further includes:
the basic database module is used for providing basic database files;
the CAN data transceiver is used for receiving and transmitting process data of control physical quantity and feedback physical quantity of the tested aerospace system software based on a CAN bus;
and the data processing module is used for carrying out data processing on the process data of the control physical quantity and the feedback physical quantity of the tested aerospace system software received and transmitted by the CAN data transceiver in a precompiled compiler environment based on the basic database file and the local file.
In a second aspect, the present invention further provides a reliability testing method, where the reliability testing method is applied to the reliability testing system, and the reliability testing method includes:
the fault injection testing module acquires a trigger result of a fault injection testing control in the reliability testing interface and performs fault injection operation based on the trigger result of the fault injection testing control;
the periodic message frame loss monitoring module acquires a trigger result of a periodic message frame loss monitoring control in a reliability test interface, and performs periodic message frame loss monitoring operation based on the trigger result of the periodic message frame loss control;
and the bus load rate monitoring module acquires a trigger result of a bus load rate monitoring control in the reliability test interface and carries out bus load rate monitoring operation based on the trigger result of the bus load rate monitoring control.
Optionally, the fault injection operation corresponding to the fault injection testing module includes injecting an exception message, performing super-threshold transmission on a parameter with amplitude limitation, and performing a test according to an error flow sequence, where the exception message includes a message with correct ID data, a message with CRC check and sending an error CRC, and a message with a multi-frame transmission sequence error.
Optionally, the periodic message frame loss monitoring operation corresponding to the periodic message frame loss monitoring module includes frame counting real-time monitoring of the periodic message, continuous frame loss quantity real-time monitoring of the periodic message, total frame loss quantity real-time monitoring in the whole test flow, and continuous frame loss time marking of the periodic message.
Optionally, the bus load rate monitoring operation corresponding to the bus load rate monitoring module includes real-time monitoring of the current load rate and the peak load rate of the bus, display of a bus load rate curve, and injection of an invalid bus message.
Optionally, the reliability testing method further includes:
the basic database module is used for providing basic database files;
the CAN data transceiver is used for receiving and transmitting process data of control physical quantity and feedback physical quantity of the tested aerospace system software based on a CAN bus;
and the data processing module is used for processing the process data of the control physical quantity and the feedback physical quantity of the tested aerospace system software received and transmitted by the CAN data transceiver based on the basic database file and the local file in the precompiled compiler environment.
The invention provides a reliability test system and a method, wherein the reliability test system comprises: the fault injection testing module is used for acquiring a trigger result of a fault injection testing control in the reliability testing interface and performing fault injection operation based on the trigger result of the fault injection testing control; the periodic message frame loss monitoring module is used for acquiring a triggering result of a periodic message frame loss monitoring control in the reliability test interface and carrying out periodic message frame loss monitoring operation based on the triggering result of the periodic message frame loss control; and the bus load rate monitoring module is used for acquiring the trigger result of the bus load rate monitoring control in the reliability test interface and carrying out bus load rate monitoring operation based on the trigger result of the bus load rate monitoring control. The invention can test the reliability of the aerospace system software with higher test efficiency and test quality, thereby correcting errors which have large influence on the reliability in time based on the test result and improving the reliability and robustness of the aerospace system equipment software.
Drawings
FIG. 1 is a block diagram of an embodiment of a reliability testing system according to an embodiment of the present invention;
fig. 2 is a schematic flow chart of an embodiment of a reliability testing method according to an embodiment of the present invention.
The implementation, functional features and advantages of the present invention will be further described with reference to the accompanying drawings.
Detailed Description
It should be understood that the specific embodiments described herein are merely illustrative of the invention and are not intended to limit the invention.
On the first hand, in the existing reliability test process of the aerospace system software, the situation that testers mainly perform case design and execution according to respective test experiences and lack systematic test tools for standard guidance is considered, and the test efficiency and the test quality are low. Software reliability testing requires multiple tests for functions which are frequently used by users and prone to errors, and errors which have large influences on reliability are found and corrected by concentrated force. Therefore, the embodiment of the invention provides a reliability test system.
Referring to fig. 1, fig. 1 is a block diagram of a reliability testing system according to an embodiment of the invention.
In one embodiment of the reliability testing system of the present invention, the reliability testing system comprises:
the fault injection testing module 10 is configured to obtain a trigger result of a fault injection testing control in the reliability testing interface, and perform a fault injection operation based on the trigger result of the fault injection testing control;
the periodic message frame loss monitoring module 20 is configured to obtain a trigger result of a periodic message frame loss monitoring control in the reliability test interface, and perform a periodic message frame loss monitoring operation based on the trigger result of the periodic message frame loss control;
and the bus load rate monitoring module 30 is configured to obtain a trigger result of a bus load rate monitoring control in the reliability test interface, and perform a bus load rate monitoring operation based on the trigger result of the bus load rate monitoring control.
In this embodiment, the reliability test system is developed based on CANoe software, a portable computer or a PC is used as an upper computer, a system basic database is configured on the upper computer through cannb + + of the CANoe software, and includes system nodes, messages, signals and environment variables, reliability test interface settings of a fault injection module, a periodic message frame loss monitoring module and a bus load rate monitoring module are completed through a panel editor of the CANoe software, and include control settings and physical quantity display settings on an interface, and meanwhile, links of the system basic database are performed on the controls and the physical quantities on the interface. And finally, finishing message triggering, control triggering and timer triggering event function processing in a capl compiler environment, and transmitting a processing result to be displayed to an associated reliability test interface in real time.
When the reliability of the aerospace system software is tested, besides the normal logic branches of the software, the aerospace system equipment software can take corresponding fault-tolerant measures when the abnormal logic branches of the software under other abnormal working conditions need to be verified through fault injection, so that the coverage rate of statement branches and conditional branches of the software is improved, and the reliability of the software is verified. The method is characterized in that fault injection is carried out in a physical environment of the aerospace system, and all abnormal working conditions are difficult to simulate, wherein the hardware structure determines that part of the working conditions cannot be simulated, and the part of the working conditions has irreversible damage to the hardware.
The fault injection module in the reliability test system based on the CANoe software just makes up the situation that the real test environment can not simulate all abnormal working conditions. For example, the working range of the power supply in the physical test environment is within ± 5V, and normally, the statement branch with the power supply voltage larger than 8V cannot be executed in the software. And the fault injection test module included in the reliability system can perform fault injection by performing fault injection operation based on the trigger instruction of the fault injection test control after receiving the trigger instruction of the fault injection test control in the reliability test interface. If the CAN message containing the power supply voltage physical quantity larger than 8V is sent to the bus, whether the execution condition of the software meets the requirement after entering the branch larger than 8V is checked.
The space system needs real-time periodic messages to provide real-time navigation calculation, and the monitoring of the periodic messages is also used for testing the reliability of the space system software, so that the space system software is in an out-of-control state when the number of frames of the periodic messages are continuously lost under each working condition is verified, and the maximum limit of frame loss of the periodic messages for keeping the space system software still capable of normally running under each working condition is obtained. Therefore, when the reliability system in this embodiment performs the reliability test on the aerospace system software, if the trigger instruction of the periodic message frame loss monitoring control in the reliability test interface is received, the periodic message frame loss monitoring module performs the periodic message frame loss monitoring operation based on the trigger instruction of the periodic message frame loss monitoring control, for example, counts the time stamps or frames of the periodic messages to realize the maximum time interval statistics of the frame loss of the periodic message frame loss amount.
Meanwhile, the CAN messages CAN be transmitted on the CAN bus of the aerospace system in real time, so that the load rate on the CAN bus is monitored and analyzed, the real-time transmission quantity of the CAN messages on the system CAN bus of the system software under a certain working condition CAN be found, the message blockage on the CAN bus is avoided, and the reliability of the aerospace system software is further ensured. Therefore, the bus load rate monitoring module included in the reliability system in this embodiment performs a bus load rate monitoring operation based on the triggering instruction of the bus load rate monitoring control if the triggering instruction of the bus load rate monitoring control in the reliability test interface is received when the reliability test is performed on the aerospace system software.
The reliability of the aerospace system software is tested by the fault injection testing module, the periodic message monitoring module and the bus load rate monitoring module in the scheme of the embodiment, so that the testing efficiency and the testing quality are improved, and therefore, subsequent aerospace system managers can correct errors which have large influences on the reliability in time based on the testing result, and the reliability and the robustness of the aerospace system equipment software are improved.
Further, in an embodiment, the fault injection operation corresponding to the fault injection testing module includes injecting an exception message, performing super-threshold transmission on a parameter with amplitude limitation, and performing a test according to an error flow sequence, where the exception message includes a message with error ID correct data, a message with correct ID error data, a message with CRC check to send an error CRC, and a message with a multi-frame delivery sequence error.
In this embodiment, the fault injection test module verifies whether the aerospace system equipment software can take corresponding fault-tolerant measures when the aerospace system equipment software triggers the abnormal logic branch under other abnormal working conditions by triggering the fault injection operation, so that the coverage rate of statement branches and conditional branches of the software is improved, and the reliability of the software is verified. The fault injection test module can simulate single-machine artificial injection abnormity, and carry out parameter modification on the single-machine simulation to enter an abnormal logic branch, wherein the fault injection test module comprises the steps of injecting abnormal messages, carrying out super-threshold transmission on parameters with amplitude limitation and carrying out test according to an error flow sequence, such as messages with error ID correct data, messages with correct ID error data, messages with CRC check and sending error CRC and multi-frame transmission sequence error messages, so as to test a CRC check mechanism and test an ID abnormity test and response mechanism.
Further, in an embodiment, the periodic message frame loss monitoring operation corresponding to the periodic message frame loss monitoring module includes frame counting real-time monitoring of the periodic message, continuous frame loss number real-time monitoring of the periodic message, total frame loss amount real-time monitoring in the whole test flow, and continuous frame loss time marking of the periodic message.
In this embodiment, the periodic message frame loss monitoring module verifies the maximum periodic message frame loss limit that the aerospace system software can still normally operate under various working conditions by triggering the periodic message frame loss monitoring operation. The periodic message frame loss monitoring operation comprises the steps of processing serial numbers of two continuous frames through a message trigger mechanism to monitor the frame count of the periodic message in real time, monitor the continuous frame loss quantity of the periodic message in real time, monitor the total frame loss quantity in the whole testing process in real time and mark the continuous frame loss time of the periodic message, and the aerospace system software can be in an out-of-control state when the number of the continuous frames of the periodic message are lost under each working condition according to the running state of the aerospace system, so that a follow-up aerospace system manager can control the frame loss quantity of the periodic message in the whole process on the basis of the testing result of the periodic message in time, and the aerospace system software is guaranteed to run normally by adopting real-time periodic message calculation.
Further, in an embodiment, the bus load rate monitoring operation corresponding to the bus load rate monitoring module includes real-time monitoring of the current load rate and the peak load rate of the bus, display of a bus load rate curve, and injection of an invalid bus message.
In this embodiment, the bus load rate monitoring CAN be used for touching the number of CAN messages which are transmitted in real time in a system of system software under a certain working condition, the bus load rate monitoring operation includes real-time monitoring of the current load rate and the peak load rate of the bus and displaying of a bus load rate curve, and a subsequent aerospace system manager CAN analyze the bus data capacity according to the bus load rate curve to avoid message congestion on the CAN bus. And if the bus load rate obtained by analysis is too high, no excessive margin is left to increase the service information of the system, and meanwhile, the anti-interference capability of the system is weak. If the load rate obtained by analysis is too low, the system can increase more service processing, and meanwhile, the anti-interference capability of the system is strong. In the running process of the system, invalid bus messages with different priorities can be injected to simulate artificial improvement of the bus load rate and to undermine the robustness of the system bus load rate.
Further, in an embodiment, the reliability testing system further includes:
the basic database module is used for providing basic database files;
the CAN data transceiver is used for receiving and transmitting process data of control physical quantity and feedback physical quantity of the tested aerospace system software based on a CAN bus;
and the data processing module is used for carrying out data processing on the process data of the control physical quantity and the feedback physical quantity of the tested aerospace system software received and transmitted by the CAN data transceiver in a precompiled compiler environment based on the basic database file and the local file.
In this embodiment, when the aerospace system software performs the reliability test, the basic database file corresponding to the reliability test needs to be called from the upper computer, the process data of the control physical quantity and the feedback physical quantity of the aerospace system software to be tested in the reliability test process is received and transmitted through the CAN bus, and the process is subjected to data processing in a capl compiling environment based on the basic database file and the local file. Therefore, the corresponding reliability test system further comprises a basic database module, a CAN data transceiver and a data processing module, wherein the basic database module is used for providing basic database files, the CAN data transceiver is used for receiving and transmitting data of the control physical quantity and the feedback physical quantity of the tested aerospace system software based on the CAN bus, and the data processing module is used for processing the control physical quantity and the feedback physical quantity of the tested aerospace system software received and transmitted by the CAN data transceiver in a pre-compiled compiler environment based on the basic database files and the local files.
In this embodiment, a reliability testing system is provided, which includes: the fault injection testing module is used for acquiring a trigger result of a fault injection control in the reliability testing interface and performing fault injection operation based on the trigger result of the fault injection control; the periodic message frame loss monitoring module is used for acquiring a triggering result of a periodic message frame loss control in the reliability test interface and carrying out periodic message frame loss monitoring operation based on the triggering result of the periodic message frame loss control; and the bus load rate monitoring module is used for acquiring the trigger result of the bus load rate monitoring control in the reliability test interface and carrying out bus load rate monitoring operation based on the trigger result of the bus load rate monitoring control. The invention can test the reliability of the aerospace system software with higher test efficiency and test quality, thereby correcting errors which have large influence on the reliability in time based on the test result and improving the reliability and robustness of the aerospace system equipment software.
In a second aspect, an embodiment of the present invention further provides a reliability testing method applied to a reliability testing system.
Referring to fig. 2, fig. 2 is a flowchart illustrating a reliability testing method according to an embodiment of the invention.
In an embodiment of the reliability testing method of the present invention, the reliability testing method includes:
step S10, a fault injection testing module obtains a trigger result of a fault injection testing control in a reliability testing interface, and fault injection operation is carried out based on the trigger result of the fault injection testing control;
step S20, the periodic message frame loss monitoring module obtains the triggering result of the periodic message frame loss monitoring control in the reliability test interface, and carries out periodic message frame loss monitoring operation based on the triggering result of the periodic message frame loss control;
and S30, the bus load rate monitoring module acquires a trigger result of a bus load rate monitoring control in the reliability test interface, and carries out bus load rate monitoring operation based on the trigger result of the bus load rate monitoring control.
Further, in an embodiment, the fault injection operation corresponding to the fault injection testing module includes injecting an exception message, performing super-threshold transmission on a parameter with amplitude limitation, and performing a test according to an error flow sequence, where the exception message includes a message with correct ID data, a message with CRC check and sending an erroneous CRC, and a message with a multiple-frame delivery sequence error.
Further, in an embodiment, the periodic message frame loss monitoring operation corresponding to the periodic message frame loss monitoring module includes frame counting real-time monitoring of the periodic message, continuous frame loss number real-time monitoring of the periodic message, total frame loss amount real-time monitoring in the whole test flow, and continuous frame loss time marking of the periodic message.
Further, in an embodiment, the bus load rate monitoring operation corresponding to the bus load rate monitoring module includes real-time monitoring of the current load rate and the peak load rate of the bus, display of a bus load rate curve, and injection of an invalid bus message.
Further, in an embodiment, the reliability testing method further includes:
the basic database module is used for providing basic database files;
the CAN data transceiver is used for receiving and transmitting process data of control physical quantity and feedback physical quantity of the tested aerospace system software based on a CAN bus;
and the data processing module is used for carrying out data processing on the process data of the control physical quantity and the feedback physical quantity of the tested aerospace system software received and transmitted by the CAN data transceiver in a precompiled compiler environment based on the basic database file and the local file.
The steps of the embodiments in the reliability test method correspond to the functional modules in the embodiments of the reliability test method, and the functions and implementation processes are not described in detail herein.
It should be noted that, in this document, the terms "comprises," "comprising," or any other variation thereof, are intended to cover a non-exclusive inclusion, such that a process, method, article, or system that comprises a list of elements does not include only those elements but may include other elements not expressly listed or inherent to such process, method, article, or system. Without further limitation, an element defined by the phrases "comprising a," "8230," "8230," or "comprising" does not exclude the presence of other like elements in a process, method, article, or system comprising the element.
The above-mentioned serial numbers of the embodiments of the present invention are merely for description and do not represent the merits of the embodiments.
Through the above description of the embodiments, those skilled in the art will clearly understand that the method of the above embodiments can be implemented by software plus a necessary general hardware platform, and certainly can also be implemented by hardware, but in many cases, the former is a better implementation manner. Based on such understanding, the technical solution of the present invention may be embodied in the form of a software product, which is stored in a storage medium (e.g., ROM/RAM, magnetic disk, optical disk) as described above and includes instructions for causing a terminal device to execute the method according to the embodiments of the present invention.
The above description is only a preferred embodiment of the present invention, and not intended to limit the scope of the present invention, and all modifications of equivalent structures and equivalent processes, which are made by using the contents of the present specification and the accompanying drawings, or directly or indirectly applied to other related technical fields, are included in the scope of the present invention.
Claims (10)
1. A reliability testing system, characterized in that the reliability testing system comprises:
the fault injection testing module is used for acquiring a trigger result of a fault injection testing control in the reliability testing interface and performing fault injection operation based on the trigger result of the fault injection testing control;
the periodic message frame loss monitoring module is used for acquiring a triggering result of a periodic message frame loss monitoring control in the reliability test interface and carrying out periodic message frame loss monitoring operation based on the triggering result of the periodic message frame loss control;
and the bus load rate monitoring module is used for acquiring a trigger result of the bus load rate monitoring control in the reliability test interface and carrying out bus load rate monitoring operation based on the trigger result of the bus load rate monitoring control.
2. The reliability testing system of claim 1, wherein: the fault injection operation corresponding to the fault injection test module comprises injecting abnormal messages, carrying out super-threshold transmission on the parameters with amplitude limitation and carrying out test according to an error flow sequence, wherein the abnormal messages comprise messages with error ID correct data, messages with correct ID error data, messages with CRC check sending error CRC and messages with multi-frame transmission sequence errors.
3. The reliability test system of claim 1, wherein: the periodic message frame loss monitoring operation corresponding to the periodic message frame loss monitoring module comprises frame counting real-time monitoring of the periodic message, continuous frame loss quantity real-time monitoring of the periodic message, total frame loss quantity real-time monitoring in the whole testing process and continuous frame loss time marking of the periodic message.
4. The reliability testing system of claim 1, wherein: the bus load rate monitoring operation corresponding to the bus load rate monitoring module comprises real-time monitoring of the current load rate and the peak load rate of the bus, display of a bus load rate curve and injection of invalid bus messages.
5. The reliability test system of claim 1, wherein the reliability test system further comprises:
the basic database module is used for providing basic database files;
the CAN data transceiver is used for receiving and transmitting process data of control physical quantity and feedback physical quantity of the tested aerospace system software based on a CAN bus;
and the data processing module is used for processing the process data of the control physical quantity and the feedback physical quantity of the measured aerospace system software received and transmitted by the CAN data transceiver in the precompiled compiler environment based on the basic database file and the local file.
6. A reliability test method applied to the reliability test system according to claim 1, characterized by comprising:
the fault injection testing module acquires a trigger result of a fault injection testing control in the reliability testing interface and performs fault injection operation based on the trigger result of the fault injection testing control;
the periodic message frame loss monitoring module acquires a trigger result of a periodic message frame loss monitoring control in a reliability test interface, and performs periodic message frame loss monitoring operation based on the trigger result of the periodic message frame loss control;
and the bus load rate monitoring module acquires a trigger result of a bus load rate monitoring control in the reliability test interface and carries out bus load rate monitoring operation based on the trigger result of the bus load rate monitoring control.
7. The reliability test method of claim 6, wherein: the fault injection operation corresponding to the fault injection test module comprises injecting abnormal messages, carrying out super-threshold transmission on the parameters with amplitude limitation and carrying out test according to an error flow sequence, wherein the abnormal messages comprise messages with error ID correct data, messages with correct ID error data, messages with CRC check sending error CRC and messages with multi-frame transmission sequence errors.
8. The reliability test method of claim 6, wherein: the periodic message frame loss monitoring operation corresponding to the periodic message frame loss monitoring module comprises frame counting real-time monitoring of the periodic message, continuous frame loss quantity real-time monitoring of the periodic message, total frame loss quantity real-time monitoring in the whole testing process and continuous frame loss time marking of the periodic message.
9. The reliability test method of claim 6, wherein: the bus load rate monitoring operation corresponding to the bus load rate monitoring module comprises real-time monitoring of the current load rate and the peak load rate of the bus, display of a bus load rate curve and injection of invalid bus messages.
10. The reliability testing method of claim 6, further comprising:
the basic database module is used for providing basic database files;
the CAN data transceiver is used for receiving and transmitting process data of control physical quantity and feedback physical quantity of the tested aerospace system software based on a CAN bus;
and the data processing module is used for carrying out data processing on the process data of the control physical quantity and the feedback physical quantity of the tested aerospace system software received and transmitted by the CAN data transceiver in a precompiled compiler environment based on the basic database file and the local file.
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