CN113703419A - Automatic testing method and device for redundancy management algorithm of flight control system - Google Patents
Automatic testing method and device for redundancy management algorithm of flight control system Download PDFInfo
- Publication number
- CN113703419A CN113703419A CN202110905196.9A CN202110905196A CN113703419A CN 113703419 A CN113703419 A CN 113703419A CN 202110905196 A CN202110905196 A CN 202110905196A CN 113703419 A CN113703419 A CN 113703419A
- Authority
- CN
- China
- Prior art keywords
- value
- channel
- control system
- flight control
- monitoring
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Pending
Links
- RZVHIXYEVGDQDX-UHFFFAOYSA-N 9,10-anthraquinone Chemical compound C1=CC=C2C(=O)C3=CC=CC=C3C(=O)C2=C1 RZVHIXYEVGDQDX-UHFFFAOYSA-N 0.000 title claims abstract description 119
- 238000012360 testing method Methods 0.000 title claims abstract description 76
- 238000012544 monitoring process Methods 0.000 claims description 141
- 238000011084 recovery Methods 0.000 claims description 23
- 238000000034 method Methods 0.000 claims description 19
- 230000008859 change Effects 0.000 claims description 10
- 238000013459 approach Methods 0.000 claims description 5
- XEEYBQQBJWHFJM-UHFFFAOYSA-N Iron Chemical compound [Fe] XEEYBQQBJWHFJM-UHFFFAOYSA-N 0.000 description 8
- 238000010998 test method Methods 0.000 description 8
- 229910052742 iron Inorganic materials 0.000 description 4
- 230000004044 response Effects 0.000 description 4
- 230000001052 transient effect Effects 0.000 description 4
- 238000004590 computer program Methods 0.000 description 3
- 230000006870 function Effects 0.000 description 3
- 238000010586 diagram Methods 0.000 description 2
- 230000008569 process Effects 0.000 description 2
- 230000015572 biosynthetic process Effects 0.000 description 1
- 238000009529 body temperature measurement Methods 0.000 description 1
- 238000013461 design Methods 0.000 description 1
- 238000001514 detection method Methods 0.000 description 1
- 238000002955 isolation Methods 0.000 description 1
- 238000012545 processing Methods 0.000 description 1
- 238000004088 simulation Methods 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
- 238000003786 synthesis reaction Methods 0.000 description 1
Images
Classifications
-
- G—PHYSICS
- G05—CONTROLLING; REGULATING
- G05B—CONTROL OR REGULATING SYSTEMS IN GENERAL; FUNCTIONAL ELEMENTS OF SUCH SYSTEMS; MONITORING OR TESTING ARRANGEMENTS FOR SUCH SYSTEMS OR ELEMENTS
- G05B23/00—Testing or monitoring of control systems or parts thereof
- G05B23/02—Electric testing or monitoring
- G05B23/0205—Electric testing or monitoring by means of a monitoring system capable of detecting and responding to faults
- G05B23/0208—Electric testing or monitoring by means of a monitoring system capable of detecting and responding to faults characterized by the configuration of the monitoring system
- G05B23/0213—Modular or universal configuration of the monitoring system, e.g. monitoring system having modules that may be combined to build monitoring program; monitoring system that can be applied to legacy systems; adaptable monitoring system; using different communication protocols
-
- G—PHYSICS
- G05—CONTROLLING; REGULATING
- G05B—CONTROL OR REGULATING SYSTEMS IN GENERAL; FUNCTIONAL ELEMENTS OF SUCH SYSTEMS; MONITORING OR TESTING ARRANGEMENTS FOR SUCH SYSTEMS OR ELEMENTS
- G05B2219/00—Program-control systems
- G05B2219/20—Pc systems
- G05B2219/24—Pc safety
- G05B2219/24065—Real time diagnostics
Abstract
The application provides an automatic testing method of a redundancy management algorithm of a flight control system, which comprises the following steps: acquiring a channel value of each channel in the redundancy input signal; obtaining an output voting value of the flight control system under the redundancy input signal; and comparing the ideal voting value of the channel value of each channel of the redundancy input signal under the voting algorithm with the output voting value of the flight control system, judging that the redundancy voting algorithm of the flight control system is correct when the difference value of the output voting value and the ideal voting value is within a preset range, and judging that the redundancy voting algorithm of the flight control system is wrong if the difference value is not within the preset range.
Description
Technical Field
The application belongs to the technical field of aeroengine temperature measurement, and particularly relates to an automatic testing method and device for a redundancy management algorithm of a flight control system.
Background
The flight control system usually adopts redundancy design, uses the part (group) hardware with low reliability, and implements the functions of working state detection, fault isolation, fault declaration and the like of redundancy information by performing an effective redundancy management strategy on the software and hardware resources of the multiple configuration system, so as to solve each item of processing of effective work of the redundancy channel, thereby improving the task completion rate of the system, reducing the failure rate of the system, and realizing the effective promotion of the integrity and attendance rate of the whole airplane.
The redundancy management strategy generally comprises a voting algorithm, a monitoring algorithm (monitoring result output, monitoring results can be obtained through a time threshold and an amplitude threshold), fault synthesis and declaration, fault recovery and the like, the traditional model is tested through a semi-physical simulation iron bird test environment, a test case is manually input, after the manual monitoring test is completed, the record is carried out, a test data curve is drawn to check whether the redundancy management function is correct, and due to the fact that the requirement change or software implementation is different from the requirement, multiple regression tests are required to be carried out on the same test content, the test is time-consuming and labor-consuming, and the repeatable execution performance is avoided.
Disclosure of Invention
The present application is directed to a method and apparatus for automatically testing a redundancy management algorithm of a row control system, so as to solve or mitigate at least one of the problems of the background art.
In a first aspect, the technical solution of the present application is: an automatic testing method for a flight control system redundancy management algorithm, the automatic testing method comprising:
acquiring a channel value of each channel in the redundancy input signal;
obtaining an output voting value of the flight control system under the redundancy input signal;
and comparing the ideal voting value of the channel value of each channel of the redundancy input signal under the voting algorithm with the output voting value of the flight control system, judging that the redundancy voting algorithm of the flight control system is correct when the difference value of the output voting value and the ideal voting value is within a preset range, and judging that the redundancy voting algorithm of the flight control system is wrong if the difference value is not within the preset range.
Further, the method also comprises the following steps:
acquiring a channel value and an auxiliary judgment parameter of each channel in the redundancy input signal;
acquiring a monitoring value of the flight control system under the redundancy input signal and the auxiliary judgment parameter;
and comparing the channel value of the redundancy input signal and an ideal monitoring value of the auxiliary judgment parameter under the fault monitoring algorithm with a monitoring value output by the flight control system, judging that the fault monitoring algorithm of the flight control system is correct when the monitoring value output by the flight control system is the same as the ideal monitoring value, and otherwise, judging that the fault monitoring algorithm of the flight control system is wrong.
Further, the method also comprises the following steps:
acquiring a channel value of each channel in the redundancy input signal, and forming step out-of-tolerance in at least any one channel;
acquiring an output channel value and an output voting value of a flight control system under the channel value of a redundancy input signal with step out-of-tolerance formed in at least any one channel;
and judging the change time of the channel value and the voting value output by the flight control system, if the difference between the two times is within a specified error allowable range, judging that the monitoring time threshold of the flight control system is correct, otherwise, judging that the monitoring time threshold of the flight control system is wrong.
Further, the method also comprises the following steps:
acquiring a channel value of each channel in the redundancy input signal, and enabling the difference value between the channel values to be close to the amplitude threshold and not exceed the amplitude threshold;
acquiring a first monitoring amplitude value of a flight control system under a redundancy input signal, wherein the difference value of channel values is close to an amplitude threshold and is not out of tolerance, and the first monitoring amplitude value is normal;
making the difference between the channel values of the redundancy input signal exceed the amplitude threshold;
acquiring a second monitoring amplitude of the flight control system under the redundancy input signal of which the difference value between the channel values slightly exceeds an amplitude threshold;
and when the flight control system outputs an out-of-tolerance channel monitoring fault and a second monitoring amplitude threshold output by the flight control system is between the approach amplitude threshold value and the slightly-exceeding amplitude threshold value, judging that the monitoring amplitude threshold algorithm of the flight management system is correct, otherwise, judging that the monitoring amplitude threshold algorithm of the flight management system is wrong.
Further, the method also comprises the following steps:
acquiring a channel value of each channel in the redundancy input signal, and enabling a preset fault type to occur in at least one channel;
when the flight control system declares a preset fault type, enabling the channel with the preset fault type to be recovered to be normal;
acquiring an output monitoring value of a flight management system under a redundancy input signal of a channel recovering to be normal;
and if the output monitoring value of the flight management system is recovered to be normal, judging that the fault recovery algorithm of the flight management system is correct, otherwise, judging that the fault recovery algorithm of the flight management system is wrong.
In a second aspect, the present application provides the following technical solutions: an automatic testing device for redundancy management algorithm of a flight control system comprises a monitoring voting algorithm judging module, wherein the monitoring voting algorithm judging module executes the following steps:
acquiring a channel value of each channel in the redundancy input signal;
obtaining an output voting value of the flight control system under the redundancy input signal;
and comparing the ideal voting value of the channel value of each channel of the redundancy input signal under the voting algorithm with the output voting value of the flight control system, judging that the redundancy voting algorithm of the flight control system is correct when the difference value of the output voting value and the ideal voting value is within a preset range, and judging that the redundancy voting algorithm of the flight control system is wrong if the difference value is not within the preset range.
Further, the system also comprises a fault monitoring algorithm judging module, wherein the fault monitoring algorithm judging module executes the following steps:
acquiring a channel value and an auxiliary judgment parameter of each channel in the redundancy input signal;
acquiring a monitoring value of the flight control system under the redundancy input signal and the auxiliary judgment parameter;
and comparing the channel value of the redundancy input signal and an ideal monitoring value of the auxiliary judgment parameter under the fault monitoring algorithm with a monitoring value output by the flight control system, judging that the fault monitoring algorithm of the flight control system is correct when the monitoring value output by the flight control system is the same as the ideal monitoring value, and otherwise, judging that the fault monitoring algorithm of the flight control system is wrong.
Further, the system also comprises a time threshold algorithm judging module, wherein the time threshold algorithm judging module executes the following steps:
acquiring a channel value of each channel in the redundancy input signal, and forming step out-of-tolerance in at least any one channel;
acquiring an output channel value and an output voting value of a flight control system under the channel value of a redundancy input signal with step out-of-tolerance formed in at least any one channel;
and judging the change time of the channel value and the voting value output by the flight control system, if the difference between the two times is within a specified error allowable range, judging that the monitoring time threshold of the flight control system is correct, otherwise, judging that the monitoring time threshold of the flight control system is wrong.
Further, the method also comprises an amplitude threshold algorithm judging module, wherein the amplitude threshold algorithm judging module executes the following steps:
acquiring a channel value of each channel in the redundancy input signal, and enabling the difference value between the channel values to be close to the amplitude threshold and not exceed the amplitude threshold;
acquiring a first monitoring amplitude value of a flight control system under a redundancy input signal, wherein the difference value of channel values is close to an amplitude threshold and is not out of tolerance, and the first monitoring amplitude value is normal;
making the difference between the channel values of the redundancy input signal exceed the amplitude threshold;
acquiring a second monitoring amplitude of the flight control system under the redundancy input signal of which the difference value between the channel values slightly exceeds an amplitude threshold;
and when the flight control system outputs an out-of-tolerance channel monitoring fault and a second monitoring amplitude threshold output by the flight control system is between the approach amplitude threshold value and the slightly-exceeding amplitude threshold value, judging that the monitoring amplitude threshold algorithm of the flight management system is correct, otherwise, judging that the monitoring amplitude threshold algorithm of the flight management system is wrong.
Further, the system also comprises a fault recovery algorithm judging module, wherein the fault recovery algorithm judging module executes the following steps:
acquiring a channel value of each channel in the redundancy input signal, and enabling a preset fault type to occur in at least one channel;
when the flight control system declares a preset fault type, enabling the channel with the preset fault type to be recovered to be normal;
acquiring an output monitoring value of a flight management system under a redundancy input signal of a channel recovering to be normal;
and if the output monitoring value of the flight management system is recovered to be normal, judging that the fault recovery algorithm of the flight management system is correct, otherwise, judging that the fault recovery algorithm of the flight management system is wrong.
The automatic test method and the device provided by the application can realize the following advantages:
1) the automatic testing method is the same as the manual testing principle and method, the correctness of the testing method is ensured, and the data is input through the set redundancy, so that the response of the monitoring algorithm to the fault transient state is fully tested whether to be correct or not in a very short time with different requirements;
2) in the conventional type iron bird test, a manual test mode is adopted, the input data is set to the output data record, and whether the result is correct or not is analyzed in a manual mode, one test case needs several minutes for completion, the automatic test only needs hundreds of millimeters, the time of one to two weeks is needed for the whole redundancy management test, and the automatic test can be completed only several hours;
3) each step of the manual test mode needs manual operation, and the automatic test can be automatically executed by one key and pop up a test result only by clicking to start the test after selecting a test case, so that the test is convenient and quick;
4) the manual testing method has poor repeatability, the original manual work needs to be manually executed again once again after software is changed or when the same test is carried out on different computers, time and labor are wasted, and the condition of manual setting for many times cannot be ensured to be completely consistent; the automatic testing method has strong repeatability, can ensure consistent state no matter how many times of tests are executed, and saves more labor and time as the testing times are more.
Drawings
In order to more clearly illustrate the technical solutions provided by the present application, the following briefly introduces the accompanying drawings. It is to be expressly understood that the drawings described below are only illustrative of some embodiments of the invention.
Fig. 1 is a general schematic diagram of an automatic test method according to the present application.
Fig. 2 is a schematic diagram of the automatic testing apparatus according to the present application.
Detailed Description
In order to make the implementation objects, technical solutions and advantages of the present application clearer, the technical solutions in the embodiments of the present application will be described in more detail below with reference to the drawings in the embodiments of the present application.
The invention provides an automatic test method of a redundancy management algorithm of a flight control system, which mainly comprises the steps of judging whether a monitoring voting algorithm in the redundancy management algorithm is correct, judging whether a fault monitoring/reporting algorithm is correct, judging whether a monitored time threshold algorithm is correct, judging whether a monitored amplitude threshold algorithm is correct and judging whether a fault recovery algorithm is correct, thereby realizing the automatic reading and writing of input and output information of redundancy signals of a flight management computer in the flight control system and completing the test of the redundancy management function
Specifically, as shown in fig. 1, the automatic testing method includes:
monitoring voting algorithm
And acquiring the channel value of each channel in the redundancy input signal, reading the voting value output by the flight management computer, comparing, and judging that the monitoring voting algorithm is correct if the result is within the allowable error range, or judging that the monitoring voting algorithm is wrong.
In the process of outputting the aircraft attack angle, for example, firstly, the channel values of the attack angle are obtained through the attack angle sensors arranged on two sides of the aircraft nose, and then, the voting values of the attack angle are obtained through voting the two channel values, so that the use of the attack angle data is realized.
For example, the channel angle of attack value in a redundant input signal is 10 °, the other channel angle of attack value is 12 °, and the voting algorithm is
(x1 and x2 are channel values), if the attack angle value voted by the flight control computer is 11 degrees, the voting algorithm is compared with the expected value of 11 degrees +/-0.1 degrees of the voting algorithm and falls within an allowable range, and therefore the voting algorithm of the attack angle is judged to be correct; and if the voted angle of attack value of the flight control computer is 11.5 degrees, and the voted angle of attack value does not belong to the allowable range, judging that the voting algorithm of the angle of attack in the flight control computer is wrong.
Second, fault monitoring algorithm
Acquiring a channel value and other auxiliary input parameters (the auxiliary input parameters can be landing gear retraction signals and speed signals, for example) of each channel in the redundancy input signals, reading a monitoring result output by the flight tube computer under the redundancy input signals, comparing the monitoring result with an expected value, if the output monitoring result is the same as or consistent with the expected value, judging that the monitoring result and the fault monitoring algorithm are correct, otherwise, judging that the monitoring result and the fault monitoring algorithm are wrong.
For example, in the above determination process, one channel in the redundancy input signal is failed, the other channel is normal, and in addition, the expected value should be determined by the fault monitoring algorithm through the auxiliary parameter. When the flight tube computer accurately judges that one channel is in fault and the other channel is normal under the redundancy input signals and the auxiliary parameters, and the fault monitoring algorithm is correct if the fault monitoring algorithm is consistent with the expected value, otherwise, the fault monitoring algorithm is wrong.
Three, time threshold algorithm
Acquiring a channel value of a redundancy input signal, setting the over-difference of one or two channels in a large-order mode, reading the channel value and the voting value output by the flight management computer under the redundancy input signal, recording the time of the change of the channel value and the change of the voting value of the flight management computer, judging that the monitoring time threshold is correct when the time difference is within a specified error allowable range, and judging that the monitoring time threshold is wrong if the time difference is not within the specified error allowable range.
Four, amplitude threshold algorithm
Acquiring channel values of a redundancy input signal, and firstly setting a difference value between the channel values to be close to an amplitude threshold and not exceed the amplitude threshold;
reading the monitoring result output by the computer to be normal, and then setting the channel out-of-tolerance and the difference value between the channel values to slightly exceed the amplitude threshold;
reading the monitoring result output by the computer again and outputting the channel monitoring fault with the out-of-tolerance, if the output result is consistent with the expectation, indicating that the monitoring amplitude threshold is between the set approximate amplitude threshold value and the slightly-exceeding amplitude threshold value, judging that the monitoring amplitude threshold is correct, otherwise, judging that the monitoring amplitude threshold is wrong;
fifth, failure recovery algorithm
Acquiring a channel value of a redundancy input signal, setting corresponding fault types of test data of the channel value, setting the test data of the redundancy input signal to be normal after the flight management computer declares a fault, reading whether a corresponding monitoring result output by the flight management computer is normal or not, if so, testing the correctness of a fault recovery algorithm, otherwise, testing the mistake; and then, sending a fault recovery instruction, reading whether the corresponding monitoring result output by the flight management computer is recovered to be normal or not, if so, judging that the artificial fault recovery algorithm is correct, otherwise, judging that the artificial fault recovery algorithm is wrong.
In addition, as shown in fig. 2, the present application further provides an automatic testing device for a redundancy management algorithm of a flight control system, where the automatic testing device includes a monitoring voting algorithm determining module 101, and the monitoring voting algorithm determining module 101 executes the following steps:
acquiring a channel value of each channel in the redundancy input signal;
obtaining an output voting value of the flight control system under the redundancy input signal;
and comparing the ideal voting value of the channel value of each channel of the redundancy input signal under the voting algorithm with the output voting value of the flight control system, judging that the redundancy voting algorithm of the flight control system is correct when the difference value of the output voting value and the ideal voting value is within a preset range, and judging that the redundancy voting algorithm of the flight control system is wrong if the difference value is not within the preset range.
Further, the system further comprises a fault monitoring algorithm judging module 102, wherein the fault monitoring algorithm judging module 102 executes the following steps:
acquiring a channel value and an auxiliary judgment parameter of each channel in the redundancy input signal;
acquiring a monitoring value of the flight control system under the redundancy input signal and the auxiliary judgment parameter;
and comparing the channel value of the redundancy input signal and an ideal monitoring value of the auxiliary judgment parameter under the fault monitoring algorithm with a monitoring value output by the flight control system, judging that the fault monitoring algorithm of the flight control system is correct when the monitoring value output by the flight control system is the same as the ideal monitoring value, and otherwise, judging that the fault monitoring algorithm of the flight control system is wrong.
Further, the method further comprises a time threshold algorithm judging module 103, wherein the time threshold algorithm judging module 103 executes the following steps:
acquiring a channel value of each channel in the redundancy input signal, and forming step out-of-tolerance in at least any one channel;
acquiring an output channel value and an output voting value of a flight control system under the channel value of a redundancy input signal with step out-of-tolerance formed in at least any one channel;
and judging the change time of the channel value and the voting value output by the flight control system, if the difference between the two times is within a specified error allowable range, judging that the monitoring time threshold of the flight control system is correct, otherwise, judging that the monitoring time threshold of the flight control system is wrong.
Further, the method further includes an amplitude threshold algorithm determining module 104, where the amplitude threshold algorithm determining module 104 performs the following steps:
acquiring a channel value of each channel in the redundancy input signal, and enabling the difference value between the channel values to be close to the amplitude threshold and not exceed the amplitude threshold;
acquiring a first monitoring amplitude value of a flight control system under a redundancy input signal, wherein the difference value of channel values is close to an amplitude threshold and is not out of tolerance, and the first monitoring amplitude value is normal;
making the difference between the channel values of the redundancy input signal exceed the amplitude threshold;
acquiring a second monitoring amplitude of the flight control system under the redundancy input signal of which the difference value between the channel values slightly exceeds an amplitude threshold;
and when the flight control system outputs an out-of-tolerance channel monitoring fault and a second monitoring amplitude threshold output by the flight control system is between the approach amplitude threshold value and the slightly-exceeding amplitude threshold value, judging that the monitoring amplitude threshold algorithm of the flight management system is correct, otherwise, judging that the monitoring amplitude threshold algorithm of the flight management system is wrong.
Further, the method further comprises a fault recovery algorithm judging module 105, wherein the fault recovery algorithm judging module 105 executes the following steps:
acquiring a channel value of each channel in the redundancy input signal, and enabling a preset fault type to occur in at least one channel;
when the flight control system declares a preset fault type, enabling the channel with the preset fault type to be recovered to be normal;
acquiring an output monitoring value of a flight management system under a redundancy input signal of a channel recovering to be normal;
and if the output monitoring value of the flight management system is recovered to be normal, judging that the fault recovery algorithm of the flight management system is correct, otherwise, judging that the fault recovery algorithm of the flight management system is wrong.
In addition, the present application also provides a computer device, including: a processor; a memory; and a computer program stored on the memory and executable on the processor; the computer program, when executed by the processor, implements the steps of the method for automatic testing of a flight control system redundancy management algorithm described above.
Finally, a computer-readable storage medium is provided, on which a computer program is stored, which, when being executed by a processor, carries out the steps of the method for automatic testing of a flight control system redundancy management algorithm according to any one of the preceding claims.
The automatic test method and the device provided by the invention have the following advantages:
1) the method is the same as a manual test principle and a manual test method, the correctness of the test method is ensured, the input data can be set to change with different requirements within a very short time through the automatic test method, and whether the response of the monitoring algorithm to the fault transient state is correct or not is fully tested;
2) in the conventional type iron bird test, a manual test mode is adopted, the input data is set to the output data record, and whether the result is correct or not is analyzed in a manual mode, one test case needs several minutes for completion, the automatic test only needs hundreds of millimeters, the time of one to two weeks is needed for the whole redundancy management test, and the automatic test can be completed only several hours;
the time for manually setting two changes of data is usually more than the second level due to the limitation of human response time during the manual test of the traditional model iron bird test, the input data can be set to change with different requirements within a very short time through an automatic test method, various fault transient conditions can be accurately set, and whether the response of a monitoring algorithm to a fault transient is correct or not is fully tested.
3) Each step of the manual test mode needs manual operation, and the automatic test can be automatically executed by one key and pop up a test result only by clicking to start the test after selecting a test case, so that the test is convenient and quick;
4) the manual testing method has poor repeatability, the original manual work needs to be manually executed again once again after software is changed or when the same test is carried out on different computers, time and labor are wasted, and the condition of manual setting for many times cannot be ensured to be completely consistent; the automatic testing method has strong repeatability, can ensure consistent state no matter how many times of tests are executed, and saves more labor and time as the testing times are more.
The above description is only for the specific embodiments of the present application, but the scope of the present application is not limited thereto, and any changes or substitutions that can be easily conceived by those skilled in the art within the technical scope of the present application should be covered within the scope of the present application. Therefore, the protection scope of the present application shall be subject to the protection scope of the claims.
Claims (10)
1. An automatic testing method for a redundancy management algorithm of a flight control system is characterized by comprising the following steps:
acquiring a channel value of each channel in the redundancy input signal;
obtaining an output voting value of the flight control system under the redundancy input signal;
and comparing the ideal voting value of the channel value of each channel of the redundancy input signal under the voting algorithm with the output voting value of the flight control system, judging that the redundancy voting algorithm of the flight control system is correct when the difference value of the output voting value and the ideal voting value is within a preset range, and judging that the redundancy voting algorithm of the flight control system is wrong if the difference value is not within the preset range.
2. The method for automatic testing of flight control system redundancy management algorithms of claim 1, further comprising:
acquiring a channel value and an auxiliary judgment parameter of each channel in the redundancy input signal;
acquiring a monitoring value of the flight control system under the redundancy input signal and the auxiliary judgment parameter;
and comparing the channel value of the redundancy input signal and an ideal monitoring value of the auxiliary judgment parameter under the fault monitoring algorithm with a monitoring value output by the flight control system, judging that the fault monitoring algorithm of the flight control system is correct when the monitoring value output by the flight control system is the same as the ideal monitoring value, and otherwise, judging that the fault monitoring algorithm of the flight control system is wrong.
3. The method for automatic testing of flight control system redundancy management algorithms of claim 2, further comprising:
acquiring a channel value of each channel in the redundancy input signal, and forming step out-of-tolerance in at least any one channel;
acquiring an output channel value and an output voting value of a flight control system under the channel value of a redundancy input signal with step out-of-tolerance formed in at least any one channel;
and judging the change time of the channel value and the voting value output by the flight control system, if the difference between the two times is within a specified error allowable range, judging that the monitoring time threshold of the flight control system is correct, otherwise, judging that the monitoring time threshold of the flight control system is wrong.
4. The method for automatic testing of flight control system redundancy management algorithms of claim 3, further comprising:
acquiring a channel value of each channel in the redundancy input signal, and enabling the difference value between the channel values to be close to the amplitude threshold and not exceed the amplitude threshold;
acquiring a first monitoring amplitude value of a flight control system under a redundancy input signal, wherein the difference value of channel values is close to an amplitude threshold and is not out of tolerance, and the first monitoring amplitude value is normal;
making the difference between the channel values of the redundancy input signal exceed the amplitude threshold;
acquiring a second monitoring amplitude of the flight control system under the redundancy input signal of which the difference value between the channel values slightly exceeds an amplitude threshold;
and when the flight control system outputs an out-of-tolerance channel monitoring fault and a second monitoring amplitude threshold output by the flight control system is between the approach amplitude threshold value and the slightly-exceeding amplitude threshold value, judging that the monitoring amplitude threshold algorithm of the flight management system is correct, otherwise, judging that the monitoring amplitude threshold algorithm of the flight management system is wrong.
5. The method for automatic testing of flight control system redundancy management algorithms of claim 4, further comprising:
acquiring a channel value of each channel in the redundancy input signal, and enabling a preset fault type to occur in at least one channel;
when the flight control system declares a preset fault type, enabling the channel with the preset fault type to be recovered to be normal;
acquiring an output monitoring value of a flight management system under a redundancy input signal of a channel recovering to be normal;
and if the output monitoring value of the flight management system is recovered to be normal, judging that the fault recovery algorithm of the flight management system is correct, otherwise, judging that the fault recovery algorithm of the flight management system is wrong.
6. The automatic testing device for the redundancy management algorithm of the flight control system is characterized by comprising a monitoring voting algorithm judging module, wherein the monitoring voting algorithm judging module executes the following steps:
acquiring a channel value of each channel in the redundancy input signal;
obtaining an output voting value of the flight control system under the redundancy input signal;
and comparing the ideal voting value of the channel value of each channel of the redundancy input signal under the voting algorithm with the output voting value of the flight control system, judging that the redundancy voting algorithm of the flight control system is correct when the difference value of the output voting value and the ideal voting value is within a preset range, and judging that the redundancy voting algorithm of the flight control system is wrong if the difference value is not within the preset range.
7. The automatic testing apparatus of a flight control system redundancy management algorithm of claim 6, further comprising a fault monitoring algorithm determination module, the fault monitoring algorithm determination module performing the steps of:
acquiring a channel value and an auxiliary judgment parameter of each channel in the redundancy input signal;
acquiring a monitoring value of the flight control system under the redundancy input signal and the auxiliary judgment parameter;
and comparing the channel value of the redundancy input signal and an ideal monitoring value of the auxiliary judgment parameter under the fault monitoring algorithm with a monitoring value output by the flight control system, judging that the fault monitoring algorithm of the flight control system is correct when the monitoring value output by the flight control system is the same as the ideal monitoring value, and otherwise, judging that the fault monitoring algorithm of the flight control system is wrong.
8. The apparatus for automatic testing of flight control system redundancy management algorithms of claim 7, further comprising a time threshold algorithm determination module, said time threshold algorithm determination module performing the steps of:
acquiring a channel value of each channel in the redundancy input signal, and forming step out-of-tolerance in at least any one channel;
acquiring an output channel value and an output voting value of a flight control system under the channel value of a redundancy input signal with step out-of-tolerance formed in at least any one channel;
and judging the change time of the channel value and the voting value output by the flight control system, if the difference between the two times is within a specified error allowable range, judging that the monitoring time threshold of the flight control system is correct, otherwise, judging that the monitoring time threshold of the flight control system is wrong.
9. The automatic testing apparatus of a flight control system redundancy management algorithm of claim 8, further comprising an amplitude threshold algorithm determination module, the amplitude threshold algorithm determination module performing the steps of:
acquiring a channel value of each channel in the redundancy input signal, and enabling the difference value between the channel values to be close to the amplitude threshold and not exceed the amplitude threshold;
acquiring a first monitoring amplitude value of a flight control system under a redundancy input signal, wherein the difference value of channel values is close to an amplitude threshold and is not out of tolerance, and the first monitoring amplitude value is normal;
making the difference between the channel values of the redundancy input signal exceed the amplitude threshold;
acquiring a second monitoring amplitude of the flight control system under the redundancy input signal of which the difference value between the channel values slightly exceeds an amplitude threshold;
and when the flight control system outputs an out-of-tolerance channel monitoring fault and a second monitoring amplitude threshold output by the flight control system is between the approach amplitude threshold value and the slightly-exceeding amplitude threshold value, judging that the monitoring amplitude threshold algorithm of the flight management system is correct, otherwise, judging that the monitoring amplitude threshold algorithm of the flight management system is wrong.
10. The automatic test equipment for a flight control system redundancy management algorithm of claim 9, further comprising a fault recovery algorithm determination module, the fault recovery algorithm determination module performing the steps of:
acquiring a channel value of each channel in the redundancy input signal, and enabling a preset fault type to occur in at least one channel;
when the flight control system declares a preset fault type, enabling the channel with the preset fault type to be recovered to be normal;
acquiring an output monitoring value of a flight management system under a redundancy input signal of a channel recovering to be normal;
and if the output monitoring value of the flight management system is recovered to be normal, judging that the fault recovery algorithm of the flight management system is correct, otherwise, judging that the fault recovery algorithm of the flight management system is wrong.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110905196.9A CN113703419A (en) | 2021-08-08 | 2021-08-08 | Automatic testing method and device for redundancy management algorithm of flight control system |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110905196.9A CN113703419A (en) | 2021-08-08 | 2021-08-08 | Automatic testing method and device for redundancy management algorithm of flight control system |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN113703419A true CN113703419A (en) | 2021-11-26 |
Family
ID=78651817
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202110905196.9A Pending CN113703419A (en) | 2021-08-08 | 2021-08-08 | Automatic testing method and device for redundancy management algorithm of flight control system |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN113703419A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN116909123A (en) * | 2023-09-15 | 2023-10-20 | 西北工业大学 | Self-monitoring method for motor controller of aviation dual-redundancy electromechanical actuating system |
Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101916090A (en) * | 2010-07-14 | 2010-12-15 | 北京航空航天大学 | Unmanned aerial vehicle onboard three-redundancy electrical load management center |
| CN203350711U (en) * | 2013-01-29 | 2013-12-18 | 中国航空工业集团公司西安飞机设计研究所 | Closed loop type pre-flight self-detection system |
| CN104677360A (en) * | 2015-03-09 | 2015-06-03 | 中国航空工业集团公司沈阳飞机设计研究所 | Redundancy management algorithm for attitude and course angles |
| CN106773791A (en) * | 2017-01-16 | 2017-05-31 | 万微微 | A kind of flight control system experimental rig |
| KR20180083531A (en) * | 2017-01-13 | 2018-07-23 | 한국전자통신연구원 | Test automation system and test automation method for satellite control software |
| CN110488630A (en) * | 2019-07-15 | 2019-11-22 | 中国人民解放军第五七二一工厂 | A kind of control increases steady flight control computer test macro and test method |
| CN110844119A (en) * | 2018-11-30 | 2020-02-28 | 中国航空工业集团公司沈阳飞机设计研究所 | Aircraft attack angle voting method |
-
2021
- 2021-08-08 CN CN202110905196.9A patent/CN113703419A/en active Pending
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101916090A (en) * | 2010-07-14 | 2010-12-15 | 北京航空航天大学 | Unmanned aerial vehicle onboard three-redundancy electrical load management center |
| CN203350711U (en) * | 2013-01-29 | 2013-12-18 | 中国航空工业集团公司西安飞机设计研究所 | Closed loop type pre-flight self-detection system |
| CN104677360A (en) * | 2015-03-09 | 2015-06-03 | 中国航空工业集团公司沈阳飞机设计研究所 | Redundancy management algorithm for attitude and course angles |
| KR20180083531A (en) * | 2017-01-13 | 2018-07-23 | 한국전자통신연구원 | Test automation system and test automation method for satellite control software |
| CN106773791A (en) * | 2017-01-16 | 2017-05-31 | 万微微 | A kind of flight control system experimental rig |
| CN110844119A (en) * | 2018-11-30 | 2020-02-28 | 中国航空工业集团公司沈阳飞机设计研究所 | Aircraft attack angle voting method |
| CN110488630A (en) * | 2019-07-15 | 2019-11-22 | 中国人民解放军第五七二一工厂 | A kind of control increases steady flight control computer test macro and test method |
Non-Patent Citations (3)
| Title |
|---|
| 吴永亮;蔡亚男;宝音贺西;熊立川;刘盛川;: "临近空间无人飞行器多余度容错导航系统设计", 航空学报, no. 1 * |
| 王冠珺，周文雅，曾庆华，张大力: "四余度飞控余度管理算法与验证", 《机械设计》, vol. 37, pages 39 - 42 * |
| 王永国;呼明亮;王凌伟;何文静;: "基于模型驱动的四余度信号表决系统设计", 航空计算技术, no. 06 * |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN116909123A (en) * | 2023-09-15 | 2023-10-20 | 西北工业大学 | Self-monitoring method for motor controller of aviation dual-redundancy electromechanical actuating system |
| CN116909123B (en) * | 2023-09-15 | 2023-12-19 | 西北工业大学 | Self-monitoring method for motor controller of aviation dual-redundancy electromechanical actuating system |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| JP7438205B2 (en) | Parametric data modeling for model-based reasoners | |
| CN110488630B (en) | Test system and test method for controlling stability-increasing flight control computer | |
| CN104569794A (en) | FPGA on-line tester based on boundary scan structure and testing method thereof | |
| US10120785B2 (en) | Automatic generation of data coupling and control coupling test conditions | |
| CN106647701A (en) | Aero-engine controller BIT (Built-In Testing) method | |
| CN102930081A (en) | Built-in testing design method based on relevance model | |
| CN113703419A (en) | Automatic testing method and device for redundancy management algorithm of flight control system | |
| KR101042979B1 (en) | Simulation Kernel-based Simulation Fault Injection Apparatus for the Evaluation of the Dependability of Embedded Systems | |
| Johnson et al. | Design for validation | |
| CN110567485B (en) | On-orbit autonomous fault diagnosis and repair method for multi-probe star sensor | |
| EP3072046B1 (en) | Latency tolerant fault isolation | |
| KR101837899B1 (en) | Apparatus and method for diagnosing failure of scan chain | |
| CN111044826B (en) | Detection method and detection system | |
| CN209343321U (en) | A kind of computer glitch detection device | |
| CN111965609A (en) | Radar reliability evaluation method and device, electronic equipment and readable storage medium | |
| US11829229B2 (en) | Apparatus and method for diagnosing no fault failure found in electronic systems | |
| CN112712305B (en) | Aircraft system and health assessment method and device thereof | |
| CN117407207B (en) | Memory fault processing method and device, electronic equipment and storage medium | |
| US7065691B2 (en) | Apparatus and method for saving precise system state following exceptions | |
| CN113946462A (en) | Sensor system fault processing method and system for unmanned aerial vehicle cluster | |
| Zhao et al. | Radar System Testability Design and Demonstration Based on Fault Modes and Software Control | |
| Valfre | Testability modeling usage in design-for-test and product lifecycle cost reduction | |
| CN114595143A (en) | Embedded test credibility detection verification method and system for aviation communication electronic system | |
| Yeon et al. | Fault detection and diagnostic coverage for the domain control units of vehicle E/E systems on functional safety | |
| Xie et al. | Study on the application of health management techniques in aerospace testing software |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination |