CN113703419B - 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
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- G—PHYSICS
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- 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
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- 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
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Abstract
The application provides an automatic test method of a redundancy management algorithm of a flight control system, which comprises the following steps: obtaining a channel value of each channel in the redundancy input signal; obtaining an output vote value of the flight control system under the redundancy input signal; 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, and judging that the redundancy voting algorithm of the flight control system is correct when the difference value between the output voting value and the ideal voting value is within a preset range, otherwise, judging that the redundancy voting algorithm of the flight control system is wrong.
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 generally adopts redundancy design, uses parts (components) with low reliability, and realizes the functions of working state detection, fault isolation, fault reporting and the like of redundancy information by carrying out effective redundancy management strategies on software and hardware resources of the multi-configuration system so as to solve various treatments of effective work of a redundancy channel, thereby improving the task completion rate of the system, reducing the failure rate of the system and realizing the effective improvement of the integrity and attendance rate of the whole aircraft.
The redundancy management strategy generally comprises a voting algorithm, a monitoring algorithm (the monitoring result is output, the monitoring result can be obtained through a time threshold and an amplitude threshold), fault synthesis and declaration, fault recovery and the like, the previous model is tested through a semi-physical simulation iron bird test environment, test cases are manually input by people, the test cases are recorded after the manual monitoring test is finished, and whether the result is correct is checked through drawing a test data curve to check whether the redundancy management function is realized or not.
Disclosure of Invention
The application aims to provide an automatic testing method and device for a redundancy management algorithm of a row control system, which are used for solving or relieving at least one problem in the background art.
In a first aspect, the present application provides the following technical solutions: an automatic test method for a redundancy management algorithm of a flight control system, the automatic test method comprising:
obtaining a channel value of each channel in the redundancy input signal;
obtaining an output vote value of the flight control system under the redundancy input signal;
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, and judging that the redundancy voting algorithm of the flight control system is correct when the difference value between the output voting value and the ideal voting value is within a preset range, otherwise, judging that the redundancy voting algorithm of the flight control system is wrong.
Further, the method further comprises the following steps:
obtaining 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 ideal monitoring value of the redundancy input signal and the auxiliary judging parameter under the fault monitoring algorithm with the monitoring value output by the flight control system, and judging that the fault monitoring algorithm of the flight control system is correct when the monitoring value output by the flight control system is identical to the ideal monitoring value, otherwise, judging that the fault monitoring algorithm of the flight control system is wrong.
Further, the method further comprises the following steps:
obtaining a channel value of each channel in the redundancy input signal, and enabling at least any channel to form step deviation;
obtaining an output channel value and an output voting value of a flight control system under the channel value of a redundancy input signal forming step out-of-tolerance in at least any channel;
and judging the change time of the channel value and the vote value output by the flight control system, if the two time differences are within the allowable range of the specified error, 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 comprises the following steps:
Obtaining a channel value of each channel in the redundancy input signal, and enabling a difference value between the channel values to be close to an amplitude threshold and not out of tolerance;
Acquiring a first monitoring amplitude value of a flight control system under a redundancy input signal, wherein the difference value between 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 value between the channel values of the redundancy input signals exceed an amplitude threshold;
acquiring a second monitoring amplitude value of the flight control system under a redundancy input signal that the difference value between the channel values slightly exceeds an amplitude threshold;
And when the flight control system outputs out-of-tolerance channel monitoring faults, and meanwhile, a second monitoring amplitude threshold output by the flight control system is between the approaching 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 the following steps:
Obtaining a channel value of each channel in the redundancy input signal, and enabling at least one channel to generate a preset fault type;
when the flight control system declares a preset fault type, the channel with the preset fault type is recovered to be normal;
Acquiring an output monitoring value of the flight management system under a redundancy input signal for restoring the normal channel;
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 a technical solution that: an automatic testing device for a redundancy management algorithm of a flight control system, the automatic testing device comprising a monitoring voting algorithm judging module, wherein the monitoring voting algorithm judging module executes the following steps:
obtaining a channel value of each channel in the redundancy input signal;
obtaining an output vote value of the flight control system under the redundancy input signal;
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, and judging that the redundancy voting algorithm of the flight control system is correct when the difference value between the output voting value and the ideal voting value is within a preset range, otherwise, judging that the redundancy voting algorithm of the flight control system is wrong.
Further, the system also comprises a fault monitoring algorithm judging module, wherein the fault monitoring algorithm judging module executes the following steps:
obtaining 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 ideal monitoring value of the redundancy input signal and the auxiliary judging parameter under the fault monitoring algorithm with the monitoring value output by the flight control system, and judging that the fault monitoring algorithm of the flight control system is correct when the monitoring value output by the flight control system is identical to the ideal monitoring value, otherwise, judging that the fault monitoring algorithm of the flight control system is wrong.
Further, the method also comprises a time threshold algorithm judging module, wherein the time threshold algorithm judging module executes the following steps:
obtaining a channel value of each channel in the redundancy input signal, and enabling at least any channel to form step deviation;
obtaining an output channel value and an output voting value of a flight control system under the channel value of a redundancy input signal forming step out-of-tolerance in at least any channel;
and judging the change time of the channel value and the vote value output by the flight control system, if the two time differences are within the allowable range of the specified error, 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, and the amplitude threshold algorithm judging module executes the following steps:
Obtaining a channel value of each channel in the redundancy input signal, and enabling a difference value between the channel values to be close to an amplitude threshold and not out of tolerance;
Acquiring a first monitoring amplitude value of a flight control system under a redundancy input signal, wherein the difference value between 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 value between the channel values of the redundancy input signals exceed an amplitude threshold;
acquiring a second monitoring amplitude value of the flight control system under a redundancy input signal that the difference value between the channel values slightly exceeds an amplitude threshold;
And when the flight control system outputs out-of-tolerance channel monitoring faults, and meanwhile, a second monitoring amplitude threshold output by the flight control system is between the approaching 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:
Obtaining a channel value of each channel in the redundancy input signal, and enabling at least one channel to generate a preset fault type;
when the flight control system declares a preset fault type, the channel with the preset fault type is recovered to be normal;
Acquiring an output monitoring value of the flight management system under a redundancy input signal for restoring the normal channel;
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 have the following advantages:
1) The automatic test method is the same as the manual test principle and method, so that the correctness of the test method is ensured, the data can be input through the set redundancy, different requirements can be changed in extremely short time, and whether the response of the monitoring algorithm to the fault transient state is correct or not is fully tested;
2) In the prior art, a manual test mode is adopted for the iron bird test, from input data setting to output data recording, whether a result is correct or not is analyzed by a manual mode, a test case is completed in a few minutes, the automatic test only needs hundreds of millimeters, the whole redundancy management test needs one to two weeks, and the automatic test can be completed in a few hours;
3) Each step of the manual test mode is manually completed, and the automatic test can be automatically executed by clicking to start the test after the test case is selected, so that a test result can be popped up conveniently and quickly;
4) The manual testing method has poor repeatability, and the software is tested and verified again after being changed, or when the same test is carried out on different computers, the original manual work needs to be carried out again, so that time and labor are wasted, and the state of repeated manual setting cannot be ensured to be completely consistent; the automatic test method has strong repeatability, can ensure the consistent state no matter how many times of tests are executed, and saves manpower and time as the number of times of tests is increased.
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In order to more clearly illustrate the technical solution provided by the present application, the following description will briefly refer to the accompanying drawings. It will be apparent that the figures described below are merely some embodiments of the application.
FIG. 1 is a schematic diagram of an automatic test method according to the present application.
FIG. 2 is a schematic diagram of an automatic test equipment according to the present application.
Detailed Description
In order to make the objects, technical solutions and advantages of the present application become more apparent, the technical solutions in the embodiments of the present application will be described in more detail below with reference to the accompanying drawings in the embodiments of the present application.
The automatic test method of the redundancy management algorithm of the flight control system mainly comprises the steps of automatically reading and writing the input and output information of redundancy signals of a flight control computer in the flight control system to complete the test of the redundancy management function, wherein the automatic test method 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 monitoring time threshold algorithm is correct, judging whether a monitoring amplitude threshold algorithm is correct and judging whether a fault recovery algorithm is correct or not
Specifically, as shown in fig. 1, the automatic test method includes:
1. Monitoring voting algorithm
And obtaining the channel value of each channel in the redundancy input signal, reading the voting value output by the flight tube computer, comparing, and judging that the monitoring voting algorithm is correct if the result is within the allowable error range, otherwise, judging that the monitoring voting algorithm is wrong.
In the aircraft control process, a plurality of parameters are managed through redundancy, such as the output process of an aircraft attack angle, firstly an attack angle channel value is obtained through attack angle sensors arranged on two sides of an aircraft nose, and then the two channel values are voted to obtain the voting value of the attack angle, so that the use of attack angle data is realized.
For example, the channel attack angle value in a redundancy input signal is 10 DEG and the other channel attack angle value is 12 DEG, and the voting algorithm isIf the angle of attack value after the voting by the flight tube computer is 11 degrees, the angle of attack value is compared with the expected value 11 degrees plus or minus 0.1 degree of the voting algorithm and falls within the allowable range, so that the voting algorithm for judging the angle of attack is correct; if the voted attack angle value of the flight tube computer is 11.5 degrees, and the voted attack angle value is not in the allowable range, judging that the voting algorithm of the attack angle in the flight tube computer is wrong.
2. Fault monitoring algorithm
And acquiring a channel value and other auxiliary input parameters (the auxiliary input parameters can be, for example, landing gear retraction signals and meter speed signals) 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, judging that the monitoring result and a fault monitoring algorithm are correct if the output monitoring result is identical or consistent with the expected value, and otherwise, judging that the monitoring result and the fault monitoring algorithm are wrong.
For example, in the judging process, one channel in the redundancy input signal fails, the other channel is normal, and in addition, the expected value can be judged through the failure monitoring algorithm by the auxiliary parameters. When the flypipe computer accurately judges that one channel fails and the other channel is normal under the redundancy input signals and auxiliary parameters, the redundancy input signals and the auxiliary parameters are consistent with expected values, a failure monitoring algorithm in the flypipe computer is correct, and otherwise, the failure monitoring algorithm is wrong.
3. Time threshold algorithm
And obtaining the channel value of the redundancy input signal, setting one or two channels to be out of tolerance in a large-order-of-the-way mode, reading the channel value and the voting value output by the flight tube computer under the redundancy input signal, recording the time when the channel value of the flight tube computer changes and the voting value changes, judging that the monitoring time threshold is correct within the allowable range of a specified error by the time difference, and otherwise judging that the monitoring time threshold is wrong.
4. Amplitude threshold algorithm
Obtaining channel values of redundancy input signals, and firstly setting that the difference value between the channel values is close to an amplitude threshold and is not out of tolerance;
Reading that the monitoring result output by the computer is normal, and then setting the channel out of tolerance and the difference value between the channel values slightly exceeds the amplitude threshold;
Reading the monitoring result output by the computer again and outputting out-of-tolerance channel monitoring faults, if the output result is consistent with the expected value, 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;
5. fault recovery algorithm
Obtaining a channel value of the redundancy input signal, setting corresponding fault types for test data of the channel value, setting the test data of the redundancy input signal to be normal after the flyer tube computer declares a fault, reading whether a corresponding monitoring result output by the flyer tube computer is normal or not, if so, testing the correctness of a fault recovery algorithm, otherwise, making mistakes; and then, sending a fault recovery instruction, reading whether the corresponding monitoring result output by the fly tube computer is recovered to be normal, if so, correcting the manual fault recovery algorithm, otherwise, correcting the manual fault recovery algorithm.
In addition, as shown in fig. 2, the application also provides an automatic testing device for a redundancy management algorithm of a flight control system, the automatic testing device comprises a monitoring voting algorithm judging module 101, and the monitoring voting algorithm judging module 101 executes the following steps:
obtaining a channel value of each channel in the redundancy input signal;
obtaining an output vote value of the flight control system under the redundancy input signal;
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, and judging that the redundancy voting algorithm of the flight control system is correct when the difference value between the output voting value and the ideal voting value is within a preset range, otherwise, judging that the redundancy voting algorithm of the flight control system is wrong.
Further, the system further comprises a fault monitoring algorithm judging module 102, wherein the fault monitoring algorithm judging module 102 executes the following steps:
obtaining 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 ideal monitoring value of the redundancy input signal and the auxiliary judging parameter under the fault monitoring algorithm with the monitoring value output by the flight control system, and judging that the fault monitoring algorithm of the flight control system is correct when the monitoring value output by the flight control system is identical to the ideal monitoring value, 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, and the time threshold algorithm judging module 103 executes the following steps:
obtaining a channel value of each channel in the redundancy input signal, and enabling at least any channel to form step deviation;
obtaining an output channel value and an output voting value of a flight control system under the channel value of a redundancy input signal forming step out-of-tolerance in at least any channel;
and judging the change time of the channel value and the vote value output by the flight control system, if the two time differences are within the allowable range of the specified error, 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:
Obtaining a channel value of each channel in the redundancy input signal, and enabling a difference value between the channel values to be close to an amplitude threshold and not out of tolerance;
Acquiring a first monitoring amplitude value of a flight control system under a redundancy input signal, wherein the difference value between 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 value between the channel values of the redundancy input signals exceed an amplitude threshold;
acquiring a second monitoring amplitude value of the flight control system under a redundancy input signal that the difference value between the channel values slightly exceeds an amplitude threshold;
And when the flight control system outputs out-of-tolerance channel monitoring faults, and meanwhile, a second monitoring amplitude threshold output by the flight control system is between the approaching 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 judgment module 105, wherein the fault recovery algorithm judgment module 105 performs the following steps:
Obtaining a channel value of each channel in the redundancy input signal, and enabling at least one channel to generate a preset fault type;
when the flight control system declares a preset fault type, the channel with the preset fault type is recovered to be normal;
Acquiring an output monitoring value of the flight management system under a redundancy input signal for restoring the normal channel;
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 application also provides a computer device, which comprises: 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 automatic test method for the redundancy management algorithm of the flight control system described above.
Finally, the present application also provides a computer readable storage medium, on which a computer program is stored, which when executed by a processor, implements the steps of the automatic test method for a redundancy management algorithm of a flight control system according to any one of the above.
The automatic test method and the device provided by the invention have the following advantages:
1) The method has the same principle and method as the manual test, ensures the correctness of the test method, can set the input data to change in different demands in extremely short time by the automatic test method, and fully tests whether the response of the monitoring algorithm to the fault transient state is correct or not;
2) In the prior art, a manual test mode is adopted for the iron bird test, from input data setting to output data recording, whether a result is correct or not is analyzed by a manual mode, a test case is completed in a few minutes, the automatic test only needs hundreds of millimeters, the whole redundancy management test needs one to two weeks, and the automatic test can be completed in a few hours;
When the conventional model iron bird test is manually tested, because the response time of a person is limited, the time for manually setting the two changes of data is usually more than a second level, the input data can be set to change in different requirements in extremely short time by an automatic test method, various fault transient conditions can be accurately set, and whether the response of a monitoring algorithm to the fault transient is correct or not is fully tested.
3) Each step of the manual test mode is manually completed, and the automatic test can be automatically executed by clicking to start the test after the test case is selected, so that a test result can be popped up conveniently and quickly;
4) The manual testing method has poor repeatability, and the software is tested and verified again after being changed, or when the same test is carried out on different computers, the original manual work needs to be carried out again, so that time and labor are wasted, and the state of repeated manual setting cannot be ensured to be completely consistent; the automatic test method has strong repeatability, can ensure the consistent state no matter how many times of tests are executed, and saves manpower and time as the number of times of tests is increased.
The foregoing is merely illustrative of the present application, and the present application is not limited thereto, and any changes or substitutions easily contemplated by those skilled in the art within the scope of the present application should be included in the present application. Therefore, the protection scope of the present application shall be subject to the protection scope of the claims.
Claims (8)
1. An automatic test method for a redundancy management algorithm of a flight control system, the automatic test method comprising: a redundancy voting algorithm and a time threshold algorithm;
the redundancy voting algorithm comprises the following processes:
obtaining a channel value of each channel in the redundancy input signal;
obtaining an output vote value of the flight control system under the redundancy input signal;
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, and judging that the redundancy voting algorithm of the flight control system is correct when the difference value between the output voting value and the ideal voting value is within a preset range, otherwise, judging that the redundancy voting algorithm of the flight control system is wrong;
the time threshold algorithm comprises the following steps:
obtaining a channel value of each channel in the redundancy input signal, and enabling at least any channel to form step deviation;
obtaining an output channel value and an output voting value of a flight control system under the channel value of a redundancy input signal forming step out-of-tolerance in at least any channel;
and judging the change time of the channel value and the voting value output by the flight control system, if the two time differences are within the allowable range of the specified error, 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.
2. The method for automatically testing a redundancy management algorithm for a flight control system of claim 1, further comprising:
obtaining 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 ideal monitoring value of the redundancy input signal and the auxiliary judging parameter under the fault monitoring algorithm with the monitoring value output by the flight control system, and judging that the fault monitoring algorithm of the flight control system is correct when the monitoring value output by the flight control system is identical to the ideal monitoring value, otherwise, judging that the fault monitoring algorithm of the flight control system is wrong.
3. The method for automatically testing a redundancy management algorithm for a flight control system of claim 1, further comprising:
Obtaining a channel value of each channel in the redundancy input signal, and enabling a difference value between the channel values to be close to an amplitude threshold and not out of tolerance;
Acquiring a first monitoring amplitude value of a flight control system under a redundancy input signal, wherein the difference value between 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 value between the channel values of the redundancy input signals exceed an amplitude threshold;
acquiring a second monitoring amplitude value of the flight control system under a redundancy input signal that the difference value between the channel values slightly exceeds an amplitude threshold;
When the flight control system outputs out-of-tolerance channel monitoring faults, and meanwhile, a second monitoring amplitude threshold output by the flight control system is between a near amplitude threshold value and a 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.
4. The method for automatically testing a redundancy management algorithm for a flight control system of claim 3, further comprising:
Obtaining a channel value of each channel in the redundancy input signal, and enabling at least one channel to generate a preset fault type;
when the flight control system declares a preset fault type, the channel with the preset fault type is recovered to be normal;
Acquiring an output monitoring value of the flight management system under a redundancy input signal for restoring the normal channel;
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.
5. The automatic testing device for the redundancy management algorithm of the flight control system is characterized by comprising a monitoring voting algorithm judging module and a time threshold algorithm judging module, wherein the monitoring voting algorithm judging module executes the following steps:
obtaining a channel value of each channel in the redundancy input signal;
obtaining an output vote value of the flight control system under the redundancy input signal;
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, and judging that the redundancy voting algorithm of the flight control system is correct when the difference value between the output voting value and the ideal voting value is within a preset range, otherwise, judging that the redundancy voting algorithm of the flight control system is wrong;
the time threshold algorithm judging module executes the following steps:
obtaining a channel value of each channel in the redundancy input signal, and enabling at least any channel to form step deviation;
obtaining an output channel value and an output voting value of a flight control system under the channel value of a redundancy input signal forming step out-of-tolerance in at least any channel;
and judging the change time of the channel value and the vote value output by the flight control system, if the two time differences are within the allowable range of the specified error, 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.
6. The automatic test equipment for a redundancy management algorithm of a flight control system as claimed in claim 5, further comprising a fault monitoring algorithm judgment module, said fault monitoring algorithm judgment module executing the steps of:
obtaining 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 ideal monitoring value of the redundancy input signal and the auxiliary judging parameter under the fault monitoring algorithm with the monitoring value output by the flight control system, and judging that the fault monitoring algorithm of the flight control system is correct when the monitoring value output by the flight control system is identical to the ideal monitoring value, otherwise, judging that the fault monitoring algorithm of the flight control system is wrong.
7. The automatic test equipment for a redundancy management algorithm of a flight control system of claim 5, further comprising an amplitude threshold algorithm judgment module, said amplitude threshold algorithm judgment module executing the steps of:
Obtaining a channel value of each channel in the redundancy input signal, and enabling a difference value between the channel values to be close to an amplitude threshold and not out of tolerance;
Acquiring a first monitoring amplitude value of a flight control system under a redundancy input signal, wherein the difference value between 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 value between the channel values of the redundancy input signals exceed an amplitude threshold;
acquiring a second monitoring amplitude value of the flight control system under a redundancy input signal that the difference value between the channel values slightly exceeds an amplitude threshold;
When the flight control system outputs out-of-tolerance channel monitoring faults, and meanwhile, a second monitoring amplitude threshold output by the flight control system is between a near amplitude threshold value and a 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.
8. The automatic test equipment for a redundancy management algorithm of a flight control system according to claim 7, further comprising a failure recovery algorithm judgment module, said failure recovery algorithm judgment module executing the steps of:
Obtaining a channel value of each channel in the redundancy input signal, and enabling at least one channel to generate a preset fault type;
when the flight control system declares a preset fault type, the channel with the preset fault type is recovered to be normal;
Acquiring an output monitoring value of the flight management system under a redundancy input signal for restoring the normal channel;
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.
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| 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 |
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