Civil aircraft flight control system identification test method and test system

Abstract

The present invention is a civil aircraft flight control system identification test method and test system, the method comprising: according to the characteristics of multiple measured signals of the civil aircraft flight control system to be tested, selecting the types and parameters of multiple monitors corresponding thereto, the types and parameters of multiple monitors forming the test criteria for the civil aircraft flight control system identification test; defining the format of the data recording file and the post-processing test report file; conducting the identification test, recording the data and outputting the results. Before the identification test begins, the present invention selects the types and parameters of multiple monitors to form the test criteria for the identification test, providing a judgment basis for the test of the post-processing process; by defining the file formats of the data recording file and the post-processing test report, correlation is established to meet the airworthiness requirements; by recording the data of the entire identification test process, all the data are processed and evaluated using the test criteria, and the results are more complete and objective.

Description

Technical Field

[0001] The disclosed embodiments relate to the technical field of aircraft testing and data processing, and in particular to a civil aircraft flight control system identification test method and test system. Background Art

[0002] The flight control system is the core safety component of the aircraft, and the flight control system of civil aircraft is required to have a safety level of 1E-9 / FH, where FH represents flight hours. The flight control system certification test is one of the most critical development processes for civil aircraft flight control systems to demonstrate their compliance. Civil aircraft flight control systems that have passed the flight control system certification test have demonstrated high safety and reliability under various complex environmental stresses and can meet the airworthiness MC9 standard (MC9 is the equipment qualification code).

[0003] At present, the domestic flight control system identification test mainly determines whether the test is passed by manually observing the device output of the digital flight test interface (usually the discrete Fourier transform interface, Discrete Fourier Transform Interface, DFTI) and the fault light status on the flight control console, and the observation results are manually filled in the test report form. This method is based on an open-loop test system consisting of a DFTI computer and a flight control system under test. The test steps are: first, the state of the flight control system under test is set to ground or air through the wheel load switch, and the DFTI software on the DFTI computer is run to receive and display the flight data sent by the flight control system under test for testing. During the test, the DFTI data is manually observed to see if it reports a fault and whether the fault light on the flight control console is on. After the test is completed, the observation results are manually filled in the test report form.

[0004] The above test process lacks test configuration and complete data records. The test results rely on the voting results of the system's own monitor and manual observation to determine whether a fault has occurred and whether the test has passed. On the one hand, when a system fault occurs, it is necessary to determine which monitor is triggered, how much the monitor is exceeded, and what causes the system failure. The lack of complete test data is not conducive to fault analysis and system improvement. On the other hand, the test results are determined by manual observation, and there is a possibility of missing short-term intermittent faults. The test report can only record the final observed continuous faults and whether the test has passed. It does not include information such as transient faults and the duration of the fault. The test report lacks data support.

[0005] The civil aircraft flight control system identification test for airworthiness review requires that the test criteria cover all characteristic signals of the system under test, the test process data is complete, and the test conclusions are detailed, objective and credible. The current test method lacks complete test process records, there are many human factors in the test, there is a lack of sufficient objective factual basis and test process data, and the test conclusions have poor objective credibility and cannot be used as evidence for airworthiness certification.

[0006] Therefore, it is necessary to improve one or more problems existing in the above-mentioned related technical solutions.

[0007] It should be noted that this section is intended to provide background or context for the technical solutions of the present disclosure stated in the claims. The description herein is not admitted to be prior art by virtue of being included in this section. Summary of the invention

[0008] The purpose of the embodiments of the present disclosure is to provide a civil aircraft flight control system identification test method and test system, thereby overcoming one or more problems caused by the limitations and defects of related technologies at least to a certain extent.

[0009] The present disclosure first provides a civil aircraft flight control system identification test method, including:

[0010] S101, selecting and determining the types and parameters of multiple monitors corresponding to the characteristics of multiple measured signals of the flight control system of the civil aircraft to be tested, the types and parameters of the multiple monitors forming a test criterion for the identification test of the flight control system of the civil aircraft, and defining the fields of the criterion file of the test criterion;

[0011] The monitor includes: a threshold monitor, a data frame activity monitor and a CRC check monitor; the threshold monitor is used to monitor whether the data in the measured signal of the civil aircraft flight control system under test exceeds the threshold value and the number of beats required by the identification test; the data frame activity monitor is used to monitor the continuity of the data frame of the measured signal of the civil aircraft flight control system under test; the CRC check monitor is used to monitor the data integrity of the measured signal of the civil aircraft flight control system under test;

[0012] S102, defining a file format of a data recording file, wherein the data recording file is used to record data of the entire process of the identification test, and the file format of the data recording file includes: a first file naming format and a first file content format;

[0013] According to the first file naming format, the first file name includes: the test name and the bus type; according to the first file content format, the first file content includes the following items: file header information, test data, user operation and steady-state mean of the measured signal, the data of each item includes multiple data segments, and the first data segment of each item is provided with a data identifier corresponding to the item;

[0014] S103, defining a file format of a post-processing test report file, wherein the file format of the post-processing test report file includes: a second file naming format and a second file content format;

[0015] According to the second file naming format, the second file naming includes: the test name, bus type and post-processing test report file name suffix; according to the second file content format, the second file content includes the following items: file header information, test mode, user operation, steady-state mean of the measured signal, test data statistical information, evaluation results of the measured signal, test conclusion and file tail;

[0016] S104, performing an identification test on the flight control system of the civil aircraft to be tested using the test criteria, and recording data of the entire identification test process according to the file format of the data recording file;

[0017] S105, using the test criteria to process and evaluate the information in the data record file, and using a post-processing test report file to output the processing and evaluation results.

[0018] The present disclosure also provides an identification test system for a civil aircraft flight control system, which uses the above method to perform an identification test on the civil aircraft flight control system to be tested, and the test system includes:

[0019] A simulation load is used to send a first excitation signal to the flight control system of the civil aircraft to be tested so that the flight control system of the civil aircraft to be tested operates under the first excitation signal, and receive a test signal returned by the flight control system of the civil aircraft to be tested;

[0020] A real load, used for sending a second excitation signal to the flight control system of the civil aircraft to be tested so that the flight control system of the civil aircraft to be tested operates under the second excitation signal;

[0021] The controller is used to send a first excitation signal to a simulated load and receive a measured signal through the simulated load, and receive the measured signal returned by the flight control system of the civil aircraft to be tested when running under the second excitation signal; and is used to select and determine the types and parameters of multiple monitors corresponding to the multiple measured signals of the flight control system of the civil aircraft to be tested according to the characteristics of the multiple measured signals, the types and parameters of the multiple monitors form the test criteria of the civil aircraft flight control system identification test, and define the fields of the criterion file of the test criteria; define the file format of the data recording file, the data recording file is used to record the data of the entire identification test process; define the file format of the post-processing test report file; record the data of the entire identification test process according to the file format of the data recording file; use the test criteria to process and evaluate the information of the data recording file, and use the post-processing test report file to output the processing and evaluation results.

[0022] The technical solution provided by the embodiments of the present disclosure includes the following beneficial effects:

[0023] The civil aircraft flight control system identification test method and test system in the disclosed embodiment, before the identification test begins, by selecting and determining the types and parameters of multiple monitors corresponding to the characteristics of the measured signal, constitute the test criteria of the identification test, and provide a judgment basis for the test of the post-processing process; by defining the file format of the data recording file and the post-processing test report, the two are correlated and meet the airworthiness requirements; by recording the data of the entire identification test process, all the data are processed and evaluated using the test criteria, and the processing and evaluation results obtained are more complete and objective. BRIEF DESCRIPTION OF THE DRAWINGS

[0024] The accompanying drawings herein are incorporated into the specification and constitute a part of the specification, illustrate embodiments consistent with the present disclosure, and together with the specification are used to explain the principles of the present disclosure. Obviously, the accompanying drawings described below are only some embodiments of the present disclosure, and for ordinary technicians in this field, other accompanying drawings can be obtained based on these accompanying drawings without creative work.

[0025] Figure 1 A schematic diagram showing a flow chart of a civil aircraft flight control system identification test method in an exemplary embodiment of the present disclosure;

[0026] Figure 2 A model diagram of a threshold monitor in an exemplary embodiment of the present disclosure is shown;

[0027] Figure 3 A data frame activity monitor model diagram in an exemplary embodiment of the present disclosure is shown;

[0028] Figure 4 A CRC check monitor model diagram in an exemplary embodiment of the present disclosure is shown;

[0029] Figure 5 A schematic diagram showing the structure of an identification test system for a civil aircraft flight control system in an exemplary embodiment of the present disclosure;

[0030] Figure 6 A flowchart showing post-processing in an exemplary embodiment of the present disclosure;

[0031] Figure 7 Showing the content display of the data record file in the exemplary embodiment of the present disclosure;

[0032] Figure 8 Showing the content display of a data record file in yet another exemplary embodiment of the present disclosure;

[0033] Fig. 9 Showing the content display of the post-processing test report in the exemplary embodiment of the present disclosure;

[0034] Fig.10 The content display of a post-processing test report in yet another exemplary embodiment of the present disclosure is shown. DETAILED DESCRIPTION

[0035] Example embodiments will now be described more fully with reference to the accompanying drawings. However, example embodiments can be implemented in a variety of forms and should not be construed as limited to the examples set forth herein; rather, these embodiments are provided so that the disclosure will be more comprehensive and complete and to fully convey the concepts of the example embodiments to those skilled in the art. The described features, structures, or characteristics may be combined in any suitable manner in one or more embodiments.

[0036] In addition, the accompanying drawings are only schematic illustrations of the embodiments of the present disclosure and are not necessarily drawn to scale. The same reference numerals in the figures represent the same or similar parts, and their repeated descriptions will be omitted. Some of the block diagrams shown in the accompanying drawings are functional entities and do not necessarily correspond to physically or logically independent entities.

[0037] This example implementation method first provides a civil aircraft flight control system identification test method, please refer to Figure 1 , may include: Step S101-Step S105. Specifically as follows:

[0038] S101, based on the characteristics of multiple measured signals of the civil aircraft flight control system 104 to be tested, select and determine the types and parameters of multiple monitors corresponding to the characteristics, the types and parameters of the multiple monitors form the test criteria for the civil aircraft flight control system identification test, and define the fields of the criteria file of the test criteria.

[0039] Among them, the monitor includes: a threshold monitor, a data frame activity monitor and a CRC (Cyclic Redundancy Check) check monitor; the threshold monitor is used to monitor whether the data in the test signal of the civil aircraft flight control system 104 under test exceeds the threshold value and the number of beats required by the identification test; the data frame activity monitor is used to monitor the continuity of the data frame of the test signal of the civil aircraft flight control system 104 under test; the CRC check monitor is used to monitor the data integrity of the test signal of the civil aircraft flight control system 104 under test.

[0040] S102, defining a file format of a data recording file, wherein the data recording file is used to record data of the entire identification test process, and the file format of the data recording file includes: a first file naming format and a first file content format.

[0041] Among them, according to the first file naming format, the first file name includes: experimental test name and bus type; according to the first file content format, the first file content includes the following items: file header information, experimental data, user operations and steady-state mean of the measured signal, the data of each item includes multiple data segments, and the first data segment of each item is provided with a data identifier corresponding to the item.

[0042] S103, defining a file format of a post-processing test report file, wherein the file format of the post-processing test report file includes: a second file naming format and a second file content format.

[0043] Among them, according to the second file naming format, the second file naming includes: test name, bus type and post-processing test report file name suffix; according to the second file content format, the second file content includes the following items: file header information, test mode, user operation, steady-state mean of the measured signal, test data statistical information, evaluation results of the measured signal, test conclusions and file tail.

[0044] S104, performing an identification test on the flight control system 104 of the civil aircraft to be tested using the test criteria, and recording data of the entire identification test process according to the file format of the data recording file.

[0045] S105, using the test criteria to process and evaluate the information in the data record file, and using a post-processing test report file to output the processing and evaluation results.

[0046] In this embodiment, before the identification test begins, the types and parameters of multiple monitors corresponding to the characteristics of the measured signal are selected and determined to form the test criteria for the identification test, providing a judgment basis for the identification test and the post-processing test; by defining the file format of the data recording file and the post-processing test report, a correlation is established between the two and the airworthiness requirements are met; by recording the data of the entire identification test process and using the test criteria to process and evaluate all the data, the processing and evaluation results obtained are more complete and objective.

[0047] Among them, in S104, the step of performing an identification test using the test criteria includes:

[0048] Record the data of the whole process of identification test according to the file format of data recording file;

[0049] Determine whether the measured signal has entered a steady state. The identification test can only be started after entering a steady state.

[0050] The mean value of the measured signal entering the steady state is calculated and recorded.

[0051] Among them, in S105, the step of processing and evaluating the information of the data record file using the test criterion includes:

[0052] Determine whether the measured signal has entered a steady state;

[0053] Calculate the mean value of the measured signal that enters the steady state;

[0054] Using the threshold value of the test criterion to judge the fault condition of the data in the data recording file;

[0055] Record the number of faults, the number of times the fault occurred, and whether the qualification test was passed or not.

[0056] In this embodiment, the data recording of the measured signal needs to be performed after the measured system enters a steady state to be effective test data.

[0057] The specific situation of the monitor is described below.

[0058] Please refer to Figure 2 , Figure 2It is a model diagram of the threshold monitor. First, the absolute value of the difference between the measured signal and the expected value (the expected value of the discrete quantity is given by the criterion file, and the expected value of the analog quantity is the calculated steady-state mean) is taken. If the absolute value is greater than the Fault threshold (default threshold), a transient fault (Fault) is recorded, and the fault count stored in the upper shot is added to the fault count increase value to obtain a new fault count value; otherwise, the fault count stored in the upper shot is subtracted from the fault count decrease value to obtain a new fault count value. The new fault count value is limited. If the new fault count value after limiting is greater than the Fail threshold (failed to pass the threshold), a permanent fault (Fail) is recorded. In this application, the threshold monitor is used to monitor whether the data of the measured signal in the flight control system 104 of the civil aircraft to be tested exceeds the threshold value and the number of beats required by the identification test. It can not only monitor the permanent fault of the measured signal, but also monitor the transient fault, and record the time, frequency and source code data of the fault detected by this type of threshold monitor in the post-processing test report file.

[0059] Please refer to Figure 3 , Figure 3 The data frame activity monitor model diagram is shown in Figure 1. Subtract the time stamp of the data frame under test from the time stamp of the received previous data frame. If the difference is greater than the maximum waiting time, it indicates that frame loss has occurred and a permanent fault (Fail) is recorded. The data frame activity monitor is used to monitor the time integrity of the measured signal of the civil aircraft flight control system 104 to be tested, and the time, frequency and source code data of the fault detected by this type of data frame activity monitor are recorded in the post-processing test report file.

[0060] Please refer to Figure 4 , Figure 4 This is a CRC check monitor model diagram. The CRC value of the data frame load data is calculated according to the CRC calculation method, and then compared with the CRC value in the data frame. If the two values ​​are not equal, a transient fault (Fault) is recorded, and the fault count stored in the upper shot is added to the fault count increase value to obtain a new fault count value; otherwise, the fault count stored in the upper shot is subtracted from the fault count decrease value to obtain a new fault count value. The new fault count value is limited. If the new fault count value after limiting is greater than the Fail threshold, a permanent fault (Fail) is recorded. The CRC check monitor is used to assess the data integrity of the measured signal of the civil aircraft flight control system 104 to be tested. It can not only monitor the permanent faults of the measured signal, but also monitor transient faults. The time, frequency and source code data of the faults detected by this type of CRC check monitor are recorded in the post-processing test report file.

[0061] Each measured signal has a corresponding monitor to monitor its time-based sequence data, and all monitors and their parameters are combined to form a criterion file. The criterion file can be in CSV format (Comma-Separated Values), with the first line containing the names of the columns and the second line containing the characteristics of each important measured signal, including signal name, test mode, monitor type and parameters, etc.

[0062] Specifically, the criteria file should contain at least the following fields:

[0063] (1) Signal name: the name of the signal being measured at the aircraft level;

[0064] (2) Test mode: the working mode of the civil aircraft flight control system 104 to be tested;

[0065] (3) Bus type: On which type of bus is the measured signal, including A429, A664 and other bus types;

[0066] (4) Bus name: Which bus link does the measured signal belong to? For example, ACE1_FCM means that the measured signal belongs to the link from ACE1 (ACE stands for actuator control electronics) to FCM (flight control module);

[0067] (5) Monitor type: The monitor types used in this criterion include threshold, activity and CRC check;

[0068] (6) Label: the label of the data frame where the measured signal is located;

[0069] (7) Subtag number: the subtag number of the data frame where the measured signal is located;

[0070] (8) Starting word position: the starting word position of the measured signal in the data frame to which it belongs;

[0071] (9) End word position: the end word position of the measured signal in the data frame to which it belongs;

[0072] (10) Data type: data operation type of the measured signal, including discrete, Boolean, floating point, etc.;

[0073] (11) Least significant bit: the least significant byte of the source code of the signal under test in the data word in the data frame;

[0074] (12) Most significant bit: the most significant byte of the source code of the signal under test in the data frame;

[0075] (13) Standard deviation threshold: used to determine whether the measured signal has entered a steady state. The steady-state mean of the measured signal can be calculated only after the measured signal has entered a steady state.

[0076] (14) Expected value: expected value of the measured signal;

[0077] (15) Least significant bit weight: the weight represented by the least significant bit of the source code of the measured signal in the data word in the data frame;

[0078] (16) Fault threshold: The threshold of the difference between the measured signal and the expected value. If it exceeds the threshold, the monitor outputs "fault" and the built-in fault counter of the monitor increases. If it is within the threshold, the monitor outputs "normal" and the built-in fault counter of the monitor decreases.

[0079] (17) Fault counter upper threshold: the maximum limit value of the fault counter of the signal monitor under test;

[0080] (18) Fault counter increment value: If the monitor outputs "fault", the value of the monitor's built-in fault counter increments;

[0081] (19) Fault counter reduction value: If the monitor output is "normal", the value of the built-in fault counter of the monitor is reduced;

[0082] (20) Failure threshold: If the built-in fault counter of the monitor is greater than the failure threshold, the monitor outputs “failure”;

[0083] (21) Maximum waiting time: If the maximum waiting time in milliseconds exceeds the maximum waiting time, the data frame activity monitor is judged as a failure.

[0084] The details of the data record file are described below.

[0085] First, the naming format of the data recording file is explained, that is, the first file naming format: the naming format is XXX.YYY format, where XXX is the test name and YYY is the bus type.

[0086] Secondly, the content format of the data record file is explained, that is, the first file content format:

[0087] The data logging file contains file header information, test data, user operations, and steady-state mean values ​​of the measured signal. The data logging file is a line text file, each line contains multiple data segments, and the data segments are separated by commas, as follows:

[0088] (1) File header information

[0089] The file header information consists of 6 lines in total, and each line includes two data segments.

[0090] The first data segment of the file header information is the data identifier, using "#" as a marker.

[0091] The second data segment of the first line is the total number of lines in the data file;

[0092] The second data segment of the second line is the bus type of the data acquisition hardware;

[0093] The second data segment of the third line is the name and version number of the data acquisition device;

[0094] The second data segment of the fourth line is the year, month, day, hour, minute, and second when data recording starts;

[0095] The second data segment in the fifth line is the name of the criterion file used by the data acquisition device;

[0096] The second data segment in the sixth row is the test mode.

[0097] (2) Test data

[0098] The test data includes N rows in total, and each row includes 6 data segments.

[0099] The first data segment is a data identifier, using "!" as a marker;

[0100] The second data segment is the hardware channel number for collecting data;

[0101] The third data segment is the data frame hardware failure flag;

[0102] The fourth data segment is the data frame data, which is expressed in hexadecimal and is separated from each other.

[0103] The fifth data segment is the time stamp of the data frame collected by the hardware - seconds;

[0104] The sixth data segment is the time stamp of the data frame collected by the hardware - microseconds.

[0105] (3) User operation

[0106] The user operation includes N lines, each line includes 2 data segments.

[0107] The first data segment is a data identifier, using "*" as a symbol;

[0108] The second data segment is the user operation text.

[0109] There are three types of user operation texts: "Start Test", "Stop Test" and "Clear Fault". "Start Test" means the test is officially started, and the data after this text is valid data; "Stop Test" means the test is stopped, and the data after this text is invalid data.

[0110] (4) Steady-state mean of the measured signal

[0111] The steady-state mean value of the measured signal includes N rows in total, and each row includes 7 data segments.

[0112] The first data segment is a data identifier, using "%" as a sign;

[0113] The second data segment is the hardware channel number for collecting data;

[0114] The third data segment is the data frame LABLE (label) number;

[0115] The fourth data segment is the starting word position of the measured signal in the data frame;

[0116] The fifth data segment is the starting bit position of the measured signal in the starting word of the data frame;

[0117] The sixth data segment is the stop bit position of the measured signal in the start word of the data frame;

[0118] The seventh data segment is the steady-state mean of the measured signal.

[0119] The following is an explanation of the file format of the post-processing test report file.

[0120] The post-processing test report should provide sufficient, detailed and reliable data analysis results for airworthiness. The post-processing test report file format includes the report file naming format (second file naming format) and content format (second file content format).

[0121] First, the file naming format of the post-processing test report is as follows:

[0122] XXX.YYY.qrpt. XXX is the test name, YYY is the bus type. To ensure the traceability of test data and reports, the report prefix is ​​consistent with the name of the data record file, and the file is in text format.

[0123] Secondly, the content format of the post-processing test report is as follows:

[0124] The file contents of the post-processing test report include: header information, test modal information, steady-state mean information of the measured signal, data statistics information of the data recording file, evaluation result information of each measured signal, test conclusion and file tail information.

[0125] (1) File header information

[0126] The file header mainly records the configuration information of this data processing. The main information starts with the "*" character and contains the following content:

[0127] 1) The version number of the data post-processing software used to perform this processing;

[0128] 2) The name of the processed data record file;

[0129] 3) Name of the judgment file used;

[0130] 4) Name of the test report generated;

[0131] 5) The date and time of processing.

[0132] (2) Test modal information

[0133] Starting with a "*" character, the record includes: the type of data bus processed and the flight control system operating mode tested.

[0134] (3) User operation information

[0135] Record the number of lines and recording time of the "Clear Faults", "Start Test" and "Stop Test" marks generated by the test personnel's operations in the original data file.

[0136] (4) Steady-state mean information of the measured signal

[0137] It mainly records the relevant information and steady-state mean of the measured analog signal. The steady-state mean will be used as the basis for subsequent monitor judgment, mainly including the following information:

[0138] 1) The label or channel name of the measured signal;

[0139] 2) Signal name;

[0140] 3) The word position of the measured signal in the data frame;

[0141] 4) The steady-state value of the measured signal.

[0142] (5) Test data statistics

[0143] Test data statistics include: the total number of lines in the test data file, the recording duration, and the number of occurrences of Clear Faults, Start Test, and Stop Test.

[0144] (6) Evaluation result information of the measured signal

[0145] It mainly contains the following information:

[0146] 1) The type of monitor used for the signal being measured;

[0147] 2) Aircraft-level name of the signal being measured;

[0148] 3) The word position, bit start and end position of the measured signal in the data frame;

[0149] 4) Number of failures;

[0150] 5) Number of failures;

[0151] 6) If the number of faults is greater than 0, the original data frame content where the fault occurred is displayed.

[0152] (7) Experimental conclusion

[0153] At the end of the report, information on whether the test passed and the number of Failures is given.

[0154] (8) File end information

[0155] At the end of the report, mark the end of the report (END OF REPORT).

[0156] After the monitor, data logging file format, and post-processing test report file format are defined, the qualification test begins.

[0157] After explaining the identification test system, the specific process of the identification test is explained.

[0158] Please refer to Figure 5 The present application also provides an identification test system for a civil aircraft flight control system, the test system comprising: a simulation load 101, a real load 102 and a controller 103, the test system is used to perform an identification test on a civil aircraft flight control system 104 to be tested.

[0159] Specifically, the simulation load 101 is used to send a first excitation signal to the flight control system 104 of the civil aircraft to be tested so that the flight control system 104 of the civil aircraft to be tested operates under the first excitation signal, and receive a test signal returned by the flight control system 104 of the civil aircraft to be tested;

[0160] The real load 102 is used to send a second excitation signal to the flight control system 104 of the civil aircraft to be tested so that the flight control system 104 of the civil aircraft to be tested operates under the second excitation signal;

[0161] The controller 103 is used to send a first excitation signal to the simulation load 101 and receive the measured signal through the simulation load 101, and receive the measured signal returned by the flight control system 104 of the civil aircraft to be tested under the second excitation signal; and is used to select and determine the types and parameters of multiple monitors corresponding thereto according to the characteristics of multiple measured signals of the flight control system 104 of the civil aircraft to be tested, the types and parameters of multiple monitors form the test criteria of the identification test of the flight control system of the civil aircraft, and define the fields of the criterion file of the test criteria; define the file format of the data recording file, the data recording file is used to record the data of the whole process of the identification test; define the file format of the post-processing test report file; record the data of the whole process of the identification test according to the file format of the data recording file; use the test criteria to process and evaluate the information of the data recording file, and use the post-processing test report file to output the processing and evaluation results. The controller 103 can be a data acquisition / post-processing computer.

[0162] Among them, the bus interface of the simulated load 101 is connected to the bus interface of the controller 103 through cable a, the bus interface of the simulated load 101 is connected to the bus interface of the civil aircraft flight control system 104 to be tested through cable b, and the interface between the interface of the civil aircraft flight control system 104 to be tested and the interface between the real load 102 is connected through cable c.

[0163] When conducting the identification test, first load the test criteria into the controller 103, determine the data recording file name, and determine other test conditions: set the state, test mode and test excitation of the flight control system under test according to the identification test outline.

[0164] Then the test data is recorded. When the user clicks the "Start Simulation" button on the data acquisition software of the controller 103, a file is generated according to the data recording file name and the file header information is written.

[0165] The file header information is as follows:

[0166] Set the file pointer to the second line and write “#,” the bus type of the data acquisition hardware;

[0167] The third line contains “#,” the name and version number of the data acquisition software;

[0168] The fourth line contains “#,” which is the current system time: year, month, day, hour, minute, and second.

[0169] The fifth line, write “#,” the name of the test criteria file;

[0170] In the sixth line, write “#,” the mode of the test.

[0171] Test data:

[0172] The received data frames are read one by one from the data queue in the controller 103 and written line by line to the data record file in the format of: !, hardware channel number, data frame fault flag, data frame content (hexadecimal), data frame time stamp - seconds, data frame time stamp - milliseconds.

[0173] The user operations are as follows:

[0174] When the user clicks the "Clear Faults" button on the data acquisition software of the controller 103, "*, Clear Faults" is written in the data log file;

[0175] The user clicks the "Start Test" button on the data acquisition software, and writes the steady-state mean of the measured signal line by line in the data recording file. The format is: %, hardware channel number, measured signal frame number, starting word position of the measured signal in the data frame, starting bit position of the measured signal in the starting word of the data frame, stop bit position of the measured signal in the starting word of the data frame, and steady-state mean of the measured signal. Write "*, Start Test" in the next line;

[0176] When the user clicks the "Stop Test" button on the data acquisition software, "*, StopTest" is written in the data logging file;

[0177] Stop recording:

[0178] When the user clicks the "Stop Simulation" button on the data acquisition software, the reading and writing of data frames will stop. The file pointer will move to the starting line of the file, and "#," the total number of lines in the file will be written. The file will be closed.

[0179] Data post-processing:

[0180] The post-processing flowchart is as follows Figure 6 As shown, the data post-processing software first loads the recorded data file and the judgment file, and then scans the data record file line by line according to the key symbols defined in the data record file, extracts the key information, uses the monitor group to calculate the time series-based data, and generates a post-processing test report based on the statistical calculation results.

[0181] As an example, a data log file such as Figure 7 and Figure 8 As shown, the post-processing test report is as follows Fig. 9 and Fig.10 shown.

[0182] The present invention determines the type and parameters of the monitor to be used according to the signal characteristics, forms the identification test criterion, realizes the monitor monitoring and judgment in the post-processing process, and gives the final conclusion; according to the airworthiness requirements, determines the reading method and rules between the file data record source code file and the post-processing method to ensure the correlation between the two; according to the airworthiness requirements, defines the source code data record file format and the data acquisition software in the data acquisition computer during the test process to completely record the test configuration, user operation, data row attributes and the format requirements of the test data. After the test is completed, the data is post-processed, and the criterion file is loaded using the data post-processing software. According to the file record format, real-time recording and the reading method and rules between the post-processing method, the data record file is processed line by line. After the processing is completed, a test report based on the data of each tested signal monitor is given, and the test results and test conclusions are given.

[0183] In summary, the beneficial effects of the present invention are as follows:

[0184] The present invention provides a comprehensive test application method that combines real-time data test records and post-processing report generation to meet the civil aircraft airworthiness requirements for civil aircraft flight control system identification tests. On the one hand, by generating data files in real time, the contradictions between data collection, judgment and report generation are resolved, the high data integrity requirements of "zero packet loss" civil aircraft airworthiness are met, and objective fact source code data is provided; on the other hand, by determining the test criteria, a complete evaluation of the civil aircraft identification test results by post-processing methods of multiple types of monitors is achieved, and a complete and detailed test report based on source data is given in accordance with airworthiness requirements, solving the problem that it is difficult to complete monitoring tests under short-term excitation tests of high field strength / lightning and other types of identification tests.

[0185] This method completely records the data of the entire test process, including test configuration, test time, user operation, steady-state mean, valid data and invalid data. The recorded data is processed based on time series using an external monitor group, and an objective, complete and detailed identification test report is provided after completion. The workload is small, manpower and time are saved, and it is not easy to make mistakes.

[0186] For example, in one embodiment of the present invention, the method of the present application was used to obtain airworthiness certification for a flight control system identification test of a large civil aircraft, providing a highly credible, objective and detailed report for airworthiness, while shortening the test time by about 50%, providing a basis for ensuring the credibility of airworthiness certification and the traceability of the process. According to the test flight requirements, the test data and test reports must be kept for more than three years in preparation for possible later inspections.

[0187] The embodiments of the present invention are described above in conjunction with the accompanying drawings, but the present invention is not limited to the above-mentioned specific implementation modes, which are merely illustrative rather than restrictive. Under the guidance of the present invention, ordinary technicians in this field can also make many forms without departing from the scope of protection of the present invention and the claims, all of which are within the protection of the present invention.

Claims

1. Civil aircraft flight control system identification test method, characterized in that: include: S101, selecting and determining the types and parameters of multiple monitors corresponding to the characteristics of multiple measured signals of the flight control system of the civil aircraft to be tested, the types and parameters of the multiple monitors forming a test criterion for the identification test of the flight control system of the civil aircraft, and defining the fields of the criterion file of the test criterion; The monitor includes: a threshold monitor, a data frame activity monitor and a CRC check monitor; the threshold monitor is used to monitor whether the data in the measured signal of the civil aircraft flight control system under test exceeds the threshold value and the number of beats required by the identification test; the data frame activity monitor is used to monitor the continuity of the data frame of the measured signal of the civil aircraft flight control system under test; the CRC check monitor is used to monitor the data integrity of the measured signal of the civil aircraft flight control system under test; S102, defining a file format of a data recording file, wherein the data recording file is used to record data of the entire process of the identification test, and the file format of the data recording file includes: a first file naming format and a first file content format; According to the first file naming format, the first file name includes: the test name and the bus type; according to the first file content format, the first file content includes the following items: file header information, test data, user operation and steady-state mean of the measured signal, the data of each item includes multiple data segments, and the first data segment of each item is provided with a data identifier corresponding to the item; S103, defining a file format of a post-processing test report file, wherein the file format of the post-processing test report file includes: a second file naming format and a second file content format; According to the second file naming format, the second file naming includes: the test name, bus type and post-processing test report file name suffix; according to the second file content format, the second file content includes the following items: file header information, test mode, user operation, steady-state mean of the measured signal, test data statistical information, evaluation results of the measured signal, test conclusion and file tail; S104, performing an identification test on the flight control system of the civil aircraft to be tested using the test criteria, and recording data of the entire identification test process according to the file format of the data recording file; S105, using the test criteria to process and evaluate the information in the data record file, and using a post-processing test report file to output the processing and evaluation results.

2. The civil aircraft flight control system identification test method according to claim 1, characterized in that: Each of the measured signals has a corresponding monitor, and the monitor is used to monitor the time-based sequence data of the measured signal.

3. The civil aircraft flight control system identification test method according to claim 1, characterized in that: The threshold value of the test criterion is stricter than the threshold value of the built-in monitor of the flight control system of the civil aircraft to be tested.

4. The civil aircraft flight control system identification test method according to claim 1, characterized in that: The CRC check monitor is also used to monitor permanent faults and transient faults of the measured signal of the flight control system of the civil aircraft to be tested.

5. The civil aircraft flight control system identification test method according to claim 1, characterized in that: The criterion file of the test criterion is in CSV format.

6. The civil aircraft flight control system identification test method according to claim 1, characterized in that: The fields of the test criterion file include: the name of the signal to be tested, the test mode, the type and parameters of the monitor.

7. The civil aircraft flight control system identification test method according to claim 3, characterized in that: The step of processing and evaluating the information of the data record file using the test criteria comprises: Determine whether the measured signal has entered a steady state; Calculate the mean value of the measured signal that enters the steady state; Using the threshold value of the test criterion to judge the fault condition of the data in the data recording file; Record the number of faults, the number of times the fault occurred, and whether the qualification test was passed or not.

8. The identification test system of the civil aircraft flight control system is characterized by: The method according to any one of claims 1 to 7 is used to perform an identification test on the flight control system of a civil aircraft to be tested, wherein the test system comprises: A simulation load is used to send a first excitation signal to the flight control system of the civil aircraft to be tested so that the flight control system of the civil aircraft to be tested operates under the first excitation signal, and receive a test signal returned by the flight control system of the civil aircraft to be tested; A real load, used for sending a second excitation signal to the flight control system of the civil aircraft to be tested so that the flight control system of the civil aircraft to be tested operates under the second excitation signal; The controller is used to send a first excitation signal to a simulated load and receive a measured signal through the simulated load, and receive the measured signal returned by the flight control system of the civil aircraft to be tested when running under the second excitation signal; and is used to select and determine the types and parameters of multiple monitors corresponding to the multiple measured signals of the flight control system of the civil aircraft to be tested according to the characteristics of the multiple measured signals, the types and parameters of the multiple monitors form the test criteria of the civil aircraft flight control system identification test, and define the fields of the criterion file of the test criteria; define the file format of the data recording file, the data recording file is used to record the data of the entire identification test process; define the file format of the post-processing test report file; record the data of the entire identification test process according to the file format of the data recording file; use the test criteria to process and evaluate the information of the data recording file, and use the post-processing test report file to output the processing and evaluation results.

9. The identification test system for the civil aircraft flight control system according to claim 8, characterized in that: The monitor includes: a threshold monitor, a data frame activity monitor and a CRC check monitor; the threshold monitor is used to monitor whether the data in the measured signal of the civil aircraft flight control system under test exceeds the threshold value and the number of beats required by the identification test; the data frame activity monitor is used to monitor the continuity of the data frame of the measured signal of the civil aircraft flight control system under test; the CRC check monitor is used to monitor the data integrity of the measured signal of the civil aircraft flight control system under test.

10. The identification test system for the civil aircraft flight control system according to claim 8, characterized in that: The file format of the data record file matches the file format of the post-processing test report file.

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