Simulation analysis method based on helicopter flight fault
Through simulation analysis methods, the operationality of the helicopter flight control system is solved, and the performance problem of the flight control system cannot be effectively verified in the existing technology in the case of failure is achieved, and fast and accurate verification and evaluation results are achieved.
Patent Information
- Application Number
- CN202411986503.0
- Authority / Receiving Office
- CN · China
- Patent Type
- Applications(China)
- Current Assignee / Owner
- Filing Date
- 2024-12-31
- Publication Date
- 2025-05-02
AI Technical Summary
The prior art cannot effectively verify the operability of the helicopter flight control system in specific failure situations, resulting in the inability to accurately evaluate the performance of the flight control system.
Through a simulation analysis method based on helicopter flight failure, test flight data are obtained and faults are injected into the virtual environment, the flight status is recorded and verified, and simulation analysis results are generated. The method includes obtaining historical and real-time flight test data, monitoring fault information in real time, and transmitting fault instructions to the flight control computer through the manipulation of the fault interface.
It realizes the operationality of the flight control system in a virtual environment in the specific fault situation, improves verification efficiency, and accurately evaluates the performance of the flight control system by comparing simulated flight data and test flight data.
Smart Images
Figure CN119918261A_ABST
Abstract
Description
Technical Field
[0001] The invention relates to the technical field of flight control, and in particular to a simulation analysis method based on helicopter flight failure. Background Art
[0002] According to the airworthiness test flight requirements of the "Helicopter Automatic Flight Control System Airworthiness Verification Flight Test Program", external fault information needs to be loaded during the fault simulation flight to verify that the helicopter can still be safely controlled for a long time after a failure, will not affect the control system, will not cause dangerous loads to the helicopter or cause dangerous deviations of the helicopter.
[0003] However, in the existing technology, it is impossible to verify the operability of the flight control system under specific failure conditions because it is impossible to provide real automatic flight control system dual redundancy failure, automatic flight control system single redundancy failure, automatic flight control system automatic balancing failure, automatic flight control system single-axis failure, automatic flight control system advanced mode failure, automatic flight control system fault, and automatic flight control system servo failure during the test flight. Summary of the invention
[0004] The present application solves the problem in the prior art that the operability of the flight control system under specific fault conditions cannot be verified by providing a simulation analysis method based on helicopter flight faults, thereby achieving the technical effect of quickly verifying the operability of the flight control system under specific fault conditions.
[0005] The present application provides a simulation analysis method based on helicopter flight failure, the method comprising:
[0006] S100: Acquire flight test data, the flight test data including historical flight test data and real-time flight test data. During the aircraft flight test, transmit the real-time flight test data to a data receiving terminal, monitor fault information in real time, and transmit fault instructions to a flight control computer by manipulating a fault interface.
[0007] S200: Record the fault sending time, fault solving time, actual flight time, and verify the flight status in real time to generate simulation analysis results.
[0008] Furthermore, the historical test flight data are the fault data and route trajectory data of the aircraft in the historical test flight missions; and the real-time test flight data are the fault data and route trajectory data of the aircraft in the current test flight mission.
[0009] Furthermore, the fault information includes: automatic flight control system dual redundancy failure, automatic flight control system single redundancy failure, automatic flight control system automatic balancing failure, automatic flight control system single axis failure, automatic flight control system advanced mode failure, automatic flight control system failure and automatic flight control system steering gear failure.
[0010] Furthermore, the method also includes: after receiving a fault instruction, clicking a fault injection button to inject a corresponding fault, prompting whether to confirm the injection of relevant fault information, and after confirmation, the fault injection button is displayed in red, indicating that the fault information has been injected; starting to record the fault injection time, clicking the corresponding fault button again, prompting whether to end the fault injection, after confirmation, the fault injection ends, and the fault injection time is recorded, and the button returns to green.
[0011] Furthermore, the method further includes: if the injected fault cannot be cleared, clicking a fault clear button to clear all the injected faults.
[0012] Furthermore, the method also includes: comparing and analyzing the simulated flight data and the test flight data based on the simulation analysis results, analyzing the degree of deviation between the simulated flight trajectory and the test flight trajectory, analyzing the deviation data generated when comparing the fault data based on the degree of trajectory deviation, determining whether it is necessary to retest the aircraft data, and generating a fault handling plan.
[0013] Furthermore, a comparative analysis is performed on the simulated flight data and the test flight data, including: preprocessing the simulated flight data and the test flight data, the preprocessing including aligning data time, cleaning data and unifying dimensions; selecting flight parameters for one-by-one comparison, calculating the relative error of each parameter at the same time point, performing statistical analysis on the relative errors, calculating statistical indicators, and obtaining the difference between the simulated data and the test flight data based on the statistical indicators.
[0014] Furthermore, the degree of deviation between the simulated flight trajectory and the test flight trajectory is analyzed, including: drawing the simulated flight trajectory and the test flight trajectory in a unified three-dimensional space, calculating the distance difference between the simulated trajectory and the test flight trajectory at each time point, and analyzing the directional deviation of the trajectory; and performing weighted summation of the distance difference and the directional deviation to obtain the degree of deviation.
[0015] Furthermore, the deviation data generated when comparing the fault data is analyzed according to the trajectory deviation degree to determine whether the aircraft data needs to be retested, including: classifying the deviation data according to the trajectory deviation degree, and analyzing the correlation between the deviation data and the fault data for deviation data of different levels; presetting a deviation degree threshold and a correlation threshold, and when the deviation degree is not less than the deviation degree threshold and the correlation is not less than the correlation threshold, the aircraft data needs to be retested.
[0016] Furthermore, a corresponding fault simulation scheme is designed according to the fault handling scheme, including: selecting a fault type according to the fault handling scheme, and determining specific simulation parameters, creating a simulation environment consistent with the actual flight environment, configuring a fault injection tool, generating fault simulation results, and verifying the effectiveness of the fault handling scheme according to the fault simulation results.
[0017] One or more technical solutions provided in this application have at least the following technical effects or advantages:
[0018] Through simulation analysis methods, the operability of the flight control system under specific fault conditions can be quickly verified in a virtual environment, thereby improving verification efficiency. By comparing simulated flight data and test flight data, the degree of deviation can be analyzed and the performance of the flight control system can be accurately evaluated, thus achieving precise control of simulation parameters and improving the accuracy of simulation analysis. BRIEF DESCRIPTION OF THE DRAWINGS
[0019] Figure 1 It is a schematic diagram of the overall flow of a simulation analysis method based on helicopter flight failure in an embodiment of the present invention;
[0020] Figure 2 A schematic diagram of the connection principle of a verification method of a simulation analysis method based on helicopter flight failure in an embodiment of the present invention;
[0021] Figure 3 The present invention is a schematic diagram of a fault sending interface of a verification method in a simulation analysis method based on helicopter flight failures in an embodiment of the present invention. DETAILED DESCRIPTION
[0022] In order to facilitate the understanding of the present invention, the present application will be described more comprehensively below with reference to the relevant drawings.
[0023] like Figure 1 As shown, a simulation analysis method based on helicopter flight failure, the method comprises:
[0024] S100: Acquire flight test data, the flight test data including historical flight test data and real-time flight test data. During the aircraft flight test, transmit the real-time flight test data to a data receiving terminal, monitor fault information in real time, and transmit fault instructions to a flight control computer by manipulating a fault interface.
[0025] S200: Record the fault sending time, fault solving time, actual flight time, and verify the flight status in real time to generate simulation analysis results.
[0026] In some embodiments, the historical test flight data is the fault data and route trajectory data of the aircraft in the historical test flight mission; the real-time test flight data is the fault data and route trajectory data of the aircraft in the current test flight mission.
[0027] In some embodiments, the real-time test flight data is the test flight data transmitted in real time via ground-to-air communication during the actual test flight of the aircraft.
[0028] In some embodiments, the fault information includes but is not limited to: automatic flight control system dual redundancy failure, automatic flight control system single redundancy failure, automatic flight control system automatic trim failure, automatic flight control system single axis failure, automatic flight control system advanced mode failure, automatic flight control system failure and automatic flight control system steering gear failure. Combine the fault information with the RS232 bus fault sending data definition, as shown in Table 1:
[0029] Table 1- RS232 bus fault sending data definition
[0030]
[0031]
[0032] In some embodiments, the method further includes: after receiving a fault instruction, clicking a fault injection button to inject a corresponding fault, prompting whether to confirm the injection of relevant fault information, and after confirmation, the fault injection button is displayed in red, indicating that the fault information has been injected; starting to record the fault injection time, clicking the corresponding fault button again, prompting whether to end the fault injection, after confirmation, the fault injection ends, and the fault injection time is recorded, and the button returns to green.
[0033] In some embodiments, the method further includes: if the injected fault cannot be cleared, clicking a fault clear button to clear all the injected faults.
[0034] like Figure 2 As shown, the verification method of this application uses a portable computer with built-in battery, 2 RS232 serial ports, 10″ WSVGA (1024×768) TFT-LCD display (high brightness 300nits, readable in sunlight) capacitive touch screen. Enter the fault interface as shown Figure 3 As shown, click the fault injection button (only one fault is injected at a time), and you will be prompted to confirm whether to inject the relevant fault information. After confirmation, the fault injection button will be displayed in red, indicating that the fault information has been injected and the fault injection time will be recorded. Click the corresponding fault button again, and you will be prompted to end the fault injection. After confirmation, the fault injection is ended, and the fault injection time is ended, and the button returns to green.
[0035] The method for verifying the helicopter flight control system fault simulation test flight of the present application also designs a fault clearing button to prevent the fault from being injected all the time and unable to be cancelled. This button can cancel the injected fault with one click; in order to understand in real time whether the method is in normal working state, such as Figure 3 As shown, the "Running Time" displayed in the lower left corner of the fault simulation interface can help you understand the running status of the flight control fault simulation device software in real time to prevent a crash.
[0036] Specifically, the method of verifying the failure of the automatic flight control system is explained by taking the verification of the dual redundancy failure of the automatic flight control system as an example:
[0037] By clicking Figure 3 The "Flight Control Amplifier Failure" button in the dual-redundancy failure area of the automatic flight control system on the interface is pressed, and the page prompts "Do you want to inject a fault?". After the co-pilot clicks "OK," the flight control system has loaded the fault. The "HT / HOV" knob on the automatic flight control console and the corresponding indicators of the "AP1," "AP2," and "A.TRIM" buttons on the main flight control console are all off, the warning list on the integrated display screen displays "Flight Control Failure," the flight control status bar displays amber "AFCSDISENGAGED," and the headset issues a voice warning "Please operate manually," indicating that the dual-redundancy of the automatic flight control system has failed and the pilot is required to manually operate the flight. After observing the warning information, the pilot delays for 1.5 seconds and then flies manually for 2 minutes. After the mission is completed, the co-pilot clicks the "Flight Control Amplifier Failure" button in the dual-redundancy failure area of the automatic flight control system in the fault simulation interface of the flight control system fault simulation device. The page prompts "Do you want to end the fault injection?". After the co-pilot clicks "OK," the flight control system has canceled the fault injection and the flight control system returns to normal. Figure 3 All fault buttons in the display interface bar display the words "Not Injected".
[0038] The above operations verify the identifiability of the dual-redundancy failure alarm of the automatic flight control system, and whether it will cause dangerous flight trajectory deviation or overload that endangers the structure within the reaction time. At the same time, the flight crew's intervention control can be corrected in time and will not cause dangerous flight trajectory deviation or overload that endangers the structure.
[0039] In some embodiments, the method further includes: comparing and analyzing the simulated flight data and the test flight data based on the simulation analysis results, analyzing the degree of deviation between the simulated flight trajectory and the test flight trajectory, analyzing the deviation data generated when comparing the fault data based on the degree of trajectory deviation, determining whether it is necessary to retest the aircraft data, and generating a fault handling plan.
[0040] In some embodiments, a comparative analysis is performed on the simulated flight data and the test flight data, including: preprocessing the simulated flight data and the test flight data, the preprocessing including aligning data time, cleaning data and unifying dimensions; selecting flight parameters for one-by-one comparison, calculating the relative error of each parameter at the same time point, performing statistical analysis on the relative error, calculating statistical indicators, and obtaining the difference between the simulated data and the test flight data based on the statistical indicators.
[0041] Specifically, the flight parameters include speed, altitude, heading, attitude angle, etc., and the statistical indicators include average value, standard deviation, maximum value, minimum value, etc.
[0042] In some embodiments, analyzing the degree of deviation between the simulated flight trajectory and the test flight trajectory includes: drawing the simulated flight trajectory and the test flight trajectory in a unified three-dimensional space, calculating the distance difference between the simulated trajectory and the test flight trajectory at each time point, and analyzing the directional deviation of the trajectory; and performing weighted summation of the distance difference and the directional deviation to obtain the degree of deviation.
[0043] In some embodiments, the deviation data generated when comparing the fault data is analyzed according to the degree of trajectory deviation, and whether the aircraft data needs to be retested is determined, including: according to the degree of trajectory deviation, the deviation data is divided into levels, and for the deviation data of different levels, the correlation between the deviation data and the fault data is analyzed; the deviation degree threshold and the correlation threshold are pre-set, and when the deviation degree is not less than the deviation degree threshold and the correlation is not less than the correlation threshold, the aircraft data needs to be retested. The levels are divided into categories such as small deviation, medium deviation and large deviation. The specific steps are as follows: collect simulated flight data and test flight data, perform time alignment, data cleaning and unit unification; use statistical analysis and visualization methods to compare key flight parameters and quantify differences; draw a trajectory map, calculate distance difference and direction deviation, and evaluate the degree of trajectory deviation; classify, cause analyze and correlation analyze the deviation data; determine whether the aircraft data needs to be retested according to the degree of deviation and impact, and formulate corresponding fault handling plans.
[0044] In some embodiments, a corresponding fault simulation scheme is designed according to the fault handling scheme, including: selecting a fault type according to the fault handling scheme, and determining specific simulation parameters, creating a simulation environment consistent with the actual flight environment, configuring a fault injection tool, generating fault simulation results, and verifying the effectiveness of the fault handling scheme based on the fault simulation results.
[0045] The technical solutions in the above embodiments of the present application have at least the following technical effects or advantages:
[0046] This application uses simulation analysis methods to quickly verify the operability of the flight control system under specific fault conditions in a virtual environment, thereby improving verification efficiency; by comparing simulated flight data and test flight data, analyzing the degree of deviation, and accurately evaluating the performance of the flight control system, it achieves precise control of simulation parameters and improves the accuracy of simulation analysis.
[0047] The above description is only a preferred embodiment of the present invention and is not intended to limit the present invention. For those skilled in the art, the present invention may have various modifications and variations. Any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the present invention shall be included in the protection scope of the present invention.
Claims
1. A simulation analysis method based on helicopter flight failure, characterized in that: The method comprises: S100: Acquire flight test data, the flight test data including historical flight test data and real-time flight test data. During the aircraft flight test, transmit the real-time flight test data to a data receiving terminal, monitor fault information in real time, and transmit fault instructions to a flight control computer by manipulating a fault interface. S200: Record the fault sending time, fault solving time, actual flight time, and verify the flight status in real time to generate simulation analysis results.
2. A simulation analysis method based on helicopter flight failure according to claim 1, characterized in that: The historical test flight data are the fault data and route trajectory data of the aircraft in the historical test flight missions; the real-time test flight data are the fault data and route trajectory data of the aircraft in the current test flight mission.
3. A simulation analysis method based on helicopter flight failure according to claim 1, characterized in that: The fault information includes: automatic flight control system dual redundancy failure, automatic flight control system single redundancy failure, automatic flight control system automatic balancing failure, automatic flight control system single axis failure, automatic flight control system advanced mode failure, automatic flight control system failure and automatic flight control system steering gear failure.
4. A simulation analysis method based on helicopter flight failure as claimed in claim 1, characterized in that: The method further includes: after receiving a fault instruction, clicking a fault injection button to inject a corresponding fault, prompting whether to confirm the injection of relevant fault information, after confirmation, the button for fault injection is displayed in red, indicating that the fault information has been injected; starting to record the fault injection time, clicking the corresponding fault button again, prompting whether to end the injection of the fault, after confirmation, the fault injection ends, and the fault injection time is recorded, and the button returns to green.
5. The simulation analysis method based on helicopter flight failure according to claim 1, characterized in that: The method further includes: if the injected fault cannot be cleared, clicking a fault clearing button to clear all the injected faults.
6. A simulation analysis method based on helicopter flight failure according to claim 1, characterized in that: The method further includes: comparing and analyzing the simulated flight data and the test flight data according to the simulation analysis result, analyzing the degree of deviation between the simulated flight trajectory and the test flight trajectory, analyzing the deviation data generated when comparing the fault data according to the degree of trajectory deviation, determining whether it is necessary to retest the aircraft data, and generating a fault handling plan.
7. A simulation analysis method based on helicopter flight failure as claimed in claim 6, characterized in that: The simulated flight data and the test flight data are compared and analyzed, including: preprocessing the simulated flight data and the test flight data, the preprocessing including aligning data time, cleaning data and unifying dimensions; selecting flight parameters for one-by-one comparison, calculating the relative error of each parameter at the same time point, performing statistical analysis on the relative error, calculating statistical indicators, and obtaining the difference between the simulated data and the test flight data according to the statistical indicators.
8. The simulation analysis method based on helicopter flight failure according to claim 6, characterized in that: Analyzing the degree of deviation between the simulated flight trajectory and the test flight trajectory, including: drawing the simulated flight trajectory and the test flight trajectory in a unified three-dimensional space, calculating the distance difference between the simulated trajectory and the test flight trajectory at each time point, and analyzing the directional deviation of the trajectory; and performing weighted summation of the distance difference and the directional deviation to obtain the degree of deviation.
9. The simulation analysis method based on helicopter flight failure according to claim 6, characterized in that: Deviation data generated when comparing fault data is analyzed according to the trajectory deviation degree to determine whether the aircraft data needs to be retested, including: classifying the deviation data according to the trajectory deviation degree, and analyzing the correlation between the deviation data and the fault data for deviation data of different levels; presetting a deviation degree threshold and a correlation threshold, and when the deviation degree is not less than the deviation degree threshold and the correlation is not less than the correlation threshold, the aircraft data needs to be retested.
10. The simulation analysis method based on helicopter flight failure according to claim 6, characterized in that: A corresponding fault simulation scheme is designed according to the fault handling scheme, including: selecting a fault type according to the fault handling scheme, determining specific simulation parameters, creating a simulation environment consistent with an actual flight environment, configuring a fault injection tool, generating fault simulation results, and verifying the effectiveness of the fault handling scheme according to the fault simulation results.