Flap fault analogue simulation implementation method and device, computer equipment and medium
By constructing a simulation method based on the characteristics of the flap system, the problem of limit cycle oscillation during flap change phase was solved, achieving accurate simulation and prediction of flap failure and improving flight safety.
Patent Information
- Authority / Receiving Office
- CN · China
- Patent Type
- Applications(China)
- Current Assignee / Owner
- Filing Date
- 2025-11-26
- Publication Date
- 2026-04-14
AI Technical Summary
When using theoretical models of stepless control of the main control surfaces of an aircraft in existing technologies, the problem of limit cycle oscillation is prone to occur, and the symptoms of flap failure are often difficult to identify in time during the flap change phase.
A simulation method for flap failure is provided. By obtaining the current flap angle, setting the failure mode, determining whether the flap has stopped deflecting, and outputting the flap deflection and convergence criterion, a simulation method based on the characteristics of the flap system is constructed.
Accurately simulate typical flap failure modes, provide a basis for predicting flap failures and handling emergencies, and improve flight safety.
Smart Images
Figure CN121859519A_ABST
Abstract
Description
Technical Field
[0001] This invention relates to the field of simulation technology, and in particular to a method, apparatus, computer equipment, and medium for simulating flap failure. Background Technology
[0002] With the booming development of the aviation industry, flight safety has always been a focus of attention. As a key component for controlling the attitude and stability of an aircraft, the reliability of its performance is directly related to flight safety.
[0003] As one of the main control surfaces of an aircraft, flaps are crucial for improving takeoff and landing performance and controlling flight attitude. However, in actual use, flaps can experience various malfunctions such as jamming and asymmetrical deflection, which can lead to serious flight accidents. Therefore, effectively predicting the flight response after flap malfunctions is of great significance for ensuring flight safety.
[0004] In recent years, to predict the impact of various potential control surface failures on flight safety, flight simulation technology has been widely used to simulate aircraft flight responses under various operating conditions, providing a theoretical basis for the compilation of flight manuals. By establishing a theoretical simulation model of flap failure and outputting the real-time flap deflection after a failure, it is possible to predict the flight response after a flap failure and formulate emergency response procedures.
[0005] Unlike the continuously variable control (CVT) primary control surfaces of aircraft, most aircraft flaps are controlled in steps via flap control handles. If a theoretical model of continuously variable control based on the primary control surfaces is used, limit cycle oscillations are likely to occur. Furthermore, flap malfunction symptoms often appear when the flaps are adjusted; if the flap configuration is not changed, even if a flap malfunction has already occurred, no symptoms will appear.
[0006] Therefore, there is an urgent need for a simulation method for the stepped control mode of flaps and the flap failure symptoms that mostly occur during the flap change phase. Summary of the Invention
[0007] In view of this, embodiments of the present invention provide a simulation method for flap failure to solve the technical problem of limit cycle oscillation that easily occurs when using theoretical models of stepless control of aircraft main control surfaces in the prior art. The method includes: Obtain the current flap angle, and determine the direction of flap movement based on the current flap angle; Set the flap failure mode, and determine the flap deflection speed and flap deflection target value corresponding to the normal mode and each failure mode according to the direction of movement; Based on the current flap angle, the target flap deflection value, and whether the flap handle position has changed, determine whether the flap has stopped deflecting, and output a flap stop deflection signal and the judgment condition corresponding to the flap stop deflection signal; Based on the flap deflection speed, the target flap deflection value, whether the flap has stopped deflecting, and the judgment condition, the flap deflection is output, and the convergence criterion of the flap deflection is determined.
[0008] This invention also provides a simulation device for flap failure, to address the technical problem of limit cycle oscillations that easily occur when using theoretical models of stepless control of aircraft main control surfaces in existing technologies. The device includes: The motion direction acquisition module is used to acquire the current flap angle and determine the motion direction of the flap based on the current flap angle. The fault setting module is used to set the fault mode of the flap, and determine the flap deflection speed and flap deflection target value corresponding to the normal mode and each fault mode according to the direction of movement. The module for determining whether to stop deflection is used to determine whether the flap has stopped deflecting based on the current flap angle, the flap deflection target value, and whether the flap handle position has changed, and outputs a flap stop deflection signal and the judgment condition corresponding to the flap stop deflection signal; The flap deflection output module is used to output the flap deflection based on the flap deflection speed, the flap deflection target value, whether the flap has stopped deflecting, and the judgment condition, and to determine the convergence criterion of the flap deflection.
[0009] This invention also provides a computer device, including a memory, a processor, and a computer program stored in the memory and executable on the processor. When the processor executes the computer program, it implements the above-mentioned simulation method for any flap failure, thereby solving the technical problem of limit cycle oscillation that easily occurs when using the theoretical model of stepless control of the aircraft main control surface in the prior art.
[0010] This invention also provides a computer-readable storage medium storing a computer program that performs the simulation method for any of the above-mentioned flap failures, in order to solve the technical problem of limit cycle oscillations that easily occur when using the theoretical model of stepless control of the aircraft main control surface in the prior art.
[0011] Compared with the prior art, the beneficial effects that at least one technical solution adopted in the embodiments of this specification can achieve include at least: A simulation method based on the characteristics of the flap system is developed, which can accurately simulate the typical failure modes of the flap. Attached Figure Description
[0012] To more clearly illustrate the technical solutions of the embodiments of this application, the drawings used in the embodiments will be briefly introduced below. Obviously, the drawings described below are only some embodiments of this application. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.
[0013] Figure 1 This is a flowchart of a simulation method for flap failure provided in an embodiment of the present invention; Figure 2 This is a schematic diagram of the flap movement direction determination logic provided in an embodiment of the present invention; Figure 3 This is a structural block diagram of a computer device provided in an embodiment of the present invention; Figure 4 This is a structural block diagram of a device for simulating flap failure provided in an embodiment of the present invention. Detailed Implementation
[0014] The embodiments of this application will now be described in detail with reference to the accompanying drawings.
[0015] The following specific examples illustrate the implementation of this application. Those skilled in the art can easily understand other advantages and effects of this application from the content disclosed in this specification. Obviously, the described embodiments are only a part of the embodiments of this application, and not all of them. This application can also be implemented or applied through other different specific embodiments, and the details in this specification can also be modified or changed based on different viewpoints and applications without departing from the spirit of this application. It should be noted that, in the absence of conflict, the following embodiments and features in the embodiments can be combined with each other. Based on the embodiments in this application, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of this application.
[0016] In this embodiment of the invention, a simulation method for flap failure is provided, such as... Figure 1 As shown, the method includes: Step S101: Obtain the current flap angle, and determine the movement direction of the flaps based on the current flap angle; Step S102: Set the fault mode of the flap, and determine the flap deflection speed and flap deflection target value corresponding to the normal mode and each fault mode according to the direction of movement. Step S103: Determine whether the flap has stopped deflecting based on the current flap angle, the flap deflection target value, and whether the flap handle position has changed, and output the flap stop deflection signal and the judgment condition corresponding to the flap stop deflection signal; Step S104: Based on the flap deflection speed, the flap deflection target value, whether the flap has stopped deflecting, and the judgment condition, output the flap deflection and determine the convergence criterion of the flap deflection.
[0017] In practice, the current flap angle is obtained through the following steps, and the movement direction of the flap is determined by the current flap angle: When the flap handle changes position or the flap enters the fault mode from the normal mode, the angle difference between the flap angle corresponding to the flap handle position and the current flap angle collected by the sensor is calculated; when the angle difference is greater than zero, the flap moves downward; when the angle difference is equal to zero, the flap does not move; when the angle difference is less than zero, the flap moves upward.
[0018] In practice, the following steps are used to set the flap fault modes: based on the direction of motion, the flap deflection speed and target value corresponding to the normal mode and each fault mode are determined: The system sets fault modes, including jamming, half-speed deflection, sudden deflection, uncommanded deflection, and asymmetric protection. In normal mode, the flap deflection speed is set to the normal flap retraction / extension speed, the flap deflection angle corresponding to the flap handle position is taken as the normal flap deflection angle, and the flap deflection target value is set to the normal flap deflection angle. In jamming mode, the flap deflection speed is set to 0, and the flap deflection target value is set to the normal flap deflection angle. In half-speed deflection mode, the flap deflection speed is set to half of the normal flap retraction / extension speed, and the flap deflection target value is set to the normal flap deflection angle. In uncommanded deflection mode, the flap deflection speed is set to the normal flap retraction / extension speed, and the flap deflection target value is set to the target value represented by the flap position ± the protection threshold value M. 保护 If the direction of movement is downward, the ± sign is positive; if the direction of movement is upward, the ± sign is negative. When the fault mode is sharp deflection, the flap deflection speed is set to the normal flap extension / retraction speed, and the flap deflection target value is set to the maximum flap angle. When the fault mode is asymmetrical protection, the flap deflection speed corresponding to the normal side is set to the normal flap extension / retraction speed, and the flap deflection speed corresponding to the abnormal side is set to the flap deflection speed V. 故障 Set the flap deflection target value to zero.
[0019] In specific implementation, the following steps are used to determine whether the flap has stopped deflecting based on the current flap angle, the target flap deflection value, and whether the flap handle position has changed, and to output a flap stop deflection signal and the corresponding judgment conditions for the flap stop deflection signal: Set a stop deflection threshold M to achieve the target flap deflection value. 停止 The maximum allowable deflection angle difference M between the left and right flaps 偏差 The first angle difference between the target flap deflection value and the current flap angle is calculated based on the current flap angle collected by the sensor. This first angle difference is set to be less than the stop deflection threshold M. 停止 As the first judgment condition; when the flap enters the fault mode from the normal mode, the flap handle position is obtained from the flap handle, and whether the manual position changes is used as the second judgment condition; the absolute value of the angle difference between the left and right flaps is calculated and used as the second angle difference value, and the second angle difference value is greater than the maximum deflection angle difference value M. 偏差 As a third judgment condition; when the first judgment condition, the second judgment condition, or the third judgment condition is met, the flap stop deflection signal and the judgment condition corresponding to the flap stop deflection signal are output.
[0020] In specific implementation, the following steps are used to output the flap deflection based on the flap deflection speed, the target flap deflection value, whether the flap has stopped deflecting, and the judgment condition, and to determine the convergence criterion of the flap deflection: When the flap stop deflection signal is not obtained, the flap is moved toward the flap deflection target value according to the flap deflection speed and flap movement direction, and the real-time flap deflection angle is output; when the flap stop deflection signal is obtained, the flap stops deflecting. If the judgment condition is the first judgment condition, the flap deflection target value is output; otherwise, the real-time current flap angle is output.
[0021] In practice, the convergence speed is adjusted through the following steps: Set weight coefficients for each of the aforementioned fault modes; calculate the fault severity index based on the weight coefficients, the absolute value of the first angle difference, and the absolute value of the second angle difference; dynamically adjust the flap convergence speed based on the fault severity index to ensure that the flap deflection meets the convergence criterion of the flap deflection, wherein the fault severity index is proportional to the flap convergence speed; calculate and output the flap deflection for the next simulation cycle based on the adjusted flap convergence speed and the current flap angle, until the flap deflection meets the convergence criterion of the flap deflection.
[0022] Specifically, the higher the fault severity index, the larger the convergence speed parameter is set to, so that the flap deflection converges to the target state more quickly.
[0023] In practice, the simulation report is generated through the following steps: During the flap failure simulation, timestamps and corresponding key data are continuously recorded and saved to the data storage area. The key data includes the current failure mode, the real-time output of the flap deflection speed and deflection angle, the current target flap deflection value, the flap's direction of motion, whether the flap has stopped deflecting, and the judgment conditions triggered when it stops deflecting. When a flap stop deflection signal is detected, or a report generation command is received, a simulation report is generated. Based on the key data, the data is summarized and analyzed to generate a simulation report including a failure event summary, event timeline, performance index table, and original data index. The fault event summary is used to record the set initial fault mode, fault injection time, flap stop deflection time, and the final judgment condition that leads to flap stop; the event timeline is used to list the key event sequence in chronological order, including fault mode switching, flap handle position change, and generation of flap stop deflection signal; the performance index table is used to calculate and output the total time from fault injection to flap stop deflection, the final deviation between the actual flap deflection angle and the target flap deflection value, and the maximum angle difference between the left and right flaps during the simulation process; the raw data index is used to provide links or identifiers pointing to the data storage area.
[0024] Specifically, the original data index is recorded for retrieval of continuously recorded key data for detailed review. This ensures the auditability and reproducibility of the entire simulation process, and has significant practical value.
[0025] In one embodiment of the present invention, assuming that the aircraft has only one flap on each side, the simulation method for flap failure includes the following steps: Step 1: Determine the deflection speed and target deflection value of the flap malfunction.
[0026] Set the fault mode; different fault modes correspond to different fault deflection speeds and deflection target values.
[0027] The fault modes are as follows: 0 (normal), 1 (stuck), 2 (half speed deflection), 3 (sudden deflection), 4 (uncommanded deflection), 5 (asymmetric protection).
[0028] The deflection speed and target deflection values for different modes are as follows: Step 1.1: Under normal conditions, the flaps deflect normally, the flap deflection speed is the normal flap extension and retraction speed, and the deflection target value is the flap deflection angle corresponding to the flap handle position. Step 1.2: When stuck, the flap deflection speed is 0, and the deflection target value remains the same as in the normal state; Step 1.3: At half deflection speed, the flap deflection speed is half of the normal deflection speed, and the deflection target value remains consistent with the normal state. Step 1.4: During a sharp descent, the flap deflection speed remains the same as in the normal state, and the target deflection value is the maximum flap angle; Step 1.5: During non-commanded deflection, the flap deflection speed remains consistent with the normal state. The deflection target value is the target value represented by the flap position ± the protection threshold value M. 保护 ; Step 1.6: During asymmetrical protection, the flap deflection speed on the normal side remains consistent with the normal state, while the flap deflection speed V on the faulty side... 故障 Determined by the flap actuator, the target value for the flap is 0.
[0029] Among them, the normal deflection speed of the flap is the system's design value V. 正常 The protection threshold value for non-command deflection is the system's professionally designed protection value M. 保护 The fault-side flap deflection speed V of asymmetric protection 故障 Determined by the flap actuator.
[0030] Step 2: Obtain the direction of movement of the flaps.
[0031] like Figure 1 As shown, when the flap handle changes position, or when the flap transitions from a normal state to a fault state, the difference between the flap angle represented by the flap handle position and the current flap angle collected by the sensor is calculated to obtain the flap's movement direction, Dir. A difference greater than 0 indicates the flap is deployed (represented by 1); a difference less than 0 indicates the flap is retracted (represented by -1); and a difference equal to 0 indicates the flap is not moving (represented by 0). When the flap moves to the target deflection value, the movement direction Dir is 0.
[0032] Step 3: Set the logic for stopping flap deflection.
[0033] Set the "stop deflection threshold M" to reach the target flap deflection value. 停止 The maximum allowable deflection angle difference M between the left and right flaps 偏差 .
[0034] The flaps will stop deflecting if any of the following three conditions are met: First judgment condition: The absolute value of the difference between the "target value of flap deflection" and the "current angle of the flap collected by the sensor" is less than the threshold value M. 停止 .
[0035] Second judgment condition: When the flap changes from normal state to fault state, the flap handle position is not changed when obtained from the flap handle.
[0036] Third criterion: The absolute value of the difference between the left and right flap angles is greater than the maximum deflection angle difference M. 偏差 hour.
[0037] Step 4: Output flap deflection and determine the flap deflection convergence criterion.
[0038] When no flap stop deflection signal is received, the flap moves toward the flap target value according to the deflection speed and flap movement direction, and outputs the real-time deflection angle of the flap; when a flap stop signal is received, the flap stops deflecting, and the real-time deflection angle of the flap is output. If the flap stop signal at this time is determined by the first judgment condition, the deflection target value of the flap is output.
[0039] In this embodiment, a computer device is provided, such as... Figure 3 As shown, it includes a memory 301, a processor 302, and a computer program stored in the memory and executable on the processor. When the processor executes the computer program, it implements the simulation method for any of the above-mentioned flap failures.
[0040] Specifically, the computer device can be a computer terminal, a server, or a similar computing device.
[0041] In this embodiment, a computer-readable storage medium is provided, which stores a computer program that performs the simulation implementation method for any of the above-described flap failures.
[0042] Specifically, computer-readable storage media include both permanent and non-permanent, removable and non-removable media, which can store information using any method or technology. Information can be computer-readable instructions, data structures, modules of programs, or other data. Examples of computer-readable storage media include, but are not limited to, phase-change memory (PRAM), static random access memory (SRAM), dynamic random access memory (DRAM), other types of random access memory (RAM), read-only memory (ROM), electrically erasable programmable read-only memory (EEPROM), flash memory or other memory technologies, CD-ROM, digital versatile optical disc (DVD) or other optical storage, magnetic tape, magnetic disk storage or other magnetic storage devices, or any other non-transferable medium that can be used to store information accessible by a computing device. As defined herein, computer-readable storage media do not include transient media, such as modulated data signals and carrier waves.
[0043] Based on the same inventive concept, this invention also provides a device for simulating flap failures, as described in the following embodiments. Since the principle by which the device for simulating flap failures solves the problem is similar to the method for simulating flap failures, the implementation of the device can refer to the implementation of the method for simulating flap failures, and repeated details will not be elaborated further. As used below, the terms "unit" or "module" can refer to a combination of software and / or hardware that performs a predetermined function. Although the device described in the following embodiments is preferably implemented in software, hardware implementation, or a combination of software and hardware, is also possible and contemplated.
[0044] Figure 4 This is a structural block diagram of a device for simulating flap failure according to an embodiment of the present invention, as shown below. Figure 4 As shown, it includes: motion direction acquisition module 401, fault setting module 402, determine whether to stop deflection module 403, and flap deflection output module 404. The structure is described below.
[0045] The motion direction acquisition module 401 is used to acquire the current flap angle and determine the motion direction of the flap based on the current flap angle. The fault setting module 402 is used to set the fault mode of the flap and determine the flap deflection speed and flap deflection target value corresponding to the normal mode and each fault mode according to the direction of movement. The module 403 for determining whether to stop deflection is used to determine whether the flap has stopped deflecting based on the current flap angle, the flap deflection target value, and whether the flap handle position has changed, and outputs a flap stop deflection signal and the judgment condition corresponding to the flap stop deflection signal; The flap deflection output module 404 is used to output the flap deflection based on the flap deflection speed, the flap deflection target value, whether the flap has stopped deflecting, and the judgment condition, and to determine the convergence criterion of the flap deflection.
[0046] In one embodiment, the motion direction acquisition module includes: An angle difference calculation unit is used to calculate the angle difference between the flap angle corresponding to the flap handle position and the current flap angle collected by the sensor when the flap handle changes position or the flap enters the fault mode from the normal mode. The first motion direction determination unit is used to determine that the motion direction of the flap is downward when the angle difference is greater than zero. The second motion direction determination unit is used to determine that the flaps are not moving when the angle difference is equal to zero. The third motion direction determination unit is used to determine that when the angle difference is less than zero, the motion direction of the flap is upward retraction.
[0047] In one embodiment, the fault setting module includes: A fault mode setting unit is used to set fault modes, wherein the fault modes include jamming, half-speed deflection, sudden deflection, uncommanded deflection, and asymmetric protection. The normal mode setting unit is used to set the flap deflection speed to the normal flap retraction speed, set the flap deflection angle corresponding to the flap handle position as the normal flap deflection angle, and set the flap deflection target value to the normal flap deflection angle when the normal mode is in use. The jamming mode setting unit is used to set the flap deflection speed to 0 and the flap deflection target value to the normal flap deflection angle when the fault mode is jamming. The deflection half-speed mode setting unit is used to set the flap deflection speed to half of the normal flap retraction and extension speed when the fault mode is deflection half-speed, and to set the flap deflection target value to the normal flap deflection angle. The non-command deflection mode setting unit is used to set the flap deflection speed to the normal flap retraction and extension speed when the fault mode is non-command deflection, and to set the flap deflection target value to the flap position representative target value ± protection threshold value M. 保护 If the direction of movement is downward, the ± sign is positive; if the direction of movement is upward, the ± sign is negative. The acute deflection mode setting unit is used to set the flap deflection speed to the normal flap retraction and extension speed and set the flap deflection target value to the maximum flap angle when the fault mode is acute deflection. The asymmetric mode setting unit is used to, when the fault mode is asymmetric protection, set the flap deflection speed corresponding to the flap on the normal side to the normal flap retraction / extension speed, and set the flap deflection speed corresponding to the flap on the abnormal side to the flap deflection speed V. 故障 Set the flap deflection target value to zero.
[0048] In one embodiment, determining whether to stop the deflection module includes: The parameter setting unit is used to set the stop deflection threshold M for achieving the target flap deflection value. 停止 The maximum allowable deflection angle difference M between the left and right flaps 偏差 ; A first judgment condition unit is constructed to calculate the first angle difference between the target flap deflection value and the current flap angle, based on the current flap angle acquired by the sensor, and sets the first angle difference to be less than the stop deflection threshold value M. 停止 As the first condition for judgment; A second judgment condition unit is constructed, which is used to obtain the flap handle position from the flap handle when the flap enters the fault mode from the normal mode, and use whether the manual position changes as the second judgment condition. A third judgment condition unit is constructed to calculate the absolute value of the angle difference between the left and right flaps, and use it as the second angle difference value. The second angle difference value is set to be greater than the maximum deflection angle difference value M. 偏差 As a third condition for judgment; The judgment condition generation unit is used to output a flap stop deflection signal and the judgment condition corresponding to the flap stop deflection signal when the first judgment condition, the second judgment condition, or the third judgment condition is met.
[0049] In one embodiment, the flap deflection output module includes: The deflection angle output unit is used to move the flap toward the flap deflection target value according to the flap deflection speed and flap movement direction when the flap stop deflection signal is not obtained, and output the real-time deflection angle of the flap. The flap deflection target value output unit is used to stop the flap deflection when the flap stop deflection signal is obtained. If the judgment condition is the first judgment condition, the flap deflection target value is output; otherwise, the current flap angle in real time is output.
[0050] In one embodiment, the above-described apparatus further includes a convergence speed adjustment module.
[0051] In one embodiment, the convergence speed adjustment module includes: A weighting coefficient setting unit is used to set the weighting coefficient corresponding to each of the fault modes; The fault severity index calculation unit is used to calculate the fault severity index based on the weighting coefficient, the absolute value of the first angle difference, and the absolute value of the second angle difference. The flap convergence speed adjustment unit is used to dynamically adjust the flap convergence speed according to the fault severity index, so that the flap deflection meets the convergence criterion of the flap deflection, wherein the fault severity index is proportional to the flap convergence speed. An iterative unit is used to calculate and output the flap deflection for the next simulation cycle based on the adjusted flap convergence speed and the current flap angle, until the flap deflection meets the convergence criterion of the flap deflection.
[0052] In one embodiment, the above-described apparatus further includes a simulation report generation module.
[0053] In one embodiment, the simulation report generation module includes: The key data recording unit is used to continuously record timestamps and key data corresponding to the timestamps during the flap failure simulation process, and save them to the data storage area. The key data includes the current failure mode, the real-time output of the flap deflection speed and the flap deflection degree, the current flap deflection target value, the movement direction of the flap, whether the flap has stopped deflecting, and the judgment conditions triggered when the deflection stops. The simulation report generation timing acquisition unit is used to generate a simulation report when the flap stop deflection signal is detected or a report generation command is received. The simulation report generation unit is used to summarize and analyze the key data to generate a simulation report including a fault event summary, event timeline, performance index table, and raw data index. The fault event summary generation unit is used to record the set initial fault mode, fault injection time, flap stop deflection time and the final judgment condition that causes the flap to stop. The event timeline generation unit is used to list a sequence of key events in chronological order, including fault mode switching, flap handle position change, and generation of flap stop deflection signal. The performance index table generation unit is used to calculate and output the total time from fault injection to flap stop deflection, the final deviation between the actual flap deflection angle and the flap deflection target value, and the maximum angle difference between the left and right flaps during the simulation process. A raw data index generation unit is used for the raw data index to provide links or identifiers pointing to the data storage area.
[0054] The embodiments of the present invention achieve the following technical effects: Based on the characteristics of stepped flap control and the fact that flap malfunctions often occur during flap change phases, a method for simulating flap malfunctions is provided. This method establishes a theoretical simulation model of flap malfunctions based on the working principle and common failure modes of the flap system. By simulating the motion state and response characteristics of the flap under different operating conditions, dynamic simulation of the flap deflection process is achieved, and real-time flap deflection data is obtained. Most aircraft flap systems are controlled in stepped positions via flap control handles. These systems are complex in structure and have rigorous control logic. Furthermore, flaps require frequent operation during flight to adapt to different flight conditions. Actual operation shows that flap malfunctions often occur during flap movement, such as flap jamming, asymmetrical deflection, or abnormal position feedback, seriously affecting flight safety. Based on the aforementioned characteristics of the flap system, the designed flap fault simulation method fully considers factors such as control command response, mechanical transmission delay, and sensor signal interference. It can accurately simulate typical fault modes that may occur in actual operation of the flap. The simulation method of this invention can provide a theoretical basis for fault prediction, health management, and diagnostic analysis of the flap system. It is applicable to multiple application scenarios such as flight control system simulation testing, aircraft maintenance training, and fault logic verification, and has high engineering practical value.
[0055] Obviously, those skilled in the art should understand that the modules or steps of the above-described embodiments of the present invention can be implemented using general-purpose computing devices. They can be centralized on a single computing device or distributed across a network of multiple computing devices. Optionally, they can be implemented using computer-executable program code, thereby storing them in a storage device for execution by a computing device. In some cases, the steps shown or described can be performed in a different order than those presented here, or they can be fabricated as separate integrated circuit modules, or multiple modules or steps can be fabricated as a single integrated circuit module. Thus, the embodiments of the present invention are not limited to any particular hardware and software combination.
[0056] The above description is merely a preferred embodiment of the present invention and is not intended to limit the present invention. For those skilled in the art, various modifications and variations can be made to the embodiments of the present invention. Any modifications, equivalent substitutions, improvements, etc., made within the spirit and principles of the present invention should be included within the protection scope of the present invention.
Claims
1. A simulation method for flap failure, characterized in that, include: Obtain the current flap angle, and determine the direction of flap movement based on the current flap angle; Set the flap failure mode, and determine the flap deflection speed and flap deflection target value corresponding to the normal mode and each failure mode according to the direction of movement; Based on the current flap angle, the target flap deflection value, and whether the flap handle position has changed, determine whether the flap has stopped deflecting, and output a flap stop deflection signal and the judgment condition corresponding to the flap stop deflection signal; Based on the flap deflection speed, the target flap deflection value, whether the flap has stopped deflecting, and the judgment condition, the flap deflection is output, and the convergence criterion of the flap deflection is determined.
2. The simulation method for flap failure as described in claim 1, characterized in that, The fault modes of the flaps are set, and based on the direction of motion, the flap deflection speed and target value corresponding to the normal mode and each fault mode are determined, including: The fault modes are set, including jamming, half-speed deflection, sudden deflection, uncommanded deflection, and asymmetric protection. When in normal mode, the flap deflection speed is set to the normal flap retraction speed, the flap deflection angle corresponding to the flap handle position is taken as the normal flap deflection angle, and the flap deflection target value is set as the normal flap deflection angle. When the fault mode is stuck, the flap deflection speed is set to 0, and the flap deflection target value is set to the normal flap deflection angle. When the fault mode is half-speed deflection, the flap deflection speed is set to half of the normal flap retraction and extension speed, and the flap deflection target value is set to the normal flap deflection angle. When the fault mode is non-command deflection, the flap deflection speed is set to the normal flap retraction / extension speed, and the flap deflection target value is set to the flap position target value ± the protection threshold value M. 保护 If the direction of movement is downward, the ± sign is positive; if the direction of movement is upward, the ± sign is negative. When the fault mode is sharp deflection, the flap deflection speed is set to the normal flap retraction and extension speed, and the flap deflection target value is set to the maximum flap angle. When the fault mode is asymmetric protection, the flap deflection speed corresponding to the flap on the normal side is set to the normal flap extension / retraction speed, and the flap deflection speed corresponding to the flap on the abnormal side is set to the flap deflection speed V. 故障 Set the flap deflection target value to zero.
3. The simulation method for flap failure as described in claim 1, characterized in that, Obtaining the current flap angle and determining the flap's movement direction based on the current flap angle includes: When the flap handle changes position or the flap enters the fault mode from the normal mode, the angle difference between the flap angle corresponding to the flap handle position and the current flap angle collected by the sensor is calculated. When the angle difference is greater than zero, the flap moves downwards. When the angle difference is zero, the flaps do not move; When the angle difference is less than zero, the flap moves in an upward retraction direction.
4. The simulation method for flap failure as described in claim 1, characterized in that, Based on the current flap angle, the target flap deflection value, and whether the flap handle position has changed, it is determined whether the flap has stopped deflecting, and a flap stop deflection signal and the corresponding judgment conditions are output, including: Set a stop deflection threshold M to achieve the target flap deflection value. 停止 The maximum allowable deflection angle difference M between the left and right flaps 偏差 ; The first angle difference between the target flap deflection value and the current flap angle is calculated based on the current flap angle acquired by the sensor. This first angle difference is set to be less than the stop deflection threshold M. 停止 As the first condition for judgment; When the flap changes from the normal mode to the fault mode, the flap handle position is obtained from the flap handle, and whether the manual position changes is used as the second judgment condition. Calculate the absolute value of the angular difference between the left and right flaps, and use it as the second angular difference. Make sure this second angular difference is greater than the maximum deflection angle difference M. 偏差 As a third condition for judgment; When the first judgment condition, the second judgment condition, or the third judgment condition is met, the flap stop deflection signal and the judgment condition corresponding to the flap stop deflection signal are output.
5. The simulation method for flap failure as described in claim 1, characterized in that, Based on the flap deflection speed, the target flap deflection value, whether the flap has stopped deflecting, and the judgment condition, the flap deflection is output, and the convergence criterion for the flap deflection is determined, including: When the flap stop deflection signal is not obtained, the flap is moved toward the flap deflection target value according to the flap deflection speed and flap movement direction, and the real-time deflection angle of the flap is output. When the flap deflection stop signal is received, the flap deflection is stopped. If the judgment condition is the first judgment condition, the flap deflection target value is output; otherwise, the current flap angle in real time is output.
6. The simulation method for flap failure as described in any one of claims 1 to 5, characterized in that, Also includes: Set the weight coefficient for each of the aforementioned fault modes; The fault severity index is calculated based on the weighting coefficient, the absolute value of the first angle difference, and the absolute value of the second angle difference. Based on the fault severity index, the flap convergence speed is dynamically adjusted so that the flap deflection meets the convergence criterion of the flap deflection, wherein the fault severity index is proportional to the flap convergence speed. Based on the adjusted flap convergence speed and the current flap angle, calculate and output the flap deflection for the next simulation cycle until the flap deflection meets the convergence criterion.
7. The simulation method for flap failure as described in any one of claims 1 to 5, characterized in that, Also includes: During the flap failure simulation process, timestamps and key data corresponding to the timestamps are continuously recorded and saved to the data storage area. The key data includes the current failure mode, the real-time output of the flap deflection speed and the flap deflection degree, the current flap deflection target value, the movement direction of the flap, whether the flap has stopped deflecting, and the judgment conditions triggered when the flap stops deflecting. When the flap deflection stop signal is detected, or a report generation command is received, a simulation report is generated: Based on the key data, the data is summarized and analyzed to generate a simulation report that includes a summary of fault events, an event timeline, a performance index table, and an index of the raw data. The fault event summary is used to record the set initial fault mode, fault injection time, flap stop deflection time, and the final judgment condition that causes the flap to stop. The event timeline is used to list the sequence of key events in chronological order. The sequence of key events includes fault mode switching, flap handle position changes, and the generation of flap stop deflection signals. The performance index table is used to calculate and output the total time from fault injection to flap stop deflection, the final deviation between the actual flap deflection angle and the flap deflection target value, and the maximum angle difference between the left and right flaps during the simulation process. The original data index is used to provide a link or identifier to the data storage area.
8. A simulation device for flap failure, characterized in that, include: The motion direction acquisition module is used to acquire the current flap angle and determine the motion direction of the flap based on the current flap angle. The fault setting module is used to set the fault mode of the flap, and determine the flap deflection speed and flap deflection target value corresponding to the normal mode and each fault mode according to the direction of movement. The module for determining whether to stop deflection is used to determine whether the flap has stopped deflecting based on the current flap angle, the flap deflection target value, and whether the flap handle position has changed, and outputs a flap stop deflection signal and the judgment condition corresponding to the flap stop deflection signal; The flap deflection output module is used to output the flap deflection based on the flap deflection speed, the flap deflection target value, whether the flap has stopped deflecting, and the judgment condition, and to determine the convergence criterion of the flap deflection.
9. A computer device, comprising a memory, a processor, and a computer program stored in the memory and executable on the processor, characterized in that, When the processor executes the computer program, it implements the simulation method for flap failure as described in any one of claims 1 to 7.
10. A computer-readable storage medium, characterized in that, The computer-readable storage medium stores a computer program that performs a simulation method for flap failure according to any one of claims 1 to 7.