An automatic calibration method for the position zero of an aircraft flap rudder surface

Abstract

The application provides an automatic calibration method for the position zero of an aircraft flap rudder surface, and belongs to the technical field of high lift of an aircraft. Specifically, two flap control computers of the aircraft store flap electrical position data when the flap rudder surface is adjusted to a mechanical zero position. The flap control computer sends the flap electrical position data in the flap position data with an invalid state of a data usage flag to a rear cross-link flap power drive controller as flap zero position data. When one of the flap control computers is replaced, a central maintenance system obtains new flap position zero position data according to the flap electrical position data of the two flap control computers and the flap electrical position data of the two flap power drive controllers. Through the processing scheme, the calibration efficiency and reliability of the flap position zero position are improved when the spare parts are replaced in the outfield, the maintenance work is simplified, and the safety hidden danger is eliminated.

Description

TECHNICAL FIELD

[0001] The present application relates to the field of high-lift system of aircraft, and particularly to a method for automatically calibrating the position of aileron rudder surface. BACKGROUND

[0002] Modern large aircraft are equipped with high-lift systems. In the low-speed state of take-off and landing, the aileron and slat are controlled to extend outward and bend downward to increase the wing surface area, change the airfoil, and improve the lift of the aircraft, so as to ensure a reasonable taxi distance and a safe take-off speed of the aircraft, and improve the climb rate, approach speed, and approach flight attitude of the aircraft. The aileron control computer is the core component of the high-lift system. Each aircraft is generally equipped with two aileron control computers, each of which is configured with a command channel and a monitoring channel. The aileron control computer command and monitoring channels respectively collect the control handle and wing surface position sensor information, and perform position closed-loop control after control law calculation. Therefore, the accuracy of the mechanical zero position of the aileron wing surface and the electrical zero position of the aileron position collected by the aileron control computer has a significant impact on the control precision of the entire high-lift system. Inaccurate mechanical zero position and electrical zero position may also cause aileron wing surface asymmetry false alarm faults and affect flight safety. When the aileron control computer is replaced, personnel need to adjust the aileron wing surface position and then re-collect the aileron position electrical zero position. This method is low in efficiency and has high requirements for the maintenance environment.

[0003] The current processing method is as follows. When the aircraft enters the assembly stage, the aircraft assembly personnel install the left and right aileron surfaces and perform mechanical zero adjustment to ensure that the installation position of the wing surface meets the design requirements. However, since the above work is generally completed manually, errors in the installation position of the left and right wing surfaces and errors between the left and right wing surfaces are actually unavoidable. To solve the problem of inaccurate aileron position collection information caused by mechanical zero adjustment errors, or even the serious problem of wing surface asymmetry, electrical zero position collection work still needs to be performed when the aileron control computer is initially installed on the aircraft. The specific process is as follows. After confirming that the mechanical position of the wing surface basically meets the mechanical zero design requirements, the aileron control computer enters the ground maintenance mode, and the command and monitoring channels respectively read the aileron position sensor information cross-linked to each channel. If the read aileron position information meets the system allocation index, the data is valid, and the data is stored in the non-volatile memory (NVRAM) of the computer as the aileron position electrical zero position for software operation. If the collected data exceeds the system allocation index, mechanical zero adjustment and electrical zero position collection work need to be performed again until the requirements are met.

[0004] The above processing mode can effectively avoid the control precision and flap asymmetry caused by the mechanical zero position installation position error of the flap surface, but each operation depends on the adjustment of the mechanical zero position and the cooperation of the ground maintenance equipment, and in some cases, especially in the case of rapid replacement of spare parts and lack of maintenance equipment in the field, the flap surface zero position cannot be calibrated. In this case, if mechanical zero adjustment and flap control computer flap position electrical zero adjustment are still required using field ground maintenance equipment to put the replaced spare parts into use, it is obviously not meet the requirements of actual combat. SUMMARY

[0005] Therefore, the present application provides an aircraft flap surface position zero automatic calibration method, which solves the problems in the prior art, improves the efficiency and reliability of the flap position zero calibration of the spare parts replacement in the field, simplifies the maintenance work, and eliminates safety hazards.

[0006] The aircraft flap surface position zero automatic calibration method provided by the present application adopts the following technical scheme:

[0007] An aircraft flap surface position zero automatic calibration method comprises:

[0008] Step 1: The two flap control computers of the aircraft store the flap electrical position data when the flap surface is adjusted to the mechanical zero position, and the flap position data includes the flap electrical position data and a data use flag, and the initial state of the data use flag is invalid.

[0009] Step 2: The flap control computer sends the flap electrical position data in the flap position data with the invalid state of the data use flag to the rear cross-link flap power drive controller as the flap zero data, the rear cross-link flap power drive controller stores the received flap electrical position data, the flap control computer changes the data use flag to the valid state and stores it in the flap control computer.

[0010] Step 3: When only one of the two flap control computers is replaced, the two flap control computers send the flap electrical position data as first data and second data to the central maintenance system of the aircraft, and the two flap power drive controllers send the flap electrical position data as third data and fourth data to the central maintenance system of the aircraft, and the central maintenance system calculates the difference between the first data and the third data, the difference between the first data and the fourth data, the difference between the second data and the third data, and the difference between the second data and the fourth data.

[0011] When the four differences are all less than a threshold value, the average of the first data, the second data, the third data and the fourth data is taken as the new flap position zero data.

[0012]

[0012] When the difference between the first data and the third data is less than the threshold value, the difference between the first data and the fourth data is less than the threshold value, and the difference between the first data and the second data is greater than the threshold value, the average of the first data, the third data and the fourth data is taken as the new flap position zero data.

[0013] When the difference between the second data and the third data is less than the threshold value, the difference between the second data and the fourth data is less than the threshold value, and the difference between the first data and the second data is greater than the threshold value, the average of the second data, the third data and the fourth data is taken as the new flap position zero data.

[0014] The new flap position zero data is sent to the two flap control computers and the two flap power drive controllers.

[0015] Optionally, in step 3, when the difference between the first data and the third data is greater than the threshold value, the difference between the first data and the fourth data is greater than the threshold value, and the difference between the first data and the second data is greater than the threshold value, steps 1 and 2 are repeated to reacquire the flap electrical position data when the flap surface is adjusted to the mechanical zero position.

[0016] When the difference between the first data and the third data is greater than the threshold value, the difference between the first data and the fourth data is greater than the threshold value, and the difference between the first data and the second data is less than the threshold value, steps 1 and 2 are repeated to reacquire the flap electrical position data when the flap surface is adjusted to the mechanical zero position.

[0017] When the difference between the first data and the third data is less than the threshold value, the difference between the first data and the fourth data is greater than the threshold value, steps 1 and 2 are repeated to reacquire the flap electrical position data when the flap surface is adjusted to the mechanical zero position.

[0018] When the difference between the second data and the third data is greater than the threshold value, the difference between the second data and the fourth data is greater than the threshold value, and the difference between the first data and the second data is greater than the threshold value, steps 1 and 2 are repeated to reacquire the flap electrical position data when the flap surface is adjusted to the mechanical zero position.

[0019] When the difference between the second data and the third data is greater than the threshold value, the difference between the second data and the fourth data is greater than the threshold value, and the difference between the first data and the second data is less than the threshold value, steps 1 and 2 are repeated to reacquire the flap electrical position data when the flap surface is adjusted to the mechanical zero position.

[0020] Optionally, in step 1, when the aircraft is in an initial state, the flap surface of the aircraft is adjusted to the mechanical zero position, and the two flap control computers each acquire the flap electrical position data when the flap surface is adjusted to the mechanical zero position, and the flap electrical position data when the flap surface is adjusted to the mechanical zero position is stored on the two flap control computers.

[0021] Optionally, the electrical position data of the flaps when the flap control surfaces are adjusted to the mechanical zero position is stored in the NVRAM of the two flap control computers.

[0022] Optionally, in step 2, before the flap control computer sends the flap electrical position data in the flap position data with the flag set to invalid as the flap zero position data to the back-end crosslinking flap power drive controller, the following steps are also included: the two flap control computers each determine whether their respective flap control computers and the back-end crosslinking equipment flap power drive controller are communicating normally. If the communication is normal, they determine whether the flap position data uses the flag state.

[0023] Optionally, after sending the new flap position zero-point data to the two flap control computers and the two flap power drive controllers in step 3, the two flap control computers and the two flap power drive controllers also store the received new flap position zero-point data.

[0024] In summary, this application includes the following beneficial technical effects:

[0025] The method in this application covers the flap position zeroing and implementation process, and the functional description is complete;

[0026] The method in this application requires no additional hardware resources and has the characteristics of low implementation cost and high usability.

[0027] The method described in this application enables rapid zeroing of flap control surfaces, and is highly efficient and reliable. Attached Figure Description

[0028] 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.

[0029] Figure 1 This is a flowchart illustrating the electrical zero-position acquisition stage of the flap position in this application;

[0030] Figure 2 This is a flowchart illustrating the application's runtime phase. Detailed Implementation

[0031] The embodiments of this application will now be described in detail with reference to the accompanying drawings.

[0032] 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.

[0033] It should be noted that various aspects of embodiments within the scope of the appended claims are described below. It will be apparent that the aspects described herein can be embodied in a wide variety of forms, and any particular structure and / or function described herein is merely illustrative. Based on this application, those skilled in the art will understand that one aspect described herein can be implemented independently of any other aspect, and two or more of these aspects can be combined in various ways. For example, any number of aspects set forth herein can be used to implement the device and / or practice the method. Additionally, this device and / or method can be implemented using structures and / or functionalities other than one or more of the aspects set forth herein.

[0034] It should also be noted that the illustrations provided in the following embodiments are only schematic representations of the basic concept of this application. The drawings only show the components related to this application and are not drawn according to the actual number, shape and size of the components in the actual implementation. In the actual implementation, the form, quantity and proportion of each component can be arbitrarily changed, and the layout of the components may also be more complex.

[0035] Furthermore, specific details are provided in the following description to facilitate a thorough understanding of the examples. However, those skilled in the art will understand that the described aspects can be practiced without these specific details.

[0036] This application provides a method for automatically calibrating the zero position of an aircraft flap control surface.

[0037] An automatic zero-position calibration method for aircraft flap control surfaces, characterized in that it includes:

[0038] Step 1: Both flap control computers of the aircraft store the flap electrical position data when the flap control surfaces are adjusted to the mechanical zero position. The flap position data includes the flap electrical position data, whether the data is used flag, and the initial state of the data use flag is set to invalid.

[0039] Step 2: The flap control computer sends the flap electrical position data from the flap position data with the data usage flag set to invalid as the flap zero position data to the back-end crosslinked flap power drive controller. The back-end crosslinked flap power drive controller stores the received flap electrical position data. The flap control computer changes the data usage flag to valid and stores it in the flap control computer.

[0040] Step 3: When only one flap control computer is replaced, the two flap control computers send the flap electrical position data as the first data and the second data to the aircraft's central maintenance system, respectively. The two flap power drive controllers send the flap electrical position data as the third data and the fourth data to the aircraft's central maintenance system. The central maintenance system calculates the difference between the first data and the third data, the difference between the first data and the fourth data, the difference between the second data and the third data, and the difference between the second data and the fourth data.

[0041] When all four differences are less than the threshold, the average of the first, second, third, and fourth data is taken as the new flap position zero data.

[0042] If the difference between the first and third data is less than the threshold, the difference between the first and fourth data is less than the threshold, and the difference between the first and second data is greater than the threshold, then the average of the first, third, and fourth data is taken as the new flap position zero value.

[0043] If the difference between the second and third data is less than the threshold, the difference between the second and fourth data is less than the threshold, and the difference between the first and second data is greater than the threshold, then the average of the second, third, and fourth data is taken as the new flap position zero value.

[0044] The new flap position zero-point data is sent to two flap control computers and two flap power drive controllers.

[0045] In step 3, when the difference between the first data and the third data is greater than the threshold, the difference between the first data and the fourth data is greater than the threshold, and the difference between the first data and the second data is greater than the threshold, repeat steps 1 and 2 to reacquire the flap electrical position data when the flap control surface is adjusted to the mechanical zero position.

[0046] If the difference between the first and third data is greater than a threshold, if the difference between the first and fourth data is greater than a threshold, and if the difference between the first and second data is less than a threshold, repeat steps 1 and 2 to reacquire the flap electrical position data when the flap control surface is adjusted to the mechanical zero position.

[0047] If the difference between the first and third data is less than the threshold, and the difference between the first and fourth data is greater than the threshold, repeat steps 1 and 2 to reacquire the flap electrical position data when the flap control surface is adjusted to the mechanical zero position.

[0048] If the difference between the second and third data is greater than a threshold, and the difference between the second and fourth data is greater than a threshold, and the difference between the first and second data is greater than a threshold, repeat steps 1 and 2 to reacquire the flap electrical position data when the flap control surface is adjusted to the mechanical zero position.

[0049] If the difference between the second and third data is greater than a threshold, and the difference between the second and fourth data is greater than a threshold, and the difference between the first and second data is less than a threshold, repeat steps 1 and 2 to reacquire the flap electrical position data when the flap control surface is adjusted to the mechanical zero position.

[0050] The electrical position data of the flaps when the flap control surfaces are adjusted to the mechanical zero position is stored in the NVRAM of the two flap control computers.

[0051] In one embodiment:

[0052] like Figure 1 As shown, during the flap position electrical zero-point acquisition phase: the flap control surfaces are adjusted to the mechanical zero position and adjusted to meet the required accuracy. The flap system is set to maintenance mode. Two flap control computers respectively acquire the flap position electrical zero-point data and store it in their respective channels' NVRAM. The stored data includes the flap position acquisition value, data validity flag, and data usage flag. The data validity flag is determined based on whether the actual acquired flap position data meets the design margin requirements and whether the checksum is correct. The data usage flag is set to invalid.

[0053] like Figure 2 As shown, this is the application runtime phase. During the flap control computer software initialization phase, the flap position data stored in NVRAM is read and its validity is checked. If the data is valid, the flap position data stored in NVRAM is used as the zero-position value for the software operation; otherwise, the default zero-position data is used. Both flap control computers determine whether they are communicating normally with the back-end flap power drive controller. If communication is normal, the data validity flag is valid, and the data usage flag is invalid, the flap control computer sends the zero-position data stored in NVRAM to the back-end flap power drive controller. Simultaneously, the flap control computer changes the data usage flag to valid and stores the updated data in NVRAM. If the above conditions are not met, the flap control computer does not send the zero-position data to the back-end flap power drive controller.

[0054] Step 3, after sending the new flap position zero-point data to the two flap control computers and the two flap power drive controllers, also includes: the two flap control computers and the two flap power drive controllers storing the received new flap position zero-point data.

[0055] The above description is merely a specific embodiment of this application, but the scope of protection of this application is not limited thereto. Any variations or substitutions that can be easily conceived by those skilled in the art within the technical scope disclosed in this application should be included within the scope of protection of this application. Therefore, the scope of protection of this application should be determined by the scope of the claims.

Claims

1. A method for automatically calibrating the zero position of aircraft flap control surfaces, characterized in that, include: Step 1: Both flap control computers of the aircraft store the flap electrical position data when the flap control surfaces are adjusted to the mechanical zero position. The flap position data includes the flap electrical position data, whether the data is used flag, and the initial state of the data is used flag is set to invalid. Step 2: The flap control computer sends the flap electrical position data from the flap position data with the data usage flag set to invalid as the flap zero position data to the back-end cross-linked flap power drive controller. The back-end cross-linked flap power drive controller stores the received flap electrical position data. The flap control computer changes the data usage flag to valid and stores it in the flap control computer. Step 3: When only one flap control computer is replaced, the two flap control computers send the flap electrical position data as the first data and the second data to the aircraft's central maintenance system, respectively. The two flap power drive controllers send the flap electrical position data as the third data and the fourth data to the aircraft's central maintenance system. The central maintenance system calculates the difference between the first data and the third data, the difference between the first data and the fourth data, the difference between the second data and the third data, and the difference between the second data and the fourth data. When all four differences are less than the threshold, the average of the first, second, third, and fourth data is taken as the new flap position zero data. If the difference between the first and third data is less than the threshold, the difference between the first and fourth data is less than the threshold, and the difference between the first and second data is greater than the threshold, then the average of the first, third, and fourth data is taken as the new flap position zero value. If the difference between the second and third data is less than the threshold, the difference between the second and fourth data is less than the threshold, and the difference between the first and second data is greater than the threshold, then the average of the second, third, and fourth data is taken as the new flap position zero value. The new flap position zero-point data is sent to two flap control computers and two flap power drive controllers.

2. The automatic zero-position calibration method for aircraft flap control surfaces according to claim 1, characterized in that, In step 3, when the difference between the first data and the third data is greater than the threshold, the difference between the first data and the fourth data is greater than the threshold, and the difference between the first data and the second data is greater than the threshold, repeat steps 1 and 2 to reacquire the flap electrical position data when the flap control surface is adjusted to the mechanical zero position. If the difference between the first and third data is greater than a threshold, if the difference between the first and fourth data is greater than a threshold, and if the difference between the first and second data is less than a threshold, repeat steps 1 and 2 to reacquire the flap electrical position data when the flap control surface is adjusted to the mechanical zero position. If the difference between the first and third data is less than the threshold, and the difference between the first and fourth data is greater than the threshold, repeat steps 1 and 2 to reacquire the flap electrical position data when the flap control surface is adjusted to the mechanical zero position. If the difference between the second and third data is greater than a threshold, and the difference between the second and fourth data is greater than a threshold, and the difference between the first and second data is greater than a threshold, repeat steps 1 and 2 to reacquire the flap electrical position data when the flap control surface is adjusted to the mechanical zero position. If the difference between the second and third data is greater than a threshold, and the difference between the second and fourth data is greater than a threshold, and the difference between the first and second data is less than a threshold, repeat steps 1 and 2 to reacquire the flap electrical position data when the flap control surface is adjusted to the mechanical zero position.

3. The automatic zero-position calibration method for aircraft flap control surfaces according to claim 1, characterized in that, In step 1, when the aircraft is in its initial state, the flap control surfaces are adjusted to the mechanical zero position. Both flap control computers collect the flap electrical position data when the flap control surfaces are adjusted to the mechanical zero position, and store the flap electrical position data when the flap control surfaces are adjusted to the mechanical zero position on the two flap control computers.

4. The automatic zero-position calibration method for aircraft flap control surfaces according to claim 1, characterized in that, The electrical position data of the flaps when the flap control surfaces are adjusted to the mechanical zero position is stored in the NVRAM of the two flap control computers.

5. The automatic zero-position calibration method for aircraft flap control surfaces according to claim 1, characterized in that, In step 2, before the flap control computer sends the flap electrical position data in the flap position data with the invalid flag as the flap zero position data to the back-end crosslinking flap power drive controller, the following steps are also taken: the two flap control computers each determine whether their respective flap control computers and the back-end crosslinking equipment flap power drive controller are communicating normally. If the communication is normal, they determine whether the flap position data uses the flag status.

6. The automatic zero-position calibration method for aircraft flap control surfaces according to claim 1, characterized in that, Step 3, after sending the new flap position zero-point data to the two flap control computers and the two flap power drive controllers, also includes: the two flap control computers and the two flap power drive controllers storing the received new flap position zero-point data.

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