System and method for automatically correcting calculated data deviation of aircraft landing gear control unit

Abstract

The invention discloses an aircraft landing gear control unit resolving data deviation automatic correction system and method, an upper computer carries out parameter configuration and control on an electric control device, and the electric control device controls a servo motor to work, so that the distance between a target and a proximity sensor can be automatically adjusted; an inductance standard value collected by the LCR tester is automatically uploaded to an upper computer through an electric control device, and an inductance calculation value obtained through calculation of each data calculation channel of the aircraft landing gear control unit and the inductance standard value are subjected to automatic linear fitting in the upper computer, so that a correction coefficient of each data calculation channel of the aircraft landing gear control unit is obtained; and the correction coefficient is automatically written into the aircraft landing gear control unit, so that the efficiency of correcting the calculation data deviation of the aircraft landing gear control unit can be greatly improved.

Description

Technical Field

[0001] The invention relates to the technical field of aircraft landing gear control units, and in particular to an automatic correction system and method for deviation of calculated data of an aircraft landing gear control unit. Background Art

[0002] The core functions of the aircraft landing gear control unit are: sending landing gear, door status information, wheel load information, system fault information to DMC through ARINC429 bus, receiving aircraft flight number and other information sent by DMC through ARINC429 bus; providing wheel load signals to other aircraft systems in discrete form; receiving the retraction and extension instructions of the retraction and extension control handle, outputting control commands to the safety valve and selector valve to control the retraction / extension of the landing gear; providing an air unlocking command to the retraction and extension control handle; detecting and processing landing gear and door position sensor signals, etc. The premise for the realization of the above core functions is that the inductance value solution channel of the aircraft landing gear control unit can stably, reliably and accurately solve the inductance value uploaded by the proximity sensor. However, due to the differences or deviations of the ADC sampling circuit, analog signal amplification circuit, filter circuit and other circuits involved in the different inductance value solution channels of the aircraft landing gear control unit, the inductance solution values ​​of the same proximity sensor collected by the aircraft landing gear control unit in different channels have large deviations, which in turn affects the realization of the above core functions.

[0003] Therefore, the industry usually corrects the coefficients of the inductance value solution channel of the aircraft landing gear control unit, so as to optimize the solution data deviation of different channels for the same model or the same proximity sensor. When correcting the coefficients, the commonly used method is: first, manually adjust the different spacings between the proximity sensor and the target position, usually 2 to 7 mm, with an interval of 1 mm, to obtain the original data of the solution inductance value. The same channel of the aircraft landing gear control unit will collect 6 sets of data. Each aircraft landing gear control unit usually has 19 inductance data solution channels. The data collected by the above operation is used as the inductance solution value; then, use the LCR tester to measure the inductance value of the proximity sensor as the inductance standard value; then, the solution value and the standard value are linearly fitted by the least squares method (y=kx+b) to obtain the k value and b value (x and y are the inductance solution value and the inductance standard value, respectively), and then manually write the k value and b value into the aircraft landing gear control unit through a dedicated host computer to complete the writing of the correction coefficient, and finally read the inductance solution value of each channel to complete the function verification test.

[0004] Through the description of the coefficient correction process of the inductance value solution channel of the above-mentioned aircraft landing gear control unit, it can be seen that the traditional method of obtaining the correction coefficient has many disadvantages:

[0005] First, since the aircraft landing gear control unit needs to solve the inductance value for each channel, the number of channels is often not less than 19, and each channel also needs to collect the inductance values ​​of the proximity sensor and the target at different positions, the number of samples is at least 6 groups, and the proximity sensor and the target position are adjusted manually, which makes the process of obtaining the solution value very cumbersome and extremely inefficient;

[0006] Second, after obtaining the inductance solution value of the aircraft landing gear control unit, it is necessary to manually use an LCR tester to obtain the standard inductance value of the proximity sensor at different positions of the target, and then perform the least squares linear fitting of the inductance solution value of different channels with the standard value to obtain the correction coefficients k and b values ​​of different channels. The above operation process is very time-consuming and inefficient.

[0007] Third, after obtaining the k and b values, the correction coefficients must be manually entered into a dedicated host computer and written into the aircraft landing gear control unit, which is also a very cumbersome operation.

[0008] At the same time, in addition to the cumbersome and inefficient operation of the correction coefficient acquisition process mentioned above, there are no authoritative operating specifications and methods in the industry for correcting the deviation of the inductance value solution data of the aircraft landing gear control unit. Summary of the invention

[0009] In view of the above-mentioned deficiencies in the prior art, the present invention provides an automatic correction system and method for deviation of calculated data of an aircraft landing gear control unit, which solves the problems of low efficiency and complicated operation of the existing method for correcting deviation of calculated data of an inductance value of an aircraft landing gear control unit.

[0010] In order to achieve the above-mentioned object of the invention, the technical solution adopted by the present invention is:

[0011] Provided is an automatic correction system for the deviation of calculated data of an aircraft landing gear control unit, which comprises a mechanical motion device, an electric control device and a host computer;

[0012] A mechanical motion device, used to fix the proximity sensor and adjust the distance between the target and the proximity sensor through a servo motor;

[0013] The electronic control device is used to control the operation of the servo motor; control the LCR tester to collect the output signal of the proximity sensor, and transmit the signal collected by the LCR tester as the inductance standard value to the host computer;

[0014] The host computer is used to perform linear fitting between the inductance solution value obtained by solving each data solution channel of the aircraft landing gear control unit and the inductance standard value, obtain the correction coefficient of each data solution channel of the aircraft landing gear control unit, write the correction coefficient into the aircraft landing gear control unit; and perform parameter configuration and control on the electronic control device.

[0015] Furthermore, the mechanical motion device includes a displacement platform, on which a loading platform is slidably arranged; the loading platform is driven by a lead screw guide rail to achieve movement; one end of the lead screw guide rail is fixed to the rotating shaft of the servo motor; the servo motor is connected to the electronic control device through an RS485 communication component;

[0016] The servo motor is located at one end of the displacement platform; the other end of the displacement platform is provided with a proximity sensor fixing component;

[0017] A target moving platform is arranged on the loading platform; a target moving guide rail is arranged on the target moving platform; a target clamp is slidably arranged on the target moving guide rail; and a target clamp locker for fixing the position of the target clamp is arranged on the target clamp.

[0018] Furthermore, the proximity sensor fixing assembly includes a proximity sensor fixing bracket, on which a fastening nut for fixing the proximity sensor is provided; the proximity sensor fixing bracket is provided with a groove for the proximity sensor to pass through; the fastening nut is arranged behind the groove for fixing the nut-fastened proximity sensor.

[0019] Furthermore, the proximity sensor fixing assembly includes a proximity sensor fixing bracket, a groove for the proximity sensor to pass through is provided on the proximity sensor fixing bracket, and clamping structures for clamping the proximity sensor are provided on the proximity sensor fixing bracket and on both sides of the groove; the clamping structure is slidably fixed to the proximity sensor fixing bracket through a fixing block; and the fastening nut fixes the proximity sensor by fixing the clamping structure.

[0020] Further, the electric control device includes a core controller, and a display circuit, a key control circuit, a zeroing circuit, a clock circuit, a switching circuit, a filter circuit, a storage circuit, a power supply circuit, a reset circuit, an RS232 communication interface, a USB communication interface and an RS485 communication interface respectively connected to the core controller for communication;

[0021] A display circuit, used for displaying the radial distance between the target and the proximity sensor, and the movement data of the stage;

[0022] Key control circuit, used for manually controlling the servo motor;

[0023] A zeroing circuit is used to mark the measurement zero position of the mechanical motion device when the axial distance between the end face of the proximity sensor and the end face of the target is 0;

[0024] The clock circuit is used to provide a clock signal for the core controller to work normally;

[0025] A switching circuit is used to switch the transmission channels between the LCR tester and the aircraft landing gear control unit and the proximity sensor, so that the signals of the corresponding proximity sensors at the same position of the loading platform are respectively transmitted to different data solution channels of the LCR tester and the aircraft landing gear control unit;

[0026] A filter circuit, used for filtering the power supply circuit;

[0027] A storage circuit, used to store data generated and received when the electronic control device is working;

[0028] A power supply circuit, used to supply power to the entire electronic control device;

[0029] A reset circuit, used for resetting the electronic control device;

[0030] RS232 communication interface, used to communicate with the host computer;

[0031] USB communication interface, used to communicate with the LCR tester;

[0032] RS485 communication interface, used to connect with RS485 communication components;

[0033] The core controller is used to respond to the parameter configuration and control instructions of the host computer; generate control signals for mechanical motion devices; parse and process communication protocols; and control the caching and transmission of data.

[0034] Further, the host computer includes a mechanical device motion control and displacement data display module, a correction coefficient processing module, a data cache module, a correction coefficient writing module and a solution data display module;

[0035] The mechanical device motion control and displacement data display module sends parameter configuration and control instructions to the electronic control device, including controlling the servo motor to drive the stage to the desired displacement point, controlling the running and stopping time of the servo motor, and setting the step distance between two adjacent displacement points of the stage; and displays the displacement point data of the stage and the use status of the key control circuit in real time;

[0036] A data cache module is used to store the standard inductance value and the calculated inductance value, and to mark a serial number for a group of calculated inductance values ​​corresponding to each data calculation channel of the aircraft landing gear control unit; wherein all the calculated inductance value data of a single data calculation channel starting from the expected displacement point and following a fixed step interval to the cut-off displacement point are grouped as one group;

[0037] The correction coefficient processing module is used to automatically call the inductance solution value and the inductance standard value in the data cache module in batches according to the marked serial number, use the least square method to perform the best straight line fitting, and return the array describing the straight line; wherein the array describing the straight line includes the correction coefficient;

[0038] The correction coefficient writing module is used to ground the mode signal line and the load signal line of the aircraft landing gear control unit, and write the correction coefficient obtained by the correction coefficient processing module into the aircraft landing gear control unit to realize automatic correction of the deviation of the calculated data of the aircraft landing gear control unit;

[0039] The solution data display module is used to perform correction verification after the deviation of the aircraft landing gear control unit solution data is automatically corrected. If the aircraft landing gear control unit solution data after the deviation is automatically corrected is within the error range, it will be displayed that the deviation correction is successful; otherwise, it will be displayed that the deviation correction fails.

[0040] A method for automatically correcting a data deviation based on an aircraft landing gear control unit is provided, which comprises the following steps:

[0041] S1. Parameter configuration of the electronic control device through the host computer;

[0042] S2. Control the mechanical motion device through the electronic control device to make the axial distance Z between the end face of the target and the end face of the proximity sensor zero, lock the target and the proximity sensor; and record the current working data of the servo motor;

[0043] S3, adjusting the target to the desired displacement point by means of a servo motor, collecting the output signal of the proximity sensor at different displacement points by means of an LCR tester, and using the signal as the inductance standard value; obtaining the inductance solution value obtained by solving each data solution channel of the aircraft landing gear control unit at different displacement points;

[0044] S4, linearly fitting the inductance solution value obtained by solving each data solution channel of the aircraft landing gear control unit with the inductance standard value, obtaining the correction coefficient of each data solution channel of the aircraft landing gear control unit, writing the correction coefficient into the aircraft landing gear control unit, and completing the automatic correction of the deviation of the solution data of the aircraft landing gear control unit.

[0045] Furthermore, after step S4, the following steps are also included:

[0046] S5. Correction verification is performed on the calculated data of the aircraft landing gear control unit that has undergone automatic deviation correction. If the calculated data of the aircraft landing gear control unit after the automatic deviation correction is within the error range, it is displayed that the deviation correction is successful; otherwise, it is displayed that the deviation correction fails.

[0047] The beneficial effects of the present invention are:

[0048] 1. The present invention configures and controls parameters of the electronic control device through a host computer, controls the operation of the servo motor through the electronic control device, automatically adjusts the distance between the target and the proximity sensor, and automatically uploads the standard inductance value collected by the LCR tester to the host computer through the electronic control device. In the host computer, the inductance solution value obtained by solving each data solution channel of the aircraft landing gear control unit is automatically linearly fitted with the standard inductance value, the correction coefficient of each data solution channel of the aircraft landing gear control unit is obtained, and the correction coefficient is automatically written into the aircraft landing gear control unit, which can greatly improve the efficiency of the deviation correction of the solution data of the aircraft landing gear control unit.

[0049] 2. This mechanical motion device controls the position of the stage through a servo motor, and fine-tunes the initial distance between the target and the proximity sensor through the target moving platform, which is convenient for the initial positioning of the entire correction. At the same time, it can prevent the target from impacting the emergency sensor during the movement of the stage, forming a stable and reliable test platform.

[0050] 3. The present invention provides proximity sensor fixing components with different structures, so that the mechanical motion device can fix different types of proximity sensors, thereby improving the adaptability of the present invention.

[0051] 4. The present invention can realize the transmission of the signal of the proximity sensor to different data solution channels of the LCR tester and the aircraft landing gear control unit respectively through the switching circuit of the electronic control device. Each data can be classified and stored through the storage circuit and the data cache module, which is convenient for the correction coefficient processing module to perform straight line fitting and realize automatic acquisition of the correction coefficient.

[0052] 5. The present invention provides a circuit for manually controlling a servo motor and a circuit for displaying the radial distance between a target and a proximity sensor, so that a user can flexibly adjust the distance between the target and the proximity sensor according to on-site conditions, thereby improving the flexibility of use of the present invention. BRIEF DESCRIPTION OF THE DRAWINGS

[0053] Figure 1 is the structural block diagram of the device;

[0054] Figure 2 It is a structural schematic diagram of a mechanical motion device;

[0055] Figure 3 A schematic diagram of the structure of a proximity sensor fixing assembly for fixing a nut-tightening type proximity sensor;

[0056] Figure 4 It is a schematic diagram of the second structure of the proximity sensor fixing assembly;

[0057] Figure 5 It is a schematic diagram of the relationship between the end face of the proximity sensor and the target position;

[0058] Figure 6 It is a block diagram of the connection between the electronic control device and other devices;

[0059] Figure 7 This is the structural block diagram of the host computer.

[0060] Among them: 1. servo motor; 2. lead screw guide; 3. stage; 4. target moving platform; 5. target fixture; 6. target moving guide; 7. target fixture locker; 8. proximity sensor fixing bracket; 9. fastening nut; 10. RS485 communication component; 11. displacement platform; 12. clamping structure; 13. fixing block. DETAILED DESCRIPTION

[0061] The specific implementation modes of the present invention are described below so that those skilled in the art can understand the present invention. However, it should be clear that the present invention is not limited to the scope of the specific implementation modes. For those of ordinary skill in the art, as long as various changes are within the spirit and scope of the present invention as defined and determined by the attached claims, these changes are obvious, and all inventions and creations utilizing the concept of the present invention are protected.

[0062] like Figure 1 As shown, the automatic correction system for the deviation of the calculated data of the aircraft landing gear control unit includes a mechanical motion device, an electric control device and a host computer;

[0063] A mechanical motion device, used to fix the proximity sensor and adjust the distance between the target and the proximity sensor through a servo motor 1;

[0064] The electronic control device is used to control the operation of the servo motor 1; control the LCR tester to collect the output signal of the proximity sensor, and transmit the signal collected by the LCR tester as the inductance standard value to the host computer;

[0065] The host computer is used to perform linear fitting between the inductance solution value obtained by solving each data solution channel of the aircraft landing gear control unit and the inductance standard value, obtain the correction coefficient of each data solution channel of the aircraft landing gear control unit, write the correction coefficient into the aircraft landing gear control unit; and perform parameter configuration and control on the electronic control device.

[0066] like Figure 2 As shown, the mechanical motion device includes a displacement platform 11, on which a loading platform 3 is slidably provided; the loading platform 3 is driven by a lead screw guide rail 2 to achieve movement; one end of the lead screw guide rail 2 is fixed to the rotating shaft of the servo motor 1; the servo motor 1 is connected to the electronic control device through an RS485 communication component 10;

[0067] The servo motor 1 is located at one end of the displacement platform 11; the other end of the displacement platform 11 is provided with a proximity sensor fixing assembly;

[0068] A target moving platform 4 is arranged on the stage 3; a target moving guide rail 6 is arranged on the target moving platform 4; a target fixture 5 is slidably arranged on the target moving guide rail 6; and a target fixture locker 7 for fixing the position of the target fixture 5 is arranged on the target fixture 5.

[0069] In one solution of this embodiment, Figure 3 As shown, the proximity sensor fixing assembly includes a proximity sensor fixing bracket 8, on which a fastening nut 9 for fixing the proximity sensor is provided; the proximity sensor fixing bracket 8 is provided with a groove for the proximity sensor to pass through; the fastening nut 9 is arranged behind the groove for fixing the nut-fastened proximity sensor.

[0070] When using Figure 5 When the proximity sensor with thread is shown, the proximity sensor is fixed on the proximity sensor fixing bracket 8 by tightening the nut 9; after the proximity sensor is fixed, the corresponding appropriate target is inserted into the target fixture 5, and then the radial distance X of the target fixture 5 fixing the target is adjusted. The adjustment principle is that the overlap area between the end face of the proximity sensor and the end face of the target is as large as possible to ensure that the output inductance value of the proximity sensor is stable and accurate. Next, move the stage 3 to the rightmost starting point of the displacement platform 11, and then move the target fixture 5 on the target moving guide rail 6, and adjust the axial distance Z between the end face of the target and the end face of the proximity sensor to zero. At this time, turn the target fixture lock 7 to lock the position of the target. After locking the relative position of the proximity sensor and the target, the axial distance between the two is zero at this time, and the electronic control device sends a zeroing instruction through the RS485 communication component 10, and the host computer sends a zeroing instruction to the electronic control device, and the electronic control device controls the mechanical motion device to mark this position as the displacement zero point (counting zero point). Next, the servo motor 1 drives the stage 3 to automatically complete the desired displacement change on the lead screw guide rail 2 according to the movement command sent by the electronic control device, thereby completing the data collection of the inductance solution value and the inductance standard value at different desired displacements. Due to the combination of high-precision servo motor 1 and lead screw guide rail 2, the position repeatability of the stage 3 is ±0.01mm, and the moving speed of the stage 3 is automatically adjustable, with a maximum moving speed of 500mm / s.

[0071] In actual use, in addition to Figure 5 In addition to the threaded proximity sensor shown in the figure, there is also a non-threaded proximity sensor. In this case, a fixing bracket capable of adapting to the size of the proximity sensor is required. Therefore, in another solution of this embodiment, as shown in FIG. Figure 4As shown, the proximity sensor fixing assembly includes a proximity sensor fixing bracket 8, on which a groove for the proximity sensor to pass through is provided, and on the proximity sensor fixing bracket 8 and on both sides of the groove are provided a clamping structure 12 for clamping the proximity sensor; the clamping structure 12 is slidably fixed on the proximity sensor fixing bracket 8 by a fixing block 13; and the fastening nut 9 fixes the proximity sensor by fixing the clamping structure 12.

[0072] When it is a proximity sensor without threads, one end of the proximity sensor with the support structure is placed against one end of the proximity sensor fixing bracket 8, and then the protruding part of the proximity sensor is fixed in position at the other end of the proximity sensor fixing bracket 8 using the clamping structure 12. At this time, the position of the clamping structure 12 passing through the fixing block 13 is determined, and then the fastening nut 9 is tightened to tighten the clamping structure 12, so that the position of the proximity sensor without threads can be locked. The subsequent operations are the same as the steps for automatically collecting the inductance solution value and the standard value of the proximity sensor with threads, and will not be repeated here.

[0073] like Figure 6 As shown, the electronic control device includes a core controller (MCU), and a display circuit, a key control circuit, a zeroing circuit, a clock circuit, a switching circuit, a filter circuit, a storage circuit, a power supply circuit, a reset circuit, an RS232 communication interface, a USB communication interface and an RS485 communication interface respectively connected to the core controller for communication;

[0074] Display circuit, the main carrier of which is an OLED display screen, used to display the radial distance between the target and the proximity sensor, and the movement data of the stage 3;

[0075] The button control circuit is used to manually control the servo motor 1; in the present embodiment, the function of this circuit is to manually control the stage 3 on the mechanical motion device to move to the designated position driven by the servo motor 1 and the lead screw guide 2 through the 10 buttons provided, and each button corresponds to a displacement distance, for example: button 1 corresponds to a movement of 1mm, button 2 corresponds to 2mm, and so on, button 10 corresponds to a movement of 10mm. The distances corresponding to the buttons can be adjusted dynamically, and the upper computer sends a step adjustment instruction (parameter configuration) to the button control circuit, and the button control circuit synchronously changes the interval displacement between the buttons, for example: sending an instruction to adjust the interval step to 2mm, then button 1 corresponds to a movement of 1mm, and button 2 corresponds to a movement of 3mm, and so on, the corresponding movement distance of button 10 is 19mm. The purpose of setting this circuit is to prevent operations when the upper computer control of the movement displacement fails and when automatic control of the movement displacement is not needed;

[0076] A zeroing circuit is used to mark the measurement zero position of the mechanical motion device when the axial distance between the end face of the proximity sensor and the end face of the target is 0;

[0077] The clock circuit is used to provide a clock signal for the core controller to work normally;

[0078] The switching circuit is mainly composed of various types of relays, and is used to switch the transmission channels between the LCR tester and the aircraft landing gear control unit and the proximity sensor, so that the signals of the proximity sensors corresponding to the same position of the loading platform 3 are respectively transmitted to different data solution channels of the LCR tester and the aircraft landing gear control unit;

[0079] A filter circuit, used for filtering the power supply circuit;

[0080] The storage circuit uses two large-capacity NANDFLASH as the basic carrier to store the data generated and received when the electronic control device is working;

[0081] A power supply circuit, used to supply power to the entire electronic control device;

[0082] Reset circuit, used to reset the electronic control device; reset can be automatic reset after abnormal program operation timeout, and can also be reset by pressing a manual button;

[0083] RS232 communication interface, used for communicating with the host computer; the communication content includes receiving the command sent by the host computer to automatically control the mechanical motion device to change the displacement, and then transmitting the command to the MCU for analysis; receiving the command sent by the host computer to adjust the corresponding interval step of the button of the key control circuit or any other command, and then transmitting the command to the MCU for analysis; uploading the current movement displacement value of the stage 3 to the host computer; feeding back the status of whether the button in the key control circuit is pressed to the host computer; at the same time, the standard inductance value of the proximity sensor measured by the LCR tester obtained by the MCU can be transmitted to the host computer;

[0084] USB communication interface, used to communicate with the LCR tester; the communication content includes receiving the SCPI command based on the VISA protocol sent by the MCU, the program-controlled LCR tester measures the inductance value of the proximity sensor, and then transmits the measured inductance standard value to the MCU, and the MCU caches these data into the storage circuit for easy access by the host computer at any time;

[0085] RS485 communication interface, used to connect with RS485 communication component 10, transmit zeroing instruction, transmit instruction sent by MCU to mechanical motion device, control the operation of servo motor 1 of mechanical motion device, and then drive lead screw guide rail 2 to make stage 3 move stably, accurately and automatically;

[0086] The core controller, as the center of the entire electronic control device, is responsible for sending control instructions, caching and transmitting control collected data, parsing and processing communication protocols, etc., including responding to parameter configuration and control instructions of the host computer; generating mechanical motion device control signals; parsing and processing communication protocols; and caching and transmitting control data.

[0087] In the specific implementation process, the execution flow of the electronic control device is as follows: the electronic control device is powered on normally, and the power indicator light and program running indicator light work normally. Under the above premise, first, the relative position between the proximity sensor and the target on the mechanical motion device is adjusted to 0, and the host computer sends a control instruction to the MCU through the RS232 interface, so that the MCU sends a zeroing instruction to let the mechanical motion device mark the counting zero point; then, the host computer sends an instruction to the MCU to control the switching circuit to let the corresponding relay close the channel for the aircraft landing gear control unit to collect proximity sensor data, and then switch the relay conduction circuit to connect the LCR tester to the proximity sensor; then, the host computer sets the interval step between adjacent displacement points, and this step is synchronously updated to the step interval between adjacent buttons of the key control circuit, and then sends an instruction to automatically collect the standard inductance value to the MCU; next, the MCU controls the stage 3 on the mechanical motion device to move according to the specified displacement step, and each time it moves to a displacement point, the stage 3 stops running for 800ms. During this period of time, the LCR tester completes the inductance value collection of this displacement point and transmits it to the MCU through the USB interface circuit for test data caching. Each time the stage 3 reaches a desired displacement point, the OLED screen of the display circuit will display the displacement distance of the current stage 3, and the synchronous MCU will upload the displacement value of the current stage 3 from the zero point to the host computer through the RS232 interface circuit for display. If the button control circuit controls the slider to move, the host computer will display which button is currently pressed while displaying the displacement distance of the current stage 3; the operation is automatically repeated. When the standard inductance values ​​of all the desired displacement points are collected, the MCU sends an identifier indicating that all the desired displacement points have been traversed to the host computer. After receiving this identifier, the host computer sends a command to stop collecting the standard inductance value; then, after a delay of 500ms, the host computer sends a zeroing command to the mechanical motion device to the MCU, and the stage 3 runs to the counting zero point.

[0088] Next, the host computer sends an instruction to the MCU to control the switching circuit to open the corresponding relay, so that a solution data channel of the aircraft landing gear control unit can collect the inductance solution data of the proximity sensor, and then switch the relay to disconnect the connection path between the LCR tester and the proximity sensor; then, the host computer sets the interval step between adjacent displacement points, and this step is synchronously updated to the step interval between adjacent buttons of the key control circuit, and then sends an instruction to automatically collect the solution inductance value to the MCU; next, the MCU controls the stage 3 on the mechanical motion device to move according to the specified displacement step, and each time it moves to a displacement point, the stage 3 stops running for 1000ms. During this period of time, the aircraft landing gear control unit can stably and reliably measure the data of the proximity sensor and cache it in the database of the host computer; each time the stage 3 reaches a desired displacement point, the OLED screen of the display circuit will display the displacement distance of the current movement of the stage 3, and the synchronous MCU will upload the displacement value of the current distance zero point of the stage 3 to the host computer through the RS232 interface circuit for display. If the button control circuit controls the slider to move, the host computer will display the displacement distance of the current standard slider and which button is currently pressed to automatically repeat the operation. When the calculated inductance values ​​of all expected displacement points are collected by the aircraft landing gear control unit and cached in the database of the host computer, the MCU sends an identifier indicating that all expected displacement points have been traversed to the host computer. After receiving this identifier, the host computer sends a command to stop collecting the calculated inductance value. Next, the host computer sends a command to let the switching circuit connect to the next calculated data channel of the aircraft landing gear control unit, repeat the above-mentioned steps of collecting the calculated inductance value, and repeat the cycle until the original data of the calculated inductance values ​​of all the calculated data channels of the aircraft landing gear control unit are collected.

[0089] After the electronic control device executes the above steps, the host computer can obtain the solved inductance value of each solved data channel of the aircraft landing gear control unit at each expected displacement point and the standard inductance value measured by the LCR tester at each expected displacement point.

[0090] like Figure 7 As shown, the host computer includes a mechanical device motion control and displacement data display module, a correction coefficient processing module, a data cache module, a correction coefficient writing module and a solution data display module;

[0091] The mechanical device motion control and displacement data display module sends parameter configuration and control instructions to the electronic control device, including controlling the servo motor 1 to drive the stage 3 to the desired displacement point, controlling the running and stopping time of the servo motor 1, and setting the step distance between two adjacent displacement points of the stage 3; and displays the displacement point data of the stage 3 and the use status of the key control circuit in real time;

[0092] The data cache module is used to store the standard inductance value and the calculated inductance value, and to mark a group of calculated inductance values ​​corresponding to each data calculation channel of the aircraft landing gear control unit with a serial number; wherein all the calculated inductance value data of a single data calculation channel from the expected displacement point to the cut-off displacement point at a fixed step interval is a group; in this embodiment, the data cache module adopts an open source relational database management system MySQL database;

[0093] The correction coefficient processing module is used to automatically call the inductance solution value and the inductance standard value in the data cache module in batches according to the marked serial number, use the least square method to perform the best straight line fitting, and return the array describing the straight line; the array describing the straight line includes the correction coefficient k and b values; the obtained correction coefficient will be saved according to the batch number and stage number of the aircraft landing gear control unit, which is convenient for subsequent direct calling to avoid repeated correction of products of the same model and batch. At the same time, data backup and archiving can also be performed to facilitate troubleshooting after a fault occurs;

[0094] The correction coefficient writing module is used to make the mode signal line and load signal line of the aircraft landing gear control unit in the grounded state, and automatically write the correction coefficients k and b values ​​obtained by the correction coefficient processing module into the aircraft landing gear control unit through the RS232 interface, so as to realize the automatic correction of the deviation of the solution data of the aircraft landing gear control unit; in the specific implementation process, there are two types of triggering events for writing the correction coefficients to the aircraft landing gear control unit. The first type: after the correction coefficients of all solution data channels are obtained, the correction coefficients are automatically written after a delay of 1000ms; the second type: directly call the existing correction coefficients of the data buffer module to automatically write. Among them, there are two sources of the correction coefficients k and b values: the first is transmitted from the correction coefficient processing module, and the second is to directly call the correction coefficients stored in the data buffer module and automatically write the correction coefficients;

[0095] The solution data display module is used to perform correction verification after the deviation of the solution data of the aircraft landing gear control unit is automatically corrected, that is, by comparing the inductance value measured by the LCR tester with the inductance value of the proximity sensor at the specified displacement collected by each solution channel after the deviation of the solution data of the aircraft landing gear control unit is automatically corrected. If the solution data of the aircraft landing gear control unit after the deviation is automatically corrected is within the error range, it is displayed that the deviation correction is successful; otherwise, it is displayed that the deviation correction fails.

[0096] In this embodiment, the method for automatically correcting the data deviation based on the aircraft landing gear control unit includes the following steps:

[0097] S1. Parameter configuration of the electronic control device through the host computer;

[0098] S2. Control the mechanical motion device through the electronic control device so that the axial distance Z between the end face of the target and the end face of the proximity sensor is zero, and lock the target and the proximity sensor; record the current working data of the servo motor 1;

[0099] S3, adjusting the target to the desired displacement point by the servo motor 1, collecting the output signal of the proximity sensor at different displacement points by the LCR tester, and using it as the inductance standard value; obtaining the inductance solution value obtained by solving each data solution channel of the aircraft landing gear control unit at different displacement points;

[0100] S4, performing linear fitting on the inductance solution value obtained by solving each data solution channel of the aircraft landing gear control unit and the inductance standard value, obtaining the correction coefficient of each data solution channel of the aircraft landing gear control unit, writing the correction coefficient into the aircraft landing gear control unit, and completing the automatic correction of the deviation of the solution data of the aircraft landing gear control unit;

[0101] S5. Correction verification is performed on the calculated data of the aircraft landing gear control unit that has undergone automatic deviation correction. If the calculated data of the aircraft landing gear control unit after the automatic deviation correction is within the error range, it is displayed that the deviation correction is successful; otherwise, it is displayed that the deviation correction fails.

[0102] In summary, the present invention configures and controls parameters of the electronic control device through the host computer, controls the servo motor 1 to work through the electronic control device, automatically adjusts the distance between the target and the proximity sensor, and automatically uploads the standard inductance value collected by the LCR tester to the host computer through the electronic control device. In the host computer, the inductance solution value obtained by each data solution channel of the aircraft landing gear control unit is automatically linearly fitted with the inductance standard value, the correction coefficient of each data solution channel of the aircraft landing gear control unit is obtained, and the correction coefficient is automatically written into the aircraft landing gear control unit, which can greatly improve the efficiency of the aircraft landing gear control unit in correcting the deviation of the solution data.

Claims

1. An automatic correction system for deviation of calculated data of an aircraft landing gear control unit, characterized in that: It includes mechanical motion device, electric control device and host computer; A mechanical motion device, used for fixing the proximity sensor and adjusting the distance between the target and the proximity sensor through a servo motor (1); The electric control device is used to control the operation of the servo motor (1); control the LCR tester to collect the output signal of the proximity sensor, and transmit the signal collected by the LCR tester as the inductance standard value to the host computer; The host computer is used to perform linear fitting between the inductance solution value obtained by solving each data solution channel of the aircraft landing gear control unit and the inductance standard value, obtain the correction coefficient of each data solution channel of the aircraft landing gear control unit, and write the correction coefficient into the aircraft landing gear control unit; Configure and control parameters of the electronic control device.

2. The automatic correction system for aircraft landing gear control unit calculation data deviation according to claim 1, characterized in that: The mechanical motion device comprises a displacement platform (11), on which a loading platform (3) is slidably arranged; the loading platform (3) is driven by a lead screw guide rail (2) to achieve movement; one end of the lead screw guide rail (2) is fixed to the rotating shaft of a servo motor (1); the servo motor (1) is connected to the electronic control device through an RS485 communication component (10); The servo motor (1) is located at one end of the displacement platform (11); a proximity sensor fixing component is provided at the other end of the displacement platform (11); A target moving platform (4) is arranged on the object carrier (3); a target moving guide rail (6) is arranged on the target moving platform (4); a target clamp (5) is slidably arranged on the target moving guide rail (6); and a target clamp locker (7) for fixing the position of the target clamp (5) is arranged on the target clamp (5).

3. The automatic correction system for the deviation of calculated data of the aircraft landing gear control unit according to claim 2, characterized in that: The proximity sensor fixing assembly comprises a proximity sensor fixing bracket (8), on which a fastening nut (9) for fixing the proximity sensor is arranged; the proximity sensor fixing bracket (8) is provided with a slot for the proximity sensor to pass through; and the fastening nut (9) is arranged behind the slot and is used to fix the nut-fastened proximity sensor.

4. The automatic correction system for the deviation of calculated data of an aircraft landing gear control unit according to claim 2, characterized in that: The proximity sensor fixing assembly comprises a proximity sensor fixing bracket (8), a groove for the proximity sensor to pass through is arranged on the proximity sensor fixing bracket (8), and a clamping structure (12) for clamping the proximity sensor is arranged on both sides of the groove on the proximity sensor fixing bracket (8); the clamping structure (12) is slidably fixed on the proximity sensor fixing bracket (8) through a fixing block (13); and a fastening nut (9) fixes the proximity sensor by fixing the clamping structure (12).

5. The automatic correction system for the deviation of calculated data of an aircraft landing gear control unit according to claim 2, characterized in that: The electric control device includes a core controller, and a display circuit, a key control circuit, a zeroing circuit, a clock circuit, a switching circuit, a filter circuit, a storage circuit, a power supply circuit, a reset circuit, an RS232 communication interface, a USB communication interface and an RS485 communication interface respectively connected to the core controller for communication; A display circuit, used for displaying the radial distance between the target and the proximity sensor, and the movement data of the stage (3); A key control circuit for manually controlling a servo motor (1); A zeroing circuit is used to mark the measurement zero position of the mechanical motion device when the axial distance between the end face of the proximity sensor and the end face of the target is 0; The clock circuit is used to provide a clock signal for the core controller to work normally; A switching circuit is used to switch the transmission channels between the LCR tester and the aircraft landing gear control unit and the proximity sensor, so that the signals of the corresponding proximity sensors at the same position of the loading platform (3) are respectively transmitted to different data solution channels of the LCR tester and the aircraft landing gear control unit; A filter circuit, used for filtering the power supply circuit; A storage circuit, used to store data generated and received when the electronic control device is working; A power supply circuit, used to supply power to the entire electronic control device; A reset circuit, used for resetting the electronic control device; RS232 communication interface, used to communicate with the host computer; USB communication interface, used to communicate with the LCR tester; RS485 communication interface, used for connecting with RS485 communication component (10); The core controller is used to respond to the parameter configuration and control instructions of the host computer; generate control signals for mechanical motion devices; parse and process communication protocols; and control the caching and transmission of data.

6. The automatic correction system for the deviation of calculated data of the aircraft landing gear control unit according to claim 5, characterized in that: The host computer includes a mechanical device motion control and displacement data display module, a correction coefficient processing module, a data cache module, a correction coefficient writing module and a solution data display module; The mechanical device motion control and displacement data display module sends parameter configuration and control instructions to the electronic control device, including controlling the servo motor (1) to drive the loading platform (3) to the desired displacement point, controlling the running and stopping time of the servo motor (1), and setting the step length interval between two adjacent displacement points of the loading platform (3); and displaying the displacement point data of the loading platform (3) and the use status of the key control circuit in real time; A data cache module is used to store the standard inductance value and the calculated inductance value, and to mark a serial number for a group of calculated inductance values ​​corresponding to each data calculation channel of the aircraft landing gear control unit; wherein all the calculated inductance value data of a single data calculation channel starting from the expected displacement point and following a fixed step interval to the cut-off displacement point are grouped as one group; The correction coefficient processing module is used to automatically call the inductance solution value and the inductance standard value in the data cache module in batches according to the marked serial number, use the least squares method to perform the best straight line fitting, and return the array describing this straight line; The array describing this line contains the correction coefficients; The correction coefficient writing module is used to ground the mode signal line and the load signal line of the aircraft landing gear control unit, and write the correction coefficient obtained by the correction coefficient processing module into the aircraft landing gear control unit to realize automatic correction of the deviation of the calculated data of the aircraft landing gear control unit; The solution data display module is used to perform correction verification after the deviation of the aircraft landing gear control unit solution data is automatically corrected. If the aircraft landing gear control unit solution data after the deviation is automatically corrected is within the error range, it will be displayed that the deviation correction is successful; otherwise, it will be displayed that the deviation correction fails.

7. A method for automatically correcting a data deviation of an aircraft landing gear control unit according to any one of claims 1 to 6, characterized in that: The following steps are involved: S1. Parameter configuration of the electronic control device through the host computer; S2, controlling the mechanical motion device through the electronic control device so that the axial distance Z between the end face of the target and the end face of the proximity sensor is zero, locking the target and the proximity sensor; recording the current working data of the servo motor (1); S3, adjusting the target to a desired displacement point by means of a servo motor (1), collecting output signals of the proximity sensor at different displacement points by means of an LCR tester, and using the output signals as standard inductance values; obtaining inductance solution values ​​obtained by solving each data solution channel of the aircraft landing gear control unit at different displacement points; S4, linearly fitting the inductance solution value obtained by solving each data solution channel of the aircraft landing gear control unit with the inductance standard value, obtaining the correction coefficient of each data solution channel of the aircraft landing gear control unit, writing the correction coefficient into the aircraft landing gear control unit, and completing the automatic correction of the deviation of the solution data of the aircraft landing gear control unit.

8. The method according to claim 7, characterized in that Step S4 further includes the following steps: S5. Correction verification is performed on the calculated data of the aircraft landing gear control unit that has undergone automatic deviation correction. If the calculated data of the aircraft landing gear control unit after the automatic deviation correction is within the error range, it is displayed that the deviation correction is successful; otherwise, it is displayed that the deviation correction fails.

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