System and method for automatic correction of data bias for aircraft landing gear control unit

Abstract

The application discloses an automatic correction system and method for solving data deviation of an airplane landing gear control unit, wherein a host computer is used to configure and control an electric control device, the electric control device is used to control the operation of a servo motor, the distance between a target and a proximity sensor can be automatically adjusted, the inductance standard value collected by an LCR tester is automatically uploaded to the host computer through the electric control device, the inductance solving value obtained by solving each data solving channel of the airplane landing gear control unit is automatically linearly fitted with the inductance standard value in the host computer, the correction coefficient of each data solving channel of the airplane landing gear control unit is obtained, and the correction coefficient is automatically written into the airplane landing gear control unit, so that the efficiency of correcting the solving data deviation of the airplane landing gear control unit can be greatly improved.

Description

TECHNICAL FIELD

[0001] The present application relates to the technical field of aircraft landing gear control unit, and particularly relates to a system and method for automatically correcting data deviation of an aircraft landing gear control unit. BACKGROUND

[0002] The core function of the aircraft landing gear control unit of an aircraft is to send landing gear, cabin door state information, wheel load information, system fault information to the DMC through the ARINC429 bus, receive the flight number information sent by the DMC through the ARINC429 bus, provide wheel load signals to other systems of the aircraft in the form of discrete quantities, receive the retracting and extending command of the retracting and extending handle, output control commands to the safety valve and selection valve to control the retracting and extending of the landing gear, provide the air unlocking command to the retracting and extending handle, and detect and process the landing gear and cabin door position sensor signals. The prerequisite for realizing the above core function is that the inductance value solving 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 and filter circuit of different inductance value solving channels of the aircraft landing gear control unit, the inductance solving values of the same proximity sensor collected by different channels of the aircraft landing gear control unit have large deviations, which affects the realization of the above core function.

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

[0004] From the description of the coefficient correction process of the inductance value solving channel of the above aircraft landing gear control unit, it can be seen that the traditional method of obtaining correction coefficients has many drawbacks.

[0005] First, since the aircraft landing gear control unit needs to calculate the inductance value of each channel, the number of channels is often no less than 19, and the inductance value of the proximity sensor and the target at different positions needs to be collected for each channel, with at least 6 groups of samples, and the adjustment of the proximity sensor and the target position is entirely manual, which makes the process of obtaining the calculation value very complicated and extremely inefficient.

[0006] Second, after obtaining the inductance calculation value of the aircraft landing gear control unit, the standard inductance value of the proximity sensor and the target at different positions needs to be obtained manually using the LCR tester, and then the inductance calculation value of different channels and the standard value need to be linearly fitted by the least squares method to obtain the correction coefficients k and b value of different channels. The above operation process is very time-consuming and very inefficient.

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

[0008] At the same time, in addition to the problems of complicated operation and low efficiency in the above correction coefficient acquisition process, there is no authoritative operation specification and method for correcting the inductance calculation data deviation of the aircraft landing gear control unit. SUMMARY

[0009] In view of the above deficiencies in the prior art, the aircraft landing gear control unit calculation data deviation automatic correction system and method provided by the present application solves the problem of low efficiency and complicated operation in the existing aircraft landing gear control unit inductance calculation data deviation correction method.

[0010] In order to achieve the above invention purpose, the technical scheme adopted by the present application is:

[0011] An aircraft landing gear control unit calculation data deviation automatic correction system is provided, which comprises a mechanical motion device, an electric control device and a host computer.

[0012] The mechanical motion device is used to fix the proximity sensor and adjust the distance between the target and the proximity sensor through a servo motor.

[0013] The electric 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 to the host computer as the inductance standard value.

[0014] The host computer is used to linearly fit the inductance calculation value obtained by each data calculation channel of the aircraft landing gear control unit with the inductance standard value, obtain the correction coefficient of each data calculation channel of the aircraft landing gear control unit, write the correction coefficient into the aircraft landing gear control unit, and configure and control the electric control device.

[0015] Further, the mechanical movement device comprises a displacement platform, a carrier platform being slidably arranged on the displacement platform; the carrier platform is driven to move by a screw rod guide rail; one end of the screw rod guide rail is fixed with a rotating shaft of a servo motor; the servo motor is in communication connection with the electric control device through an RS485 communication assembly;

[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 assembly;

[0017] The carrier platform is provided with a target moving platform; the target moving platform is provided with a target moving guide rail; a target clamp is slidably arranged on the target moving guide rail; the target clamp is provided with a target clamp locker for fixing the position of the target clamp.

[0018] Further, the proximity sensor fixing assembly comprises a proximity sensor fixing bracket, the proximity sensor fixing bracket is provided with a fastening nut for fixing the proximity sensor; the proximity sensor fixing bracket is provided with a slot for the proximity sensor to pass through; the fastening nut is arranged behind the slot for fixing the screw nut type proximity sensor.

[0019] Further, the proximity sensor fixing assembly comprises a proximity sensor fixing bracket, the proximity sensor fixing bracket is provided with a slot for the proximity sensor to pass through, and the proximity sensor fixing bracket is provided with a clamping structure on both sides of the slot for clamping the proximity sensor; the clamping structure is slidably fixed on the proximity sensor fixing bracket through a fixing block; the fastening nut fixes the proximity sensor by fixing the clamping structure.

[0020] Further, the electric control device comprises a core controller, and a display circuit, a key control circuit, a zeroing circuit, a clock circuit, a switching circuit, a filtering circuit, a storage circuit, a power supply circuit, a reset circuit, an RS232 communication interface, a USB communication interface and an RS485 communication interface which are in communication connection with the core controller respectively;

[0021] The display circuit is used for displaying the radial distance between the target and the proximity sensor, and the movement data of the carrier platform;

[0022] The key control circuit is used for manually controlling the servo motor;

[0023] The zeroing circuit is used for marking the measurement zero point position of the mechanical movement device when the axial distance between the end surface of the proximity sensor and the end surface of the target is 0;

[0024] The clock circuit is used for providing a normal working clock signal for the core controller;

[0025] Switching circuit, for switching transmission channel between LCR tester and landing gear control unit and proximity sensor, so that the signal of corresponding proximity sensor at the same position is transmitted to different data solving channels of LCR tester and landing gear control unit respectively;

[0026] Filter circuit, for filtering power supply circuit;

[0027] Storage circuit, for storing data generated during the operation of the electric control device and received data;

[0028] Power supply circuit, for supplying power to the entire electric control device;

[0029] Reset circuit, for resetting the electric control device;

[0030] RS232 communication interface, for communicating with the host computer;

[0031] USB communication interface, for communicating with the LCR tester;

[0032] RS485 communication interface, for interfacing with the RS485 communication component;

[0033] Core controller, for responding to parameter configuration and control instructions of the host computer; generating mechanical motion device control signals; analyzing and processing communication protocols; controlling data caching and transmission.

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

[0035] Mechanical device motion control and displacement data display module, for sending parameter configuration and control instructions to the electric 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, setting the step distance between the adjacent two displacement points of the stage; real-time display of the displacement point data of the stage and the usage state of the key control circuit;

[0036] Data caching module, for storing inductance standard values and inductance calculation values, and marking serial numbers for each group of inductance calculation values corresponding to each data solving channel of the landing gear control unit; wherein all inductance calculation values data from the desired displacement point to the cutoff displacement point at fixed step intervals for a single data solving channel form a group;

[0037] Correction coefficient processing module, for automatically calling inductance calculation values and inductance standard values in the data caching module in batches according to the marked serial numbers, using the least square method for optimal straight line fitting, and returning an array describing the straight line; wherein the array describing the straight line contains correction coefficients;

[0038] The correction coefficient writing module is used for grounding mode signal lines and load signal lines of the aircraft landing gear control unit, and writing the correction coefficient obtained by the correction coefficient processing module into the aircraft landing gear control unit, so as to realize automatic correction of the calculation data deviation of the aircraft landing gear control unit.

[0039] The calculation data display module is used for verifying the correction after the calculation data deviation of the aircraft landing gear control unit is automatically corrected, and if the calculation data deviation of the aircraft landing gear control unit after the automatic correction is within an error range, the correction is successful, otherwise, the correction is failed.

[0040] The application provides a method for automatically correcting the calculation data deviation of an aircraft landing gear control unit, which comprises the following steps:

[0041] S1, configuring parameters of an electric control device through an upper computer;

[0042] S2, controlling a mechanical motion device through the electric control device, so that the axial distance Z between an end surface of a target and an end surface of a proximity sensor is zero, the target and the proximity sensor are locked, and current working data of a servo motor are recorded;

[0043] S3, adjusting the target to a desired displacement point through the servo motor, collecting output signals of the proximity sensor at different displacement points through an LCR tester, and taking the output signals as inductance standard values, and obtaining inductance calculation values obtained by each data calculation channel of the aircraft landing gear control unit at different displacement points;

[0044] S4, linearly fitting the inductance calculation values obtained by each data calculation channel of the aircraft landing gear control unit and the inductance standard values, obtaining correction coefficients of each data calculation channel of the aircraft landing gear control unit, writing the correction coefficients into the aircraft landing gear control unit, and completing the automatic correction of the calculation data deviation of the aircraft landing gear control unit.

[0045] Further, the step S4 further comprises the following step:

[0046] S5, verifying the correction of the calculation data of the aircraft landing gear control unit after the automatic correction of the deviation, if the calculation data of the aircraft landing gear control unit after the automatic correction of the deviation is within an error range, the correction is successful, otherwise, the correction is failed.

[0047] The application has the following beneficial effects:

[0048] 1. The present invention configures and controls parameters of an electronic control device through a host computer, controls the operation of a servo motor through the electronic control device, automatically adjusts the distance between a target and a proximity sensor, and automatically uploads the standard inductance value collected by an LCR tester to the host computer through the electronic control device. In the host computer, the inductance solution values ​​obtained by solving each data solution channel of the aircraft landing gear control unit are automatically linearly fitted with the standard inductance value, and correction coefficients for each data solution channel of the aircraft landing gear control unit are obtained. The correction coefficients are automatically written into the aircraft landing gear control unit, which can greatly improve the efficiency of correcting deviations in 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 facilitates the initial positioning of the entire correction and prevents 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 assemblies 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 transmit the proximity sensor signal to different data calculation 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 facilitates 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 the servo motor and a circuit for displaying the radial distance between the target and the proximity sensor, so that the user can flexibly adjust the distance between the target and the proximity sensor according to the on-site conditions, thereby improving the flexibility of the present invention. BRIEF DESCRIPTION OF THE DRAWINGS

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

[0054] Figure 2 It is a structural 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 A schematic diagram of a second structure of a proximity sensor fixing assembly;

[0057] Figure 5 Schematic diagram of the relationship between the proximity sensor end face and the target position;

[0058] Figure 6 The connection diagram of the electric control device and other devices;

[0059] Figure 7 The structure diagram of the upper computer.

[0060] 1, servo motor; 2, screw guide rail; 3, object table; 4, target moving platform; 5, target clamp; 6, target moving guide rail; 7, target clamp locker; 8, proximity sensor fixing support; 9, fastening nut; 10, RS485 communication assembly; 11, displacement platform; 12, clamping structure; 13, fixed block. DETAILED DESCRIPTION

[0061] The specific embodiments of the present application are described below to facilitate the understanding of the present application by those skilled in the art, but it should be clear that the present application is not limited to the scope of the specific embodiments, and for those skilled in the art, as long as various changes are within the spirit and scope of the present application defined and determined by the appended claims, all the inventions utilizing the concept of the present application are within the scope of protection.

[0062] As shown in the figure, the aircraft landing gear control unit data deviation automatic correction system comprises a mechanical movement device, an electric control device and an upper computer; Figure 1

[0063] The mechanical movement device is used for fixing the proximity sensor and adjusting the distance between the target and the proximity sensor through the servo motor 1.

[0064] The electric control device is used for controlling the work of the servo motor 1; controlling the LCR tester to collect the output signal of the proximity sensor, and transmitting the signal collected by the LCR tester to the upper computer as the inductance standard value;

[0065] The upper computer is used for linearly fitting the inductance calculation value obtained by each data calculation channel of the aircraft landing gear control unit with the inductance standard value, obtaining the correction coefficient of each data calculation channel of the aircraft landing gear control unit, writing the correction coefficient into the aircraft landing gear control unit, and performing parameter configuration and control on the electric control device.

[0066] As shown in the figure, the mechanical movement device comprises a displacement platform 11, and the object table 3 is slidably arranged on the displacement platform 11; the object table 3 is driven to move by the screw guide rail 2; one end of the screw guide rail 2 is fixed with the rotating shaft of the servo motor 1; the servo motor 1 is in communication connection with the electric control device through the RS485 communication assembly 10; Figure 2 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;

[0067]

[0068] ​​The target moving platform 4 is arranged on the object table 3; the target moving guide rail 6 is arranged on the target moving platform 4; the target clamp 5 is slidably arranged on the target moving guide rail 6; and the target clamp lock 7 is arranged on the target clamp 5 to fix the position of the target clamp 5.

[0069] In one scheme of the embodiment, as shown in Figure 3 The proximity sensor fixing assembly comprises a proximity sensor fixing support 8, and a fastening nut 9 is arranged on the proximity sensor fixing support 8 to fix the proximity sensor; a slot is arranged on the proximity sensor fixing support 8 for the proximity sensor to pass through; and the fastening nut 9 is arranged behind the slot to fix the proximity sensor of the screw nut type.

[0070] When the proximity sensor with a thread is used, as shown in Figure 5 The proximity sensor is fixed on the proximity sensor fixing support 8 through the fastening nut 9; after the proximity sensor is fixed, the corresponding target is inserted into the target clamp 5, and then the radial distance X of the target clamp 5 for fixing the target is adjusted; the principle of adjustment is that the area of the end face of the proximity sensor coinciding with the end face of the target is as large as possible, so as to ensure that the output inductance value of the proximity sensor is stable and accurate. Then, the object table 3 is moved to the starting point at the rightmost side of the displacement platform 11, the target clamp 5 is moved on the target moving guide rail 6, the axial distance Z between the end face of the target and the end face of the proximity sensor is adjusted to be zero, at this time, the target position is locked by screwing the target clamp lock 7. After the relative positions of the proximity sensor and the target are locked, the axial distance between the two is zero, the electric control device sends a zero return instruction through the RS485 communication assembly 10, the host computer sends the zero return instruction to the electric control device, and the electric control device controls the mechanical motion device to mark this position as the displacement zero point (counting zero point). Next, the servo motor 1 automatically completes the change of the expected displacement on the lead screw guide rail 2 according to the moving instruction sent by the electric control device, so as to complete the data acquisition of the inductance calculation value and the inductance standard value at different expected displacements. Due to the combination of the high-precision servo motor 1 and the lead screw guide rail 2, the position repeatability of the object table 3 is ±0.01 mm, and the moving speed of the object table 3 is automatically adjustable, and the maximum moving speed can reach 500 mm / s.

[0071] In actual use, in addition to the threaded proximity sensor as shown in Figure 5 there are also proximity sensors without threads, at this time, the fixing support should be self-adaptable to the size of the proximity sensor, therefore, in another scheme of the embodiment, as shown in Figure 4As shown, the proximity sensor fixing assembly comprises a proximity sensor fixing support 8, a slot is arranged on the proximity sensor fixing support 8 for the proximity sensor to pass through, and a clamping structure 12 for clamping the proximity sensor is arranged on the proximity sensor fixing support 8 and on both sides of the slot; the clamping structure 12 is slidably fixed on the proximity sensor fixing support 8 through a fixing block 13; the proximity sensor is fixed by fixing the clamping structure 12 through a fastening nut 9.

[0072] When the proximity sensor is a non-threaded proximity sensor, one end of the proximity sensor with the support structure is abutted against one end of the proximity sensor fixing support 8, and then the protruding part of the proximity sensor at the other end of the proximity sensor fixing support 8 is fixed in position by 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 screwed to fasten the clamping structure 12, so that the position of the non-threaded proximity sensor can be locked. The subsequent operation and the automatic acquisition of the inductance calculation value and the standard value of the threaded proximity sensor are the same as the execution steps, which will not be described here.

[0073] As shown in the figure, Figure 6 The electric control device comprises a core controller (MCU), and a display circuit, a key control circuit, a zero reset circuit, a clock circuit, a switching circuit, a filtering circuit, a storage circuit, a power supply circuit, a reset circuit, an RS232 communication interface, a USB communication interface and an RS485 communication interface which are respectively in communication connection with the core controller;

[0074] The display circuit, mainly the carrier of which is an OLED display screen, is used for displaying the radial distance between the target and the proximity sensor and the movement data of the object table 3;

[0075] The key control circuit is used for manually controlling the servo motor 1; in the embodiment, the function of the circuit can be realized by manually controlling the object table 3 on the mechanical movement device to move to a specified position under the driving of the servo motor 1 and the lead screw guide rail 2 through 10 buttons arranged, each button corresponds to a displacement distance, for example, button 1 corresponds to moving 1mm, button 2 corresponds to 2mm, and so on, and button 10 corresponds to moving 10mm. The distance corresponding to the button can be dynamically adjusted, and the host computer sends a step length adjustment instruction (parameter configuration) to the key control circuit, and the key control circuit synchronously changes the interval displacement between the buttons, for example, if the interval step length is adjusted to 2mm by sending the instruction, then button 1 corresponds to moving 1mm, button 2 corresponds to moving 3mm at this time, and so on, and button 10 corresponds to moving 19mm. The purpose of the setting of the circuit is to prevent the operation when the host computer control movement displacement is invalid and when the movement displacement is not automatically controlled;

[0076] The zero reset circuit is used for marking the measurement zero point position of the mechanical movement device when the axial distance between the end face of the proximity sensor and the end face of the target is 0;

[0077] Clock circuit, for providing normal working clock signal for core controller;

[0078] Switching circuit, mainly composed of various types of relays, for switching transmission channel between LCR tester and landing gear control unit and proximity sensor, so that the signal of corresponding proximity sensor of the stage 3 at the same position is transmitted to different data solving channels of LCR tester and landing gear control unit respectively;

[0079] Filter circuit, for filtering power supply circuit;

[0080] Storage circuit, using 2 pieces of large-capacity NANDFLASH as basic carrier, for storing data generated during the working of the electric control device and received data;

[0081] Power supply circuit, for supplying power to the whole electric control device;

[0082] Reset circuit, for resetting the electric control device; the reset can be automatic reset after program running exception timeout, and also can be manual reset by pressing the button;

[0083] RS232 communication interface, for communicating with host computer; the communication content includes receiving the instruction of automatically controlling the displacement change of mechanical movement device sent by host computer, then transmitting the instruction to MCU for analysis; receiving the instruction of adjusting the button corresponding to the interval step of the button control circuit or any other instruction sent by host computer, then transmitting the instruction to MCU for analysis; uploading the current moving displacement value of the stage 3 to the host computer; feeding back the state of whether the button of the button 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 can be transmitted to the host computer;

[0084] USB communication interface, for communicating with LCR tester; the communication content includes receiving the SCPI instruction based on VISA protocol sent by MCU, programming the LCR tester to measure the inductance value of the proximity sensor, then transmitting the measured standard inductance value to MCU, and MCU caches these data to the storage circuit for the calling of host computer at any time;

[0085] RS485 communication interface, for interfacing with RS485 communication assembly 10, transmitting zero reset instruction, transmitting the instruction of mechanical movement device action sent by MCU, controlling the operation of servo motor 1 of mechanical movement device, then driving lead screw guide rail 2 to move the stage 3 stably and accurately and automatically;

[0086] The core controller, as the center of the whole electric control device, is responsible for sending control instructions, controlling the caching and transmission of collected data, analyzing and processing communication protocols, etc., including responding to parameter configuration and control instructions of the upper computer, generating mechanical motion device control signals, analyzing and processing communication protocols, and controlling the caching and transmission of data.

[0087] In the specific implementation process, the execution flow of the electric control device is as follows: the electric control device is normally powered on, and the power indicator light and the program running indicator light are working normally. Under the above premise, first, the relative position of the proximity sensor on the mechanical motion device to the target is adjusted to 0, and the upper computer sends control instructions to the MCU through the RS232 interface, so that the MCU sends the zeroing instruction to make the mechanical motion device mark the zero point. Then, the upper computer sends instructions to the MCU to control the switching circuit to turn off the corresponding relay to close the channel for collecting proximity sensor data of the aircraft landing gear control unit, and then turn on the loop of the switching relay to connect the LCR tester and the proximity sensor. Next, the upper computer sets the interval step length between adjacent displacement points, which is updated synchronously to the step length interval between adjacent buttons of the key control circuit, and then sends the instruction to automatically collect the standard inductance value to the MCU. Next, the MCU controls the moving stage 3 on the mechanical motion device to move according to the specified displacement step length, and stops the moving stage 3 at each displacement point for 800 ms, during which the LCR tester completes the inductance value collection at this displacement point and transmits the test data to the MCU for caching through the USB interface circuit. When the moving stage 3 reaches each expected displacement point, the OLED screen of the display circuit will display the displacement distance of the moving stage 3, and the MCU will upload the displacement value of the moving stage 3 from the zero point to the upper computer through the RS232 interface circuit for display. If the key control circuit controls the slider to move, the upper computer will display the displacement distance of the moving stage 3 at the same time, and also display which key is pressed. Automatic repeated execution is performed, and when the standard inductance value collection of all expected displacement points is completed, the MCU sends an identifier to the upper computer indicating that all expected displacement points have been traversed, and the upper computer receives the identifier and sends a standard inductance value stop collection instruction. Then, after a 500 ms delay, the upper computer sends a mechanical motion device zeroing instruction to the MCU, and the moving stage 3 runs to the zero point.

[0088] Next, the host computer sends a command to the MCU to control the switching circuit to open the corresponding relay, so that the aircraft landing gear control unit can collect the inductance calculation data of the proximity sensor in one calculation data channel, and then the switching relay is switched to disconnect the LCR tester from the proximity sensor connection path. Next, the host computer sets the interval step length between adjacent displacement points, which is synchronized to the step length interval between adjacent buttons of the key control circuit, and then sends a command to the MCU to automatically collect the inductance value. Next, the MCU controls the stage 3 on the mechanical motion device to move according to the specified displacement step length. When the stage 3 moves to a displacement point, it stops running for 1000 ms, during which time the aircraft landing gear control unit can stably and reliably measure the data of the proximity sensor and cache it to the database of the host computer. When the stage 3 reaches a desired displacement point, the OLED screen of the display circuit will display the displacement distance of the stage 3, and the MCU will upload the displacement value of the stage 3 from the zero point to the host computer through the RS232 interface circuit. If the key control circuit controls the slider to move, the host computer will display the displacement distance of the standard slider and which key is pressed to automatically repeat the operation. When all the desired displacement points have been collected and cached to the database of the host computer, the MCU sends an identifier to the host computer indicating that all the desired displacement points have been traversed, and the host computer receives the identifier and sends a command to stop collecting the inductance value. Next, the host computer sends a command to the switching circuit to connect the next calculation data channel of the aircraft landing gear control unit, and repeats the above steps to collect the inductance value, which is repeated until all the inductance value data of the calculation data channels of the aircraft landing gear control unit are collected.

[0089] After the above steps are performed by the electric control device, the host computer can obtain the inductance value of each calculation data channel of the aircraft landing gear control unit at each desired displacement point and the standard inductance value measured by the LCR tester at each desired displacement point.

[0090] As shown in Figure 7 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 calculation data display module.

[0091] The mechanical device motion control and displacement data display module sends parameter configuration and control commands to the electric 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, setting the step length interval between adjacent displacement points of the stage 3, and displaying the displacement point data of the stage 3 and the usage status of the key control circuit in real time.

[0092] A data buffer module is configured to store inductance standard values and inductance calculation values, and a serial number is marked for each group of inductance calculation values corresponding to each data calculation channel of the aircraft landing gear control unit; wherein all inductance calculation values data of a single data calculation channel from the expected displacement point to the cut-off displacement point at a fixed step interval form a group; in this embodiment, the data buffer module is a MySQL database, which is an open-source relational database management system;

[0093] A correction coefficient processing module is configured to automatically call inductance calculation values and inductance standard values in the data buffer module in batches according to the marked serial numbers, perform optimal linear fitting using the least square method, and return an array describing the straight line; wherein the array describing the straight line includes correction coefficients k and b values; the obtained correction coefficients are saved according to the batch number and stage number of the aircraft landing gear control unit, so as to facilitate subsequent direct calling, avoid repeated correction of the same model and batch of products, and also facilitate data backup and archiving, and facilitate troubleshooting after a fault occurs;

[0094] A correction coefficient writing module is configured to make the mode signal line and the load signal line of the aircraft landing gear control unit in a 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 automatic correction of the calculation data deviation of the aircraft landing gear control unit; in the specific implementation process, there are two types of triggering events for writing correction coefficients into the aircraft landing gear control unit, the first type is to automatically write after a delay of 1000 ms after all correction coefficients of the calculation data channels are obtained, and the second type is to directly call the existing correction coefficients of the data buffer module to automatically write. The correction coefficients k and b values come from two sources: the first is transmitted from the correction coefficient processing module, and the second is directly called from the correction coefficients stored in the data buffer module, and the correction coefficients are automatically written;

[0095] A calculation data display module is configured to perform correction verification after the automatic correction of the calculation data deviation of the aircraft landing gear control unit, that is, by comparing the inductance values measured by the LCR tester with the inductance values of the proximity sensor collected at the specified displacement by the aircraft landing gear control unit after the automatic correction of the calculation data deviation, if the calculation data of the aircraft landing gear control unit after the automatic correction of the deviation is within the error range, the deviation correction is successful; otherwise, the deviation correction fails.

[0096] In this embodiment, the method based on the automatic correction system of the calculation data deviation of the aircraft landing gear control unit includes the following steps:

[0097] S1, configure parameters for the electronic control device through the upper computer;

[0098] S2, the mechanical movement device is controlled through the electric control device, the axial distance Z of the target end face and the end face of the proximity sensor is zero, the target and the proximity sensor are locked, and the working data of the current servo motor 1 is recorded;

[0099] S3, the target is adjusted to the expected displacement point through the servo motor 1, the output signal of the proximity sensor at different displacement points is collected through the LCR tester and is used as an inductance standard value, and the inductance calculation values calculated by each data calculation channel of the aircraft landing gear control unit at different displacement points are obtained;

[0100] S4, the inductance calculation values calculated by each data calculation channel of the aircraft landing gear control unit are linearly fitted with the inductance standard value, the correction coefficient of each data calculation channel of the aircraft landing gear control unit is obtained, the correction coefficient is written into the aircraft landing gear control unit, and the automatic correction of the calculation data deviation of the aircraft landing gear control unit is completed;

[0101] S5, the corrected verification of the calculation data of the aircraft landing gear control unit with the automatic correction of the deviation is performed, if the calculation data of the aircraft landing gear control unit with the automatic correction of the deviation is within the error range, the deviation correction is successful, otherwise, the deviation correction fails.

[0102] As described above, the parameters of the electric control device are configured and controlled by the upper computer, the servo motor 1 is controlled to work through the electric control device, the distance between the target and the proximity sensor is automatically adjusted, the inductance standard value collected by the LCR tester is automatically uploaded to the upper computer through the electric control device, the inductance calculation values calculated by each data calculation channel of the aircraft landing gear control unit are automatically linearly fitted with the inductance standard value in the upper computer, the 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 the correction of the calculation data deviation of the aircraft landing gear control unit can be greatly improved.

Claims

1. An automatic correction system for deviation of calculated data of an aircraft landing gear control unit, characterized in that: Including mechanical motion device, electronic control device and host computer; A mechanical motion device for fixing the proximity sensor and adjusting the distance between the target and the proximity sensor via a servo motor (1); An 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; The host computer includes a correction coefficient processing module, a data cache module, a correction coefficient writing module and a solution data display module; among which: A data cache module is used to store standard inductance values ​​and calculated inductance values, and to serialize a set of calculated inductance values ​​corresponding to each data calculation channel of the aircraft landing gear control unit. A set of calculated inductance values ​​for a single data calculation channel, starting from a desired displacement point and followed by a fixed step length to a cutoff displacement point, is considered a 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 an array describing this line; the array describing this line includes the correction coefficient; 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.

2. The automatic correction system for aircraft landing gear control unit calculated data deviation according to claim 1, characterized in that: 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 via an RS485 communication component (10); The servo motor (1) is located at one end of the displacement platform (11); a proximity sensor fixing assembly is provided at the other end of the displacement platform (11); A target moving platform (4) is provided on the loading platform (3); a target moving guide rail (6) is provided on the target moving guide rail (6); a target fixture (5) is slidably provided on the target moving guide rail (6); and a target fixture locker (7) for fixing the position of the target fixture (5) is provided on the target fixture (5).

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

4. The automatic correction system for aircraft landing gear control unit calculated data deviation 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 provided on the proximity sensor fixing bracket (8), and a clamping structure (12) for clamping the proximity sensor is provided on both sides of the groove on the proximity sensor fixing bracket (8); the clamping structure (12) is slidably fixed to 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 aircraft landing gear control unit calculated data deviation according to claim 2, characterized in that: The electronic control device includes a core controller, and a display circuit, a key control circuit, a zero return 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; a display circuit for displaying the radial distance between the target and the proximity sensor, and movement data of the stage (3); A key control circuit for manually controlling the servo motor (1); a zero return circuit, used for marking 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 zero; The clock circuit is used to provide a clock signal for the core controller to operate 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; 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 to the 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 the mechanical motion device; parse and process communication protocols; and control the caching and transmission of data.

6. The automatic correction system for aircraft landing gear control unit calculated data deviation according to claim 5, characterized in that: The host computer includes a mechanical device motion control and displacement 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 distance 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.

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. Configure the parameters 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 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; S4. Performing linear fitting on the inductance solution values ​​obtained by solving each data solution channel of the aircraft landing gear control unit and the inductance standard value, obtaining correction coefficients for each data solution channel of the aircraft landing gear control unit, writing the correction coefficients into the aircraft landing gear control unit, and completing automatic correction of deviations in the solution data of the aircraft landing gear control unit.

8. The method according to claim 7, characterized in that Step S4 is followed by the following steps: S5. Correction and verification are performed on the aircraft landing gear control unit solution data that has undergone automatic deviation correction. If the aircraft landing gear control unit solution data 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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