A control system, method and medium for aircraft landing gear locking components

Abstract

The present application relates to the field of aircraft landing gear safety technology, and in particular to a control system, method, and medium for an aircraft landing gear locking component. The aircraft landing gear locking component includes a safety pin and two bushings, and the system includes a control device for the aircraft landing gear locking component and a detection device for the aircraft landing gear locking component; the control device for the aircraft landing gear locking component stores the safety pin and the bushing, wherein a first RFID chip is provided in the safety pin, wherein the first RFID chip is an embedded RFID chip; the detection device for the aircraft landing gear locking component determines whether the locking component has been safely stored by detecting whether the control device for the aircraft landing gear locking component has the first RFID chip. The present application realizes the monitoring and control of the storage status of the aircraft landing gear locking component to ensure the safe storage of the aircraft landing gear locking component.

Description

Technical Field

[0001] The present application relates to the field of aircraft landing gear safety technology, and in particular to a control system, method, and medium for aircraft landing gear locking components. Background Art

[0002] Aircraft landing gear locking components, including safety pins and bushings, are a major pain point in the industry. These locking components are designed to prevent the landing gear from accidentally retracting while the aircraft is on the ground. Before takeoff, all locking components must be removed. Otherwise, the landing gear will not retract after takeoff, potentially forcing the aircraft to return to its base. However, existing technologies for controlling landing gear locking components rely heavily on manual labor, which can lead to serious issues such as safety pins not being removed. Summary of the Invention

[0003] Based on the above technical problems, the present application aims to provide a control system, method and medium for aircraft landing gear locking components to achieve safe control of aircraft landing gear locking components.

[0004] In a first aspect, the present application provides a control system for an aircraft landing gear locking component, wherein the aircraft landing gear locking component includes a safety pin and two bushings. The system includes a control device for the aircraft landing gear locking component and a detection device for the aircraft landing gear locking component.

[0005] A control device for a locking component of an aircraft landing gear stores the safety pin and the bushing, wherein a first RFID chip is disposed within the safety pin, wherein the first RFID chip is an embedded RFID chip;

[0006] The detection device of the aircraft landing gear locking component determines whether the locking component has been safely stored by detecting whether the control device of the aircraft landing gear locking component has the first RFID chip.

[0007] In some embodiments of the present application, the control device of the aircraft landing gear locking component includes a control box and a box cover, and the control box is provided with two limited bushing mounting holes and a limited safety pin insertion hole.

[0008] In some embodiments of the present application, a rotating mechanism is provided on the top wall of the safety pin hole, a lock hole perpendicular to the safety pin hole is provided in the rotating mechanism, a lock core is installed in the lock hole, the head of the lock core is connected to a spring, and the tail of the lock core extends into the safety pin hole when the spring is relaxed.

[0009] In some embodiments of the present application, a connecting rod and a hook connected to the connecting rod are further provided in the rotating mechanism;

[0010] When the safety pin is inserted into the safety pin insertion hole, the safety pin completely pushes the tail of the lock core into the rotating mechanism, and the spring is compressed to drive the hook to rotate, so that the tongue in the box cover engages with the hook.

[0011] In some embodiments of the present application, a second RFID chip is further placed in the control box, wherein the second RFID chip is a split RFID chip, and the second RFID chip includes a chip body and an antenna;

[0012] The spring is compressed to drive the chip body to connect with the antenna, so that the second RFID chip can be detected by the detection device of the aircraft landing gear locking component.

[0013] In some embodiments of the present application, the detection device of the aircraft landing gear locking component performs the following steps when detecting the first RFID chip or the second RFID chip:

[0014] sending a scanning signal to a control device of the aircraft landing gear locking component, and receiving feedback information from a detection device of the aircraft landing gear locking component in response to the scanning signal;

[0015] The feedback information is read, and whether the first RFID chip or the second RFID chip is in the control device of the aircraft landing gear locking component is determined based on the identification data in the feedback information.

[0016] In some embodiments of the present application, the identification data includes an aircraft ID, a locked component ID, a locked component name, and / or aircraft location data.

[0017] In some embodiments of the present application, before the safety pin is inserted into the safety pin insertion hole, the two bushings are respectively inserted into the two limited bushing mounting holes.

[0018] A second aspect of the present application provides a method for controlling a locking component of an aircraft landing gear, wherein the locking component comprises a safety pin and two bushings; the method comprises:

[0019] An embedded RFID chip is provided in the safety pin;

[0020] Inserting the two bushings into a target control box, and inserting the safety pin provided with the embedded RFID chip into the target control box;

[0021] A split RFID chip is provided in the target control box, wherein the split RFID chip includes a chip body and an antenna;

[0022] When the safety pin provided with the embedded RFID chip is inserted into the target control box, the preset box cover is closed over the target control box, and the chip body is connected to the antenna;

[0023] The embedded RFID chip and / or the split RFID chip are detected.

[0024] A third aspect of the present application provides a computer-readable storage medium having a computer program stored thereon. When the computer program is executed by a processor, the method for controlling the aircraft landing gear locking component described in the embodiments of the present application is implemented.

[0025] The technical solutions provided in the embodiments of this application have at least the following technical effects or advantages:

[0026] The control system of the aircraft landing gear locking component in each embodiment of the present application, the aircraft landing gear locking component includes a safety pin and two bushings, the system includes a control device of the aircraft landing gear locking component and a detection device of the aircraft landing gear locking component, the control device of the aircraft landing gear locking component stores the safety pin and the bushing, wherein a first RFID chip is provided in the safety pin, wherein the first RFID chip is an embedded RFID chip, the detection device of the aircraft landing gear locking component determines whether the locking component has been safely stored by detecting whether the control device of the aircraft landing gear locking component has the first RFID chip, after all the aircraft landing gear locking components are placed in the control device, the inspection device performs detection and realizes monitoring and control of the storage status of the aircraft landing gear locking component by detecting the first RFID chip, so as to ensure the safe storage of the aircraft landing gear locking component.

[0027] Not only that, the control device of the aircraft landing gear locking component also places a second RFID chip, which is a split RFID chip. When the control box and the box cover in the control device are closed, the chip body and the antenna in the second RFID chip are connected, so that the second RFID chip can be detected by the detection device of the aircraft landing gear locking component, thereby realizing double verification and double insurance of the first RFID chip and the second RFID chip, improving the safe monitoring and verification of the status of the aircraft landing gear locking component, and realizing precise and safe management and control of the aircraft landing gear locking component.

[0028] It should be understood that the foregoing general description and the following detailed description are exemplary and explanatory only and are not restrictive of the present application. BRIEF DESCRIPTION OF THE DRAWINGS

[0029] Various other advantages and benefits will become apparent to those skilled in the art upon reading the detailed description of the preferred embodiment below. The accompanying drawings are for illustration purposes only and are not to be considered as limiting the present application. The same reference symbols are used throughout the drawings to represent the same components. In the drawings:

[0030] Figure 1 is a schematic diagram of a control device for a locking component of an aircraft landing gear in an exemplary embodiment of the present application;

[0031] Figure 2 This is a schematic diagram showing the state of a safety pin socket of a control device for an aircraft landing gear locking component when a safety pin is not inserted into a control box in an exemplary embodiment of the present application;

[0032] Figure 3 This is a schematic diagram showing the state of a safety pin socket of a control device for an aircraft landing gear locking component when a safety pin is inserted into a control box in an exemplary embodiment of the present application;

[0033] Figure 4 This is a schematic diagram of the steps of a method for controlling a locking component of an aircraft landing gear in an exemplary embodiment of the present application;

[0034] Figure 5 It is a structural diagram of an electronic device provided by an exemplary embodiment of the present application.

[0035] It should be understood that the foregoing general description and the following detailed description are exemplary and explanatory only and are not restrictive of the present application. DETAILED DESCRIPTION

[0036] The present application will be further described in detail below with reference to the accompanying drawings and embodiments. It should be understood that the embodiments described herein are only used to explain the relevant invention and are not intended to limit the invention. It should also be noted that for ease of description, only the parts related to the relevant invention are shown in the accompanying drawings.

[0037] However, the existing technology for controlling aircraft landing gear locking components still relies too much on manual means, which can lead to the serious problem of the safety pin not being removed. To this end, the present application provides a control system for an aircraft landing gear locking component. The aircraft landing gear locking component includes a safety pin and two bushings. The system includes a control device for the aircraft landing gear locking component and a detection device for the aircraft landing gear locking component. The control device for the aircraft landing gear locking component stores the safety pin and bushing, wherein the safety pin is provided with a first RFID (Radio-Frequency Identification) chip, wherein the first RFID chip is an embedded RFID chip. The detection device for the aircraft landing gear locking component determines whether the locking component has been safely stored by detecting whether the control device of the aircraft landing gear locking component has the first RFID chip. The detection device for the aircraft landing gear locking component detects whether the control device of the aircraft landing gear locking component has the first RFID chip to determine whether the locking component has been safely stored, thereby achieving both accurate and safe control of the aircraft landing gear locking component. The following is a detailed description of several embodiments with reference to the accompanying drawings.

[0038] Example 1

[0039] This embodiment provides a control system for an aircraft landing gear locking component. The aircraft landing gear locking component includes a safety pin and two bushings. The system includes a control device for the aircraft landing gear locking component and a detection device for the aircraft landing gear locking component. The control device for the aircraft landing gear locking component stores the safety pin and bushing. The safety pin is provided with a first RFID chip. The first RFID chip is an embedded RFID chip and is not shown in the accompanying drawings because it is embedded in the safety pin. The detection device for the aircraft landing gear locking component determines whether the locking component is securely stored by detecting whether the control device for the aircraft landing gear locking component contains the first RFID chip. In this way, this embodiment monitors and controls the storage status of the aircraft landing gear locking component to ensure its secure storage.

[0040] In a specific implementation, refer to Figure 1 , Figure 1 FIG. 1 is a schematic diagram of a control device for an aircraft landing gear locking component in an exemplary embodiment of the present application. Figure 1As shown, the control box includes a front view and a side view. The control box and its cover are two parts of the control device for the aircraft landing gear locking component. The control box contains two limited bushing mounting holes, which are actually used as the nose landing gear safety pin holes, and one limited safety pin hole, which is actually used as the main landing gear safety bushing mounting hole. The control box front view also has limited holes. These holes can be used to fix the safety pin insertion hole and bushing mounting hole with parts such as locating pins and bolts to ensure that the two bushings and safety pins are securely inserted into the corresponding holes.

[0041] In one possible implementation, refer to Figure 2 , Figure 2 FIG. 1 is a schematic diagram of a safety pin socket of a control device for an aircraft landing gear locking component when a safety pin is not inserted into a control box in an exemplary embodiment of the present application. Figure 2 As shown, a rotating mechanism is provided on the top wall of the safety pin insertion hole. A lock hole perpendicular to the safety pin insertion hole is provided in the rotating mechanism. A lock core is installed in the lock hole. The head of the lock core is connected to a spring. The tail of the lock core extends into the safety pin insertion hole when the spring is relaxed. A connecting rod and a hook connecting the connecting rod are also provided in the rotating mechanism; refer to Figure 3 and Figure 1 In the side view of the control box, when the safety pin is inserted into the safety pin socket, it pushes the rear end of the lock cylinder fully into the rotating mechanism. The spring is compressed, causing the hook to rotate, allowing it to be rotated out of the control box, allowing the tab in the box cover to engage with the hook. Furthermore, the box cannot be closed without the safety pin. When the box is not closed, a prominent red mark serves as a reminder to maintenance and crew members.

[0042] In the specific implementation, insert the two bushings into the two limited bushing mounting holes of the control box respectively, and then insert the safety pin into the safety pin socket, such as Figure 3 As shown, the safety pin completely pushes the tail of the lock cylinder into the rotating mechanism, and the spring is compressed to drive the hook to rotate, so that the hook is rotated out or exposed outside the control box, so that the tongue in the box cover engages with the hook.

[0043] It will be understood that in the above implementation, the rotating mechanism allows movement of the lock cylinder and controls the lock state. The lock cylinder locks and unlocks the safety pin receptacle while providing a restoring force via a spring. The rotating mechanism also includes a connecting rod and a hook connecting the connecting rod. These components, when the safety pin is inserted or removed, cooperate with the rotating mechanism to rotate the hook out or expose it outside the control box. However, the most important prerequisite is that the safety pin is fully inserted into the safety pin receptacle to facilitate the full entry of the lock cylinder into the control box and the subsequent closing of the control box and lid. When the safety pin is inserted into the safety pin receptacle, it pushes the rear end of the lock cylinder fully into the rotating mechanism, triggering the compression of the spring and causing the hook to rotate. This causes the hook to rotate out or expose itself outside the control box, allowing the latch in the lid to engage with the hook, thus ensuring the secure state of the aircraft landing gear locking components.

[0044] In another possible implementation, the detection device of the aircraft landing gear locking component performs the following steps when detecting the first RFID chip:

[0045] The first step is to send a scanning signal to a control device of a locking component of an aircraft landing gear, and receive feedback information of a detection device of the locking component of the aircraft landing gear in response to the scanning signal.

[0046] Specifically, this step involves communication between the detection device and the control device, which can be carried out through wireless communication. The detection device sends a scanning signal to the control device of the aircraft landing gear locking component. This signal is a radio frequency signal. When the detection device sends a scanning signal, the first RFID chip in the control device can be activated and send the information stored in the chip to the detection device. The embedded RFID chip includes an antenna associated with it, which can realize radio frequency communication with external devices such as tablet computers. The antenna allows the RFID chip to receive radio frequency signals and send response signals, thereby realizing two-way communication. The first RFID chip in the control device will be activated, which is achieved by receiving the radio frequency scanning signal sent from the detection device. After activation, the first RFID chip can use its internal antenna to send the information stored in the chip to the detection device, thereby realizing information transmission.

[0047] Furthermore, the control device sends feedback information to the detection device. This feedback information may include the received strength of the scanning signal and decoded data, etc., for subsequent analysis and judgment. The feedback information may also include identification data, such as the aircraft ID, the locked component ID, the locked component name, and / or the aircraft's location data.

[0048] In practice, the release officer uses a tablet computer to complete the routine inspection steps listed on the electronic work card and then uses the test program on the tablet computer to scan the control device. This process involves sending a scanning signal to the control device of the aircraft's landing gear locking components. Upon receiving the signal, the control device's detection device responds to the scan signal and sends feedback to the control device. By scanning the control device, activating the RFID chip, and obtaining feedback, the status of the aircraft's landing gear locking components is verified to ensure compliance with safety and operational requirements.

[0049] The second step is to read the feedback information and determine whether the first RFID chip is in the control device of the aircraft landing gear locking component based on the identification data in the feedback information.

[0050] It can be understood that this step monitors and determines the status of the safety pin of the aircraft landing gear locking component by detecting the first RFID chip and analyzing the feedback information. Specifically, the detection device reads and analyzes the feedback information from the control device. By analyzing the identification data in the feedback information, it can determine whether the first RFID chip is detected. Because the first RFID chip is embedded in the safety pin, when the first RFID chip is detected, it is determined that the safety pin containing the chip has been removed from the aircraft landing gear and safely placed in the control device of the aircraft landing gear locking component. As can be seen, this application improves the controllability and safety of the operation and realizes the safe and precise control of the aircraft landing gear locking component.

[0051] It should be understood that the foregoing general description and the following detailed description are exemplary and explanatory only and are not restrictive of the present application.

[0052] Example 2

[0053] This embodiment provides a control system for an aircraft landing gear locking component. The aircraft landing gear locking component includes a safety pin and two bushings. The system includes a control device for the aircraft landing gear locking component and a detection device for the aircraft landing gear locking component. The control device for the aircraft landing gear locking component stores the safety pin and the bushing. The safety pin is provided with a first RFID chip, wherein the first RFID chip is an embedded RFID chip. Figure 2 and Figure 3 There is also a second RFID chip in the control device, wherein the second RFID chip is a split RFID chip. The detection device of the aircraft landing gear locking component realizes double verification by detecting whether the control device of the aircraft landing gear locking component has the first RFID chip and / or the second RFID chip, thereby determining whether the locking component has been safely stored.

[0054] like Figure 2As shown, the second RFID chip placed in the control box is a split RFID chip, including a chip body and an antenna. The antenna corresponds to Figure 2 The blue component next to the card hook, the chip body corresponds to Figure 2 One side of the lock core in the rotating mechanism. Figure 3 As shown, the spring is compressed and drives the lock core into the rotating mechanism, which will cause the chip body to move and merge with the antenna. The schematic diagram after the chip body and antenna are combined can also be referred to Figure 1 The side view of the control box in the figure shows that the chip body and the antenna are connected so that the second RFID chip can be detected by the detection device of the aircraft landing gear locking component, thereby improving the safety monitoring and verification of the status of the aircraft landing gear locking component.

[0055] In another possible implementation, the detection device of the aircraft landing gear locking component performs the following steps when detecting the second RFID chip:

[0056] The first step is to send a scanning signal to a control device of a locking component of an aircraft landing gear, and receive feedback information of a detection device of the locking component of the aircraft landing gear in response to the scanning signal.

[0057] The second step is to read the feedback information and determine whether the second RFID chip is in the control device of the aircraft landing gear locking component based on the identification data in the feedback information.

[0058] After completing the routine inspection steps on the electronic work card using a tablet, the release officer uses the tablet's inspection program to scan the control device. This process involves sending a scanning signal, a radio frequency signal, to the control device for the aircraft's landing gear locking components. Upon receiving the signal, the control device's inspection device responds and sends feedback to the control device. By scanning the control device, activating the second RFID chip, and obtaining feedback, the status of the aircraft's landing gear locking components is verified.

[0059] However, after the two bushings and a safety pin are fully inserted into the control box in the control device, when the control device is used to detect the RFID chip, two chips can be detected, namely the first RFID chip built into the safety pin and the second RFID chip placed in the control box. In this way, when one chip is abnormal and cannot be identified due to extreme special circumstances, at least one chip can be detected to ensure that the aircraft landing gear locking component has been safely removed from the aircraft landing gear and placed in the control device of the aircraft landing gear locking component, which meets the safety and operational requirements and realizes both safe and precise management and control.

[0060] It should be understood that the foregoing general description and the following detailed description are exemplary and explanatory only and are not restrictive of the present application.

[0061] Example 3

[0062] This embodiment provides a method for controlling a locking component of an aircraft landing gear, wherein the locking component of the aircraft landing gear includes a safety pin and two bushings; Figure 4 As shown, the method includes steps S1 to S5.

[0063] S1. An embedded RFID chip is provided in the safety pin.

[0064] S2. Insert the two bushings into the target control box, and insert the safety pin provided with the embedded RFID chip into the target control box.

[0065] S3. Install a split-type RFID chip in the target control box, wherein the split-type RFID chip includes a chip body and an antenna.

[0066] S4. When the safety pin provided with the embedded RFID chip is inserted into the target control box, the preset box cover is closed over the target control box, and the chip body and the antenna are connected.

[0067] S5. Detect the embedded RFID chip and / or the split RFID chip.

[0068] The control method of the aircraft landing gear locking component realizes double verification and double insurance of the first RFID chip and the second RFID chip, improves the safety monitoring and verification of the status of the aircraft landing gear locking component, and realizes the precise control and safe control of the aircraft landing gear locking component.

[0069] It should be understood that the foregoing general description and the following detailed description are exemplary and explanatory only and are not restrictive of the present application.

[0070] Example 4

[0071] This embodiment provides an electronic device. Figure 5 ,like Figure 5 As shown, the electronic device 2 includes: a processor 200, a memory 201, a bus 202 and a communication interface 203, wherein the processor 200, the communication interface 203 and the memory 201 are connected via the bus 202; the memory 201 stores a computer program that can be run on the processor 200, and when the processor 200 runs the computer program, it executes any one of the methods for controlling the aircraft landing gear locking components in the embodiments of the present application.

[0072] The memory 201 may include high-speed random access memory (RAM) and may also include non-volatile memory, such as at least one disk storage. The system network element communicates with at least one other network element via at least one communication interface 203 (which may be wired or wireless), and may utilize the Internet, a wide area network, a local area network, a metropolitan area network, or the like.

[0073] Bus 202 may be an ISA bus, a PCI bus, or an EISA bus. The bus may be divided into an address bus, a data bus, a control bus, and the like. Memory 201 is used to store programs, and processor 200 executes the programs upon receiving execution instructions. The aircraft landing gear locking component control system disclosed in any of the aforementioned embodiments of the present application may be applied to or implemented by processor 200.

[0074] The processor 200 may be an integrated circuit chip with signal processing capabilities. During implementation, each step of the above method can be completed by hardware integrated logic circuits in the processor 200 or by software instructions. The above processor 200 may be a general-purpose processor, including a central processing unit (CPU), a network processor (NP), etc.; it may also be a digital signal processor (DSP), an application-specific integrated circuit (ASIC), an off-the-shelf field programmable gate array (FPGA), or other programmable logic devices, discrete gate or transistor logic devices, or discrete hardware components. It can implement or execute the various methods, steps, and logic block diagrams disclosed in the embodiments of this application. The general-purpose processor may be a microprocessor or any conventional processor. The steps of the method disclosed in conjunction with the embodiments of this application can be directly implemented and executed by a hardware decoding processor, or by a combination of hardware and software modules in the decoding processor. The software module can be located in a storage medium mature in the art, such as random access memory, flash memory, read-only memory, programmable read-only memory, electrically erasable programmable memory, registers, etc. The storage medium is located in the memory 201, and the processor 200 reads the information in the memory 201 and completes the steps of the control method of the aircraft landing gear locking component in combination with its hardware.

[0075] Example 5

[0076] This embodiment provides a computer-readable storage medium corresponding to the aircraft landing gear locking component control method provided in Example 3, on which a computer program is stored. When executed by a processor, the computer program executes the aircraft landing gear locking component control system provided in any of the aforementioned embodiments. Furthermore, examples of the computer-readable storage medium may include, but are not limited to, phase change memory (PRAM), static random access memory (SRAM), dynamic random access memory (DRAM), other types of random access memory (RAM), read-only memory (ROM), electrically erasable programmable read-only memory (EEPROM), flash memory, or other optical or magnetic storage media, and are not further detailed here.

[0077] In addition, this embodiment also provides a computer program product, including a computer program, which, when executed by a processor, implements the control method of the aircraft landing gear locking component described in the aforementioned embodiments.

[0078] Those skilled in the art will appreciate that the various component embodiments of the present application can be implemented in hardware, or in software modules running on one or more processors, or in a combination thereof. Those skilled in the art will appreciate that in practice, a microprocessor or digital signal processor (DSP) can be used to implement some or all of the functions of some or all of the components of the apparatus for creating a virtual machine according to an embodiment of the present application.

[0079] The above is only a preferred specific implementation of the present application, but the scope of protection of the present application is not limited to this. The aircraft landing gear locking component is not limited to one safety pin and two bushings. Combinations of other quantities and forms are also within the scope of protection of the present application. As long as the solution is consistent with the technical principles or technical ideas of the present application, it should be covered by the scope of protection of the present application.

Claims

1. A control system for aircraft landing gear locking components, characterized in that: The aircraft landing gear locking component includes a safety pin and two bushings, and the system includes a control device for the aircraft landing gear locking component and a detection device for the aircraft landing gear locking component; A control device for a locking component of an aircraft landing gear stores the safety pin and the bushing, wherein a first RFID chip is disposed within the safety pin, wherein the first RFID chip is an embedded RFID chip; The detection device of the aircraft landing gear locking component determines whether the locking component has been safely stored by detecting whether the control device of the aircraft landing gear locking component has the first RFID chip; The control device for the aircraft landing gear locking component includes a control box and a box cover, wherein the control box has two limited bushing mounting holes and a limited safety pin insertion hole; A rotating mechanism is provided on the top wall of the safety pin insertion hole, a connecting rod and a hook connected to the connecting rod are further provided in the rotating mechanism, a lock hole perpendicular to the safety pin insertion hole is provided in the rotating mechanism, a lock core is installed in the lock hole, and a spring is connected to the head of the lock core; A second RFID chip is also placed in the control box, wherein the second RFID chip is a split RFID chip, and the second RFID chip includes a chip body and an antenna; When the safety pin is inserted into the safety pin socket, the safety pin completely pushes the tail of the lock core into the rotating mechanism. The spring is compressed to drive the lock core into the rotating mechanism, causing the chip body to move and combine with the antenna, so that the second RFID chip can be detected by the detection device of the aircraft landing gear locking component.

2. The aircraft landing gear locking component control system according to claim 1, characterized in that: The tail of the lock core extends into the safety pin insertion hole when the spring is relaxed.

3. The control system for aircraft landing gear locking components according to claim 2, characterized in that: When the safety pin is inserted into the safety pin insertion hole, the safety pin completely pushes the tail of the lock core into the rotating mechanism, and the spring is compressed to drive the hook to rotate, so that the tongue in the box cover engages with the hook.

4. The aircraft landing gear locking component control system according to claim 1, characterized in that: The detection device of the aircraft landing gear locking component performs the following steps when detecting the first RFID chip or the second RFID chip: sending a scanning signal to a control device of the aircraft landing gear locking component, and receiving feedback information from a detection device of the aircraft landing gear locking component in response to the scanning signal; The feedback information is read, and whether the first RFID chip or the second RFID chip is in the control device of the aircraft landing gear locking component is determined based on the identification data in the feedback information.

5. The aircraft landing gear locking component control system according to claim 4, characterized in that: The identification data includes an aircraft ID, a locked component ID, a locked component name and / or aircraft location data.

6. The aircraft landing gear locking component control system according to claim 3, characterized in that: Before the safety pin is inserted into the safety pin insertion hole, the two bushings are respectively inserted into the two limited bushing mounting holes.

7. A method for controlling a locking component of an aircraft landing gear, characterized in that: An aircraft landing gear locking component includes a safety pin and two bushings; the method includes: An embedded RFID chip is provided in the safety pin; Inserting the two bushings into a target control box, and inserting the safety pin provided with the embedded RFID chip into the target control box; A split RFID chip is provided in the target control box, wherein the split RFID chip includes a chip body and an antenna; When the safety pin with the embedded RFID chip is inserted into the target control box, the preset box cover is closed over the target control box; wherein, the target control box is provided with two limited bushing mounting holes and a limited safety pin insertion hole, a rotating mechanism is provided on the top wall of the safety pin insertion hole, a connecting rod and a hook connected to the connecting rod are further provided in the rotating mechanism, a lock hole perpendicular to the safety pin insertion hole is further provided in the rotating mechanism, a lock core is installed in the lock hole, and a spring is connected to the head of the lock core; Detect the embedded RFID chip and / or split RFID chip; wherein, when the safety pin is inserted into the safety pin socket, the safety pin completely pushes the tail of the lock core into the rotating mechanism, and the spring is compressed to drive the lock core into the rotating mechanism, causing the chip body to move and merge with the antenna.

8. A computer-readable storage medium having a computer program stored thereon, characterized in that: When the computer program is executed by a processor, the method for controlling the aircraft landing gear locking component as claimed in claim 7 is implemented.

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