Aircraft ground power cord leakage alert device, system and method

Abstract

The application relates to an aircraft grounding wire electric leakage alarm device, system and method, the device comprising: a device main body sleeved on an aircraft grounding wire; an electric leakage alarm circuit is arranged in the device main body; the electric leakage alarm circuit is used for detecting electric leakage of the aircraft grounding wire through magnetic induction and giving an electric leakage prompt. The application can improve the safety of an aircraft body by highly sensitively detecting the electric leakage current of the aircraft grounding wire.

Description

Technical Field

[0001] This application belongs to the field of aviation safety and electrical protection technology, and specifically relates to an aircraft grounding wire leakage alarm device, system and method. Background Technology

[0002] Current aircraft grounding systems primarily use copper-core wires to connect the aircraft grounding socket to the grounding stake. These systems only provide electrostatic discharge and cannot detect or alert to leakage current from the ground power supply to the aircraft via the grounding wire, posing a significant safety hazard. In actual use, the ground power supply, aircraft structure, and grounding wire form a closed-loop circuit. If a fault occurs in the ground power supply or aircraft circuitry, causing AC or DC leakage, the current will be conducted to the ground through the aircraft structure and grounding wire. If personnel come into contact with the aircraft during this process, they are highly susceptible to electric shock. However, the currently used grounding wire structure is simple and lacks leakage monitoring and alarm modules, making it impossible to determine whether leakage has occurred and its severity. This risk is particularly pronounced in unattended environments such as field sites.

[0003] Therefore, there is an urgent need for a grounding device with leakage detection and alarm functions to improve the safety and reliability of ground protection operations. Summary of the Invention

[0004] In order to overcome the shortcomings of the prior art, the purpose of this application is to provide an aircraft grounding wire leakage alarm device, system and method. This application aims to improve the safety of the aircraft body by performing highly sensitive detection of the leakage current of the aircraft grounding wire.

[0005] To achieve the above objectives, this application provides the following technical solution: An aircraft grounding wire leakage alarm device includes: a device body, which is sleeved on the aircraft grounding wire; a leakage alarm circuit is provided inside the device body; the leakage alarm circuit is used to detect leakage in the aircraft grounding wire through magnetic induction and provide leakage warning.

[0006] Optionally, the leakage current alarm circuit includes a power supply module, an electromagnetic induction module, a delay alarm module, and a self-test module. The power supply module supplies power to the electromagnetic induction module, the delay alarm module, and the self-test module. The electromagnetic induction module senses leakage current anomalies in the aircraft grounding wire. The delay alarm module issues an alarm after a preset delay following the detection of a leakage current anomaly by the electromagnetic induction module. The self-test module performs a self-test on the status of the electromagnetic induction module and the delay alarm module.

[0007] Optionally, the electromagnetic induction module includes an induction coil, a capacitor, an optocoupler, an audible and visual alarm light, a first matching resistor, and a cut-off switch. The induction coil is wound around the aircraft grounding wire. A first end of the induction coil is connected to a first end of the cut-off switch, and a second end of the induction coil is connected to a first grounding terminal. The second end of the cut-off switch and the first end of the first matching resistor are connected to form a first node. The second end of the first matching resistor is connected to the input terminal of the optocoupler. A first end of the capacitor is connected to the first node, and a second end of the capacitor is connected to the first grounding terminal. A first end of the audible and visual alarm light is connected to the first node, and a second end of the audible and visual alarm light is connected to the first grounding terminal. A first output terminal of the optocoupler is connected to the first grounding terminal. A second output terminal of the optocoupler is connected to the input terminal of the delayed alarm module. A third output terminal of the optocoupler is connected to a second grounding terminal.

[0008] Optionally, the delay alarm module includes: a reset switch, a delay disconnect relay, an electric counter, a second matching resistor, and a delay audible and visual alarm light. The first terminal of the delay disconnect relay serves as the input terminal of the delay alarm module; the reset switch is connected to the second terminal of the delay disconnect relay; the first and second normally open contacts of the delay disconnect relay are connected in series with the second matching resistor to form a self-locking circuit; the third and fourth normally open contacts of the delay disconnect relay are connected to the first terminal of the delay audible and visual alarm light, and the second terminal of the delay audible and visual alarm light is connected to the second ground terminal; the fifth normally open contact of the delay disconnect relay is connected to the first input terminal of the self-test module, and the sixth normally open contact of the delay disconnect relay is connected to the first terminal of the electric counter and the second input terminal of the self-test module; the second terminal of the electric counter is connected to the second ground terminal. Optionally, the self-test module includes: a lamp test switch, a first diode, and a second diode, wherein the anode of the second diode serves as the first input terminal of the self-test module; the cathode of the second diode serves as the second input terminal of the self-test module; the anode of the first diode is connected to the anode of the second diode, and the cathode of the first diode is connected to the first node; the lamp test switch includes a first normally open contact and a second normally open contact, as well as a first normally closed contact and a second normally closed contact, the first normally open contact and the first normally closed contact are connected to the power module, the second normally open contact is connected to the anode of the first diode and the second diode, and the second normally closed contact is connected to the first terminal of the lamp test switch.

[0009] Optionally, the lamp inspection switch is a double-pole double-throw switch.

[0010] Optionally, the power module includes a solar charger and a rechargeable dry cell battery, with the solar charger electrically connected to the rechargeable dry cell battery.

[0011] This application also provides an aircraft grounding wire leakage alarm system, the system including the device as described in any of the preceding claims.

[0012] This application also provides a method for alarming leakage current in an aircraft grounding wire. The method includes: performing magnetic induction detection on the aircraft grounding wire using an electromagnetic induction module; when leakage current exists in the aircraft grounding wire, the electromagnetic induction module generates a magnetic induction voltage signal and issues a first alarm; the electromagnetic induction module isolates the magnetic induction voltage signal and transmits it to a delayed alarm module; the delayed alarm module is triggered to conduct and issues a second alarm.

[0013] Optionally, the method further includes performing a self-test on the electromagnetic induction module and the delay alarm module.

[0014] The beneficial effects of this application are as follows: This application utilizes the principle of magnetic induction to achieve sensitive detection of leakage current in the grounding wire, and combines rectification filtering and audible and visual devices to achieve real-time alarms, significantly improving the safety of ground operations. Simultaneously, an optocoupler is used to isolate and amplify the current signal, along with a self-locking circuit to achieve delayed alarm signal retention, ensuring that even if the leakage phenomenon disappears momentarily, it is still recorded and alerted, enhancing alarm reliability. The electric counter in the delay module has a power-off memory function, accurately recording the number of leakage occurrences for easy subsequent maintenance and troubleshooting. Furthermore, the device is powered by solar charging and a rechargeable battery, featuring low power consumption and long battery life, adapting to unattended field environments. Its compact and low-cost overall structure facilitates installation and widespread adoption, making it suitable for various operating scenarios in aircraft hangars and field environments, demonstrating significant novelty, creativity, and practical value. Attached Figure Description

[0015] Figure 1 This is a schematic diagram of the overall structure of an aircraft grounding wire leakage alarm device provided in one embodiment of this application; Figure 2 This is a schematic diagram of the internal circuit structure of an aircraft grounding wire leakage alarm device provided in another embodiment of this application. Detailed Implementation

[0016] The technical solutions of the embodiments of this application will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only a part of the embodiments of this application, and not all of the embodiments. Based on the embodiments of this application, all other embodiments obtained by those of ordinary skill in the art without creative effort are within the scope of protection of this application.

[0017] It should be noted that all directional indicators (such as up, down, left, right, front, back, etc.) in the embodiments of this application are only used to explain the relative positional relationship and movement of each component in a certain specific posture (as shown in the figure). If the specific posture changes, the directional indicator will also change accordingly.

[0018] In this application, unless otherwise expressly specified and limited, the terms "connection," "fixed," etc., should be interpreted broadly. For example, "fixed" can mean a fixed connection, a detachable connection, or an integral part; it can mean a mechanical connection or an electrical connection; it can mean a direct connection or an indirect connection through an intermediate medium; it can mean the internal communication of two components or the interaction between two components, unless otherwise expressly limited. Those skilled in the art can understand the specific meaning of the above terms in this application according to the specific circumstances.

[0019] Furthermore, if the embodiments of this application involve descriptions such as "first" or "second," these descriptions are for descriptive purposes only and should not be construed as indicating or implying their relative importance or implicitly specifying the number of technical features indicated. Therefore, a feature defined with "first" or "second" may explicitly or implicitly include at least one of those features. Additionally, the meaning of "and / or" throughout the text includes three parallel solutions; for example, "A and / or B" includes solution A, solution B, or a solution where both A and B are satisfied simultaneously. Furthermore, the technical solutions of the various embodiments can be combined with each other, but this must be based on the ability of those skilled in the art to implement them. When the combination of technical solutions is contradictory or impossible to implement, it should be considered that such a combination of technical solutions does not exist and is not within the scope of protection claimed in this application.

[0020] Figure 1 This is a schematic diagram of the overall structure of an aircraft grounding wire leakage alarm device provided in an exemplary embodiment of this application, as shown below. Figure 1 As shown, the device includes: a device body, which is sleeved on the aircraft grounding wire, and a leakage current alarm circuit is provided inside the device body. The leakage current alarm circuit is used to detect leakage current in the aircraft grounding wire through magnetic induction and provide leakage current warning.

[0021] In this embodiment, a leakage current alarm device is installed on the aircraft grounding wire, and a leakage current alarm circuit based on the principle of magnetic induction is integrated inside the device. This enables non-contact, real-time detection and alerting of leakage current in the aircraft grounding wire, effectively avoiding problems such as poor contact and complex structure caused by traditional contact detection. At the same time, the leakage current alarm circuit can provide an immediate alert when abnormal leakage is detected, which helps to promptly detect potential leakage hazards in unattended or complex operating environments, prevents ground personnel from accidentally touching the ground and causing electric shock, and thus enhances the safety and intelligence level of ground support operations.

[0022] In another exemplary embodiment, such as Figure 2As shown, the leakage current alarm circuit includes a power supply module 10, an electromagnetic induction module 20, a delay alarm module 30, and a self-test module 40. The power supply module 10 supplies power to the electromagnetic induction module 20, the delay alarm module 30, and the self-test module 40. The electromagnetic induction module 20 senses leakage current anomalies in the aircraft grounding wire. The delay alarm module 30 issues an alarm after a preset delay following the detection of a leakage current anomaly by the electromagnetic induction module 20. The self-test module 40 performs a self-test on the status of the electromagnetic induction module 20 and the delay alarm module 30.

[0023] In another exemplary embodiment, the power module 10 includes a solar charger and a rechargeable dry cell battery U1, wherein the solar charger is electrically connected to the rechargeable dry cell battery U1.

[0024] In this embodiment, the power module 10 consists of a solar charger and rechargeable dry cell batteries, primarily used to power the entire leakage current alarm device. During normal operation, the solar charger converts ambient light energy into electrical energy to charge the dry cell batteries, ensuring a stable and continuous power supply for the system. When solar power is insufficient, the rechargeable dry cell batteries provide independent power, ensuring continuous operation of the device even at night or in low-light conditions. This design achieves the goal of low power consumption and long battery life, meeting the usage requirements under long-term unattended conditions in the field.

[0025] In another exemplary embodiment, the electromagnetic induction module 20 includes an induction coil L1, a capacitor C1, an optocoupler OPTO (e.g., a 4N32), an audible and visual alarm light H1, a first matching resistor R1, and a cut-off switch SW1. The induction coil L1 is wound around the aircraft grounding wire. A first end of the induction coil L1 is connected to a first end of the cut-off switch SW1, and a second end of the induction coil L1 is connected to a first grounding terminal GND1. The second end of the cut-off switch SW1 and the first end of the first matching resistor R1 are connected to form a first node N1. The first terminal of the optocoupler OPTO is connected to the first node N1, and the second terminal of the capacitor C1 is connected to the first ground terminal GND1; the first terminal of the audible and visual alarm light H1 is connected to the first node N1, and the second terminal of the audible and visual alarm light H1 is connected to the first ground terminal GND1; the first output terminal of the optocoupler OPTO is connected to the first ground terminal GND1; the second output terminal of the optocoupler OPTO is connected to the input terminal of the delay alarm module 30; and the third output terminal of the optocoupler OPTO is connected to the second ground terminal GND2.

[0026] In this embodiment, the electromagnetic induction module 20 utilizes the principle of electromagnetic induction to achieve real-time detection and preliminary alarm of leakage current. When a leakage current exceeding the threshold passes through the aircraft grounding wire, the induction coil L1 generates an induced voltage signal under the action of magnetic field changes. The induced voltage signal is transmitted to the first node N1 via the cut-off switch SW1 and drives the audible and visual alarm light H1 to illuminate, thereby realizing on-site leakage warning. Simultaneously, the induced voltage signal is filtered and smoothed by the RC filter circuit composed of the first matching resistor R1 and capacitor C1, suppressing high-frequency interference fluctuations, thereby inputting a relatively stable voltage signal to the input terminal of the optocoupler OPTO. After the light-emitting diode inside the optocoupler OPTO is turned on, it excites the phototransistor, causing the second output terminal of the optocoupler OPTO to be turned on, thereby transmitting the leakage signal to the delayed alarm module 30.

[0027] By setting up an optocoupler OPTO, electrical isolation between the induced voltage signal and subsequent circuits can be achieved. When the leakage current exceeds a set threshold, the LED inside the optocoupler OPTO conducts, driving the phototransistor to output a control signal to trigger subsequent functional circuits such as the delay alarm module. This effectively avoids damage to the control circuit caused by high-voltage interference and current backflow. This structure not only enhances the anti-interference capability and operational stability of the trigger circuit but also improves the response accuracy and safety of the leakage alarm, meeting the reliable operation requirements in complex electromagnetic environments. Furthermore, in this embodiment, the output of the optocoupler OPTO is connected to both the first ground terminal GND1 and the second ground terminal GND2, forming a dual grounding structure. This further enhances the electrical isolation performance and anti-interference capability of the trigger circuit. The first ground terminal GND1 is used for grounding the front-end analog detection circuits such as the induction coil and the audible and visual alarm light H1, while the second ground terminal GND2 is dedicated to grounding the subsequent control circuit where the optocoupler output signal is located. By physically isolating the two ground potentials, interference or false triggering of the control module caused by high-frequency interference, potential fluctuations or large current backflow in the leakage signal can be effectively avoided. At the same time, noise accumulation caused by current loops and ground coupling is prevented, thereby improving the stability and reliability of the entire alarm system in complex electromagnetic environments.

[0028] Finally, it should be noted that the electromagnetic induction module 20 has a dual alert mechanism: on the one hand, the audible and visual alarm light H1 can be lit immediately to indicate the current leakage status; on the other hand, the delayed alarm module 30 is driven by the optocoupler output signal to perform subsequent recording and delayed alarm, enhancing the continuity and safety of the alarm. Furthermore, the connection of capacitor C1 can effectively suppress interference, improving circuit stability and false alarm tolerance.

[0029] In another exemplary embodiment, the delay alarm module 30 includes a reset switch SW2, a delay disconnect relay K1, an electric counter M1, a second matching resistor R2, and a delay audible and visual alarm lamp H2. The first terminal of the delay disconnect relay K1 serves as the input terminal of the delay alarm module 30. The reset switch SW2 is connected to the second terminal of the delay disconnect relay K1. The first normally open contact 1 and the second normally open contact 2 of the delay disconnect relay K1 are connected in series with the second matching resistor R2 to form a self-locking circuit. The third normally open contact 3 and the fourth normally open contact 4 of the delay disconnect relay K1 are connected to the first terminal of the delay audible and visual alarm lamp H2, and the second terminal of the delay audible and visual alarm lamp H2 is connected to the second ground terminal GND2. The fifth normally open contact 5 of the delay disconnect relay K1 is connected to the first input terminal of the self-test module 40, and the sixth normally open contact 6 of the delay disconnect relay K1 is connected to the first terminal of the electric counter M1 and the second input terminal of the self-test module 40. The second terminal of the electric counter M1 is connected to the second ground terminal GND2. In this embodiment, when the LED in the optocoupler illuminates, it triggers the phototransistor in the optocoupler to conduct. At this time, the time-delayed disconnect relay K1 will engage contacts 1 and 2 to form a self-locking circuit. Even if the leakage current disappears, the time-delayed disconnect relay K1 will still operate, illuminating the delayed audible and visual alarm H2 via contacts 3 and 4. This will alert staff to the previous leakage event within a set time period. Another function of the time-delayed disconnect relay K1 is to automatically disconnect the power supply, improving battery life. Simultaneously, it can activate the electric counter M1 via contacts 5 and 6 to count leakage events, informing staff of the number of previous leakage events. Furthermore, by setting a reset switch SW2, after an alarm is triggered, the K1 circuit can be disconnected via the reset switch SW2, terminating the self-locking state. H2 will then extinguish, and M1 will stop counting, allowing the trigger circuit to re-enter the monitoring standby state, ready for the next leakage event detection.

[0030] It should be noted that the reason this application uses a delayed alarm module 30 for delayed alarm is that leakage current often appears briefly and disappears quickly due to momentary factors such as contact jitter and arc jumping. If only instantaneous sensing is relied upon, the alarm may disappear immediately after being triggered, leading to missed alarms or difficulty in detection. Therefore, this device establishes a delayed alarm mechanism by setting up a delayed alarm module 30. Through the self-locking function of the delayed disconnect relay K1, the short-term leakage signal can be converted into a continuous alarm output, ensuring that even in noisy or unattended environments, on-site personnel can clearly perceive the alarm status. At the same time, this mechanism can drive the electric counter to accurately record leakage events, avoiding missed records and improving data traceability; the delay processing also effectively filters high-frequency interference, enhancing the stability and anti-interference capability of the trigger circuit in complex electromagnetic environments.

[0031] In another exemplary embodiment, the self-test module 40 includes a lamp detection switch SB1, a first diode D1, and a second diode D2. The anode of the second diode D2 serves as the first input terminal of the self-test module 40, and the cathode of the second diode D2 serves as the second input terminal of the self-test module 40. The anode of the first diode D1 is connected to the anode of the second diode D1, and the cathode of the first diode D1 is connected to the first node N1. The lamp detection switch SB1 includes a first normally open contact 1, a second normally open contact 2, a first normally closed contact 3, and a second normally closed contact 4. The first normally open contact 1 and the first normally closed contact 3 are connected to the power module 10, the second normally open contact 2 is connected to the anodes of the first diode D1 and the second diode D2, and the second normally closed contact 4 is connected to the first terminal of the lamp detection switch SB1.

[0032] In this embodiment, the self-test module 40 uses a double-pole double-throw lamp test switch SB1, a first diode D1, and a second diode D2 to achieve effective self-testing and current isolation protection for the electromagnetic induction module 20 and the delay alarm module 30. When the lamp test switch SB1 switches to the self-test state, its first normally open contact 1 and second normally open contact 2 close, connecting the self-test circuit. This allows the power supply current to provide a test voltage to the electromagnetic induction module 20 via the first diode D1 and the second diode D2, simulating a leakage current scenario to verify whether key components such as the induction coil and optocoupler respond normally. At the same time, the first normally closed contact 3 and the second normally closed contact 4 of the lamp test switch SB1 open, effectively cutting off the power supply path of the delay alarm module 30. This prevents the delay relay K1 from being mistakenly triggered due to the conduction of the optocoupler OPTO during the self-test process, thus avoiding the continuous operation of the counter M1 and the audible and visual alarm lamp H2. To further prevent system short circuits or malfunctions that may be caused by current crosstalk and reverse power supply, the first diode D1 configured in the self-test module 40 is used to prevent the induced current in the electromagnetic induction circuit from flowing back into the power supply module or the delay module, while the second diode D2 prevents the power supply current of the delay module from accidentally entering the induction module, thereby achieving effective isolation of the current path between different functional modules.

[0033] Through the above design, the self-test module 40 can not only perform functional tests on the delay alarm module 30, but also significantly improve the operational safety and stability of the trigger circuit, avoiding false alarms and system failures.

[0034] In another exemplary embodiment, this application also provides an aircraft grounding wire leakage alarm system, the system including the apparatus as described in any of the preceding embodiments.

[0035] In another exemplary embodiment, this application also provides a method for alarming leakage current in an aircraft grounding wire, the method comprising the following steps: S1: The electromagnetic induction module performs magnetic induction detection on the aircraft grounding wire. When there is leakage current in the aircraft grounding wire, the electromagnetic induction module generates a magnetic induction voltage signal and issues the first alarm. S2: The electromagnetic induction module isolates the magnetic induction voltage signal and transmits it to the delayed alarm module; S3: The delayed alarm module is triggered and a second alarm is issued.

[0036] In this embodiment, the electromagnetic induction module and the delayed alarm module described in this application achieve graded alarm and reliable prompting for leakage current in the aircraft grounding wire. When leakage current occurs on the grounding wire, the electromagnetic induction module immediately generates an induced voltage signal and triggers the first audible and visual alarm, promptly issuing an initial warning to on-site personnel. Simultaneously, this signal is transmitted to the delayed alarm module after isolation via an optocoupler, ensuring that subsequent control circuits are not affected by high-voltage interference. Upon receiving the isolation signal, the delayed alarm module is triggered to activate the relay self-locking mechanism, providing a continuous second audible and visual alarm prompt, and simultaneously driving a counter to record events. This method effectively avoids missed alarms, false alarms, and instantaneous signal loss, improves the stability and identifiability of the alarm system in complex electromagnetic environments, and significantly enhances the timeliness and reliability of leakage current protection.

[0037] In another exemplary embodiment, the method further includes the following steps: S4: Perform a self-test on the electromagnetic induction module and the delay alarm module.

[0038] In this embodiment, the purpose of the self-test is to simulate a leakage current signal under non-leakage conditions, verifying whether the electromagnetic induction module can generate and transmit the induction signal normally, and whether the delayed alarm module can accurately respond and trigger the audible and visual alarm and counting functions. Through this self-test process, potential device failures, power supply abnormalities, or line breaks in the system can be detected in a timely manner, avoiding the loss of alarms due to system failure when actual leakage occurs, thereby significantly improving the system's safety, reliability, and maintainability.

[0039] Finally, it should be noted that the above descriptions are merely optional examples of this application and are not intended to limit this application. Although this application has been described in detail with reference to the foregoing embodiments, those skilled in the art can still modify the technical solutions described in the foregoing embodiments or make equivalent substitutions for some of the technical features. Any modifications, equivalent substitutions, improvements, etc., made within the spirit and principles of this application should be included within the protection scope of this application.

Claims

1. An aircraft ground power cord arcing alarm device, comprising: The device includes: The main body of the device is sleeved on the aircraft grounding wire; The device body is equipped with a leakage current alarm circuit. The leakage alarm circuit is used to detect leakage current in the aircraft grounding wire through magnetic induction and provide leakage current warning. The leakage current alarm circuit includes a power supply module, an electromagnetic induction module, a time-delay alarm module, and a self-test module, wherein... The power module is used to supply power to the electromagnetic induction module, the delay alarm module and the self-test module; The electromagnetic induction module is used to detect leakage current abnormalities in the aircraft grounding wire. The delayed alarm module is used to issue an alarm after a preset time delay after the electromagnetic induction module detects the leakage abnormality. The self-test module is used to perform a self-test on the status of the electromagnetic induction module and the delay alarm module. The electromagnetic induction module includes an induction coil, a capacitor, an optocoupler, an audible and visual alarm light, a first matching resistor, and a cut-off switch. An induction coil is wrapped around the aircraft grounding wire, with a first end of the induction coil connected to a first end of a cut-off switch and a second end of the induction coil connected to a first grounding terminal. The second end of the cut-off switch and the first end of the first matching resistor are connected to form a first node, and the second end of the first matching resistor is connected to the input end of the optocoupler. The first end of the capacitor is connected to the first node, and the second end of the capacitor is connected to the first ground terminal. The first end of the audible and visual alarm light is connected to the first node, and the second end of the audible and visual alarm light is connected to the first grounding terminal. The first output terminal of the optocoupler is connected to the first ground terminal; The second output terminal of the optocoupler is connected to the input terminal of the delay alarm module; The third output terminal of the optocoupler is connected to the second ground terminal; The delay alarm module includes: The components include a reset switch, a time-delay disconnect relay, an electric counter, a second matching resistor, and a time-delayed audible and visual alarm light. The first terminal of the time-delay disconnect relay serves as the input terminal of the time-delay alarm module; A reset switch is connected to the second terminal of the time-delay disconnect relay; The first normally open contact and the second normally open contact of the time-delay disconnect relay are connected in series with the second matching resistor to form a self-locking circuit; The third and fourth normally open contacts of the time-delay disconnect relay are connected to the first terminal of the time-delayed audible and visual alarm light, and the second terminal of the time-delayed audible and visual alarm light is connected to the second ground terminal. The fifth normally open contact of the time-delay disconnect relay is connected to the first input terminal of the self-test module, and the sixth normally open contact of the time-delay disconnect relay is connected to the first terminal of the electric counter and the second input terminal of the self-test module. The second terminal of the electric counter is connected to the second ground terminal; The self-test module includes: Lamp test switch, first diode and second diode, wherein, The anode of the second diode serves as the first input terminal of the self-test module; The cathode of the second diode serves as the second input terminal of the self-test module; The anode of the first diode is connected to the anode of the second diode, and the cathode of the first diode is connected to the first node; The lamp inspection switch includes a first normally open contact and a second normally open contact, as well as a first normally closed contact and a second normally closed contact. The first normally open contact and the first normally closed contact are connected to the power module. The second normally open contact is connected to the anode of the first diode and the second diode. The second normally closed contact is connected to the first end of the lamp inspection switch. The lamp inspection switch is a double-pole double-throw switch.

2. The apparatus of claim 1, wherein, The power module includes a solar charger and a rechargeable dry cell battery, with the solar charger electrically connected to the rechargeable dry cell battery.

3. An aircraft ground power cord arcing alarm system, comprising: The system includes the apparatus as described in claim 1 or 2.

4. A method for alarming leakage current in aircraft grounding wires based on the device described in claim 1, characterized in that, The method includes: The electromagnetic induction module is used to detect the magnetic induction of the aircraft grounding wire. When there is leakage current in the aircraft grounding wire, the electromagnetic induction module generates a magnetic induction voltage signal and issues the first alarm. The electromagnetic induction module isolates the magnetic induction voltage signal and transmits it to the delayed alarm module; The delayed alarm module is triggered and a second alarm is issued.

5. The method according to claim 4, characterized in that, The method further includes: Perform self-tests on the electromagnetic induction module and the delay alarm module.

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