Fault detection apparatus and method for an aircraft

Abstract

The application discloses a kind of aircraft fault detection device and method, belong to aircraft on-board equipment ground maintenance technical field, the device includes detection device ontology, charging port is provided on the detection device ontology, battery, detection display, connector and working switch;The detection display is electrically connected with the connector, the connector is used to be connected with integrated disc box, the detection display includes: connector pin drive / acquisition state setting part, for the working state of the connector is set;Disc box inner component detection state display part, for pin drive / acquisition state and element detection result are displayed.The aircraft fault detection device and method of the above can be used in the application, the rapid detection and accurate positioning of aircraft integrated disc box fault can be realized, the rapid exclusion of aircraft power failure is realized, and maintenance cost is reduced.

Description

Technical Field

[0001] This invention relates to the field of ground maintenance technology for airborne equipment of aircraft, and in particular to a fault detection device and method for aircraft. Background Technology

[0002] With the development of aircraft integration, and the adoption of centralized power distribution in aircraft, many relays, contactors and power supply busbars are integrated inside the power distribution box, making the power distribution box of the aircraft large in size and weight, and limiting the maintenance space.

[0003] In current aircraft testing and flight trials, the status of relays, contactors, and power supply busbars inside the integrated power distribution box is mostly monitored using limited bus test parameters. When a power supply failure occurs in the aircraft, it will cause communication abnormalities, making it impossible to accurately locate the fault entirely through bus test data. Furthermore, opening and inspecting the integrated power distribution box requires extensive preparation work, making it difficult to open and inspect. Even if it can be opened, simple visual inspection cannot directly locate the fault, and checking the integrity of contactors during live operation is particularly difficult.

[0004] During aircraft operation, a faulty contactor inside the integrated control panel can cause the aircraft's electrical system to malfunction, resulting in significant economic losses for aircraft testing, flight trials, and other operations. Summary of the Invention

[0005] The purpose of this invention is to provide a fault detection device and method for aircraft. By installing and docking with the integrated panel interface of the aircraft, the health status of relays and contactors in the integrated panel can be obtained in a timely manner when the aircraft is not powered on, thereby realizing rapid detection and accurate location of faults in the integrated panel of the aircraft, enabling rapid troubleshooting of power supply faults in the aircraft, and reducing maintenance costs.

[0006] To achieve the above objectives, the present invention provides a fault detection device for an aircraft, comprising a detection device body, wherein the detection device body is provided with a charging port, a battery, a detection display, a connector, and a working switch; the detection display is electrically connected to the connector, the connector being used for docking with an integrated panel enclosure, and the detection display comprising:

[0007] The connector pin drive / acquisition status setting section is used to set the working status of the connector;

[0008] The component detection status display section inside the enclosure is used to display the pin drive / acquisition status and component detection results.

[0009] Preferably, the charging port is installed inside the detection device body and is electrically connected to the battery.

[0010] Preferably, the battery is installed inside the detection device body and is electrically connected to the charging port, detection display and connector.

[0011] Preferably, the connector pin drive / acquisition status setting section includes:

[0012] A connector pin drive status setting module, which includes several connector pin indicators for selecting different connector pins;

[0013] The pin status setting / acquisition module includes high / low level setting and level duration setting, which are used to set the high / low level and time of the input drive signal, respectively.

[0014] The GND definition and setting module is used to define and set the GND of the connector;

[0015] The GND definition and setting modules for contactors, relays, busbars, fuses, and circuit breakers are all equipped with a "Complete Pin Setting" control switch.

[0016] The connector pin drive / acquisition status setting section also includes a "Complete Physical Connection" confirmation control switch, a "Start Status Acquisition" control switch, a "Start Output Drive" control switch, and a "Stop Output Drive and Acquisition" control switch, all of which are used to control the working status of the detection device.

[0017] Preferably, the component detection status display section inside the disk enclosure includes:

[0018] The circuit breaker status indicator, busbar status indicator, fuse status indicator, relay status indicator, and contactor status indicator are provided, and each of the circuit breaker status indicator, busbar status indicator, fuse status indicator, relay status indicator, and contactor status indicator is provided with a component status normal indicator and a component status fault indicator on one side, for the status of the corresponding tested components.

[0019] It also includes a working status indicator light, which is located on one side of the "Start Status Acquisition" control switch, the "Start Output Drive" control switch, and the "Stop Output Drive and Acquisition" control switch, and is used to display the working status of the corresponding control switch;

[0020] Battery level warning indicator, used to display the device's battery level information;

[0021] Battery charging indicator, used to display the charging status of the device.

[0022] The present invention also provides a method for detecting faults in an aircraft, comprising the following steps:

[0023] S1. First, check the battery charge to ensure that the battery is fully charged before the test.

[0024] S2. Connect the connector to the integrated panel box physically, turn on the working switch, click "Complete Physical Connection" to confirm the control switch, and ensure a normal connection;

[0025] S3. Click the definition settings modules for GND, contactor pins, relay pins, busbar pins, fuse pins, and circuit breaker pins respectively to complete the pin definition settings for the components to be tested.

[0026] S4. In the connector pin driver status setting module of the display, select the connector pin to be tested, and in the pin status setting / acquisition module, set the high and low level and the duration of the level of the connector pin, and complete the status setting of the connector pin as needed.

[0027] S5. Click the "Start Status Acquisition" control switch to obtain the current status of the circuit breaker, busbar, fuse, relay and contactor components;

[0028] S6. Click the "Start Output Drive" control switch to start the output drive. Observe the component status normal indicator and component status fault indicator, obtain the information of circuit breaker status indication, busbar status indication, fuse status indication, relay status indication, and contactor status indication, and determine the health status of the tested component.

[0029] S7. Click the "Stop Output Drive and Acquisition" control switch to turn off the working switch, disconnect the physical connection between the connector and the integrated panel, and complete this component fault detection.

[0030] Preferably, in step S1, the battery power alarm indicator is checked to ensure that the battery is fully charged. If the battery power is insufficient and needs to be charged, the charging port is connected to an external charging power source, the charging indicator is observed, and charging is completed.

[0031] Therefore, the present invention employs the above-mentioned fault detection device and method for aircraft. By installing and docking with the interface of the aircraft integrated panel, it can promptly obtain the health status of relays and contactors in the integrated panel when the aircraft is not powered on, thereby realizing rapid detection and accurate location of faults in the aircraft integrated panel, enabling rapid elimination of aircraft power supply faults and reducing maintenance costs.

[0032] The technical solution of the present invention will be further described in detail below with reference to the accompanying drawings and embodiments. Attached Figure Description

[0033] Figure 1 This is a schematic diagram of an embodiment of a fault detection device and method for an aircraft according to the present invention;

[0034] Figure 2 This is a schematic diagram of the connection relationship of an embodiment of the fault detection device and method for an aircraft according to the present invention;

[0035] Figure 3 This is a schematic diagram of the detection display interface of an embodiment of the fault detection device and method for an aircraft according to the present invention.

[0036] Figure Labels

[0037] 1. Detection device body; 10. Charging port; 20. Battery; 30. Detection display; 301. Connector pin drive / acquisition status setting section; 30101. Connector pin drive status setting module; 30102. Connector pin indicator; 30103. Pin status setting / acquisition module; 30104. High / low level setting; 30105. Level duration setting; 30106. GND definition setting module; 30107. "Complete pin setting" control switch; 30108. Contactor pin definition setting module; 30109. Relay pin definition setting module; 30110. Busbar pin definition setting module; 30111. Fuse pin definition setting module; 30112. Circuit breaker pin definition setting module; 3 0113, "Complete Physical Connection" Confirmation Control Switch; 30114, "Start Status Acquisition" Control Switch; 30115, "Start Output Drive" Control Switch; 30116, "Stop Output Drive and Acquisition" Control Switch; 302, Component Detection Status Display Section in the Panel; 30201, Circuit Breaker Status Indicator; 30202, Busbar Status Indicator; 30203, Fuse Status Indicator; 30204, Relay Status Indicator; 30205, Contactor Status Indicator; 30206, Component Status Normal Indicator; 30207, Component Status Fault Indicator; 30208, Working Status Indicator; 30209, Battery Power Alarm Indicator; 30210, Battery Charging Indicator; 40, Connector; 50, Working Switch; 60, Integrated Panel. Detailed Implementation

[0038] The technical solution of the present invention will be further described below with reference to the accompanying drawings and embodiments.

[0039] Example 1

[0040] like Figure 1 and Figure 2 As shown, the present invention provides a fault detection device for an aircraft, including a detection device body 1, on which a charging port 10, a storage battery 20, a detection display 30, a connector 40 and a working switch 50 are provided.

[0041] The charging port 10 is installed inside the detection device body 1 and is electrically connected to the battery 20. The battery 20 is installed inside the detection device body 1 and is electrically connected to the charging port 10, the detection display 30, and the connector 40. The detection display 30 is electrically connected to the connector 40, which is used to interface with various components within the integrated enclosure 60.

[0042] The test display 30 includes: a connector pin drive / acquisition status setting section 301, used to set the operating status of the connector 40; and a component test status display section 302, used to display the pin drive / acquisition status and component test results.

[0043] like Figure 3 As shown, the connector pin drive / acquisition status setting section 301 includes:

[0044] The connector pin drive status setting module 30101 includes several connector pin indicators 30102 for selecting different connector pins. The pin status setting / acquisition module 30103 includes high / low level settings 30104 and level duration settings 30105, used for setting the high / low level and duration of the input drive signal, respectively.

[0045] The GND definition setting module 30106 is used to define and set the GND of connector 40. The contactor pin definition setting module 30108, relay pin definition setting module 30109, busbar pin definition setting module 30110, fuse pin definition setting module 30111, and circuit breaker pin definition setting module 30112; and the GND definition setting modules 30106, 30108, 30109, 30110, 30111, and 30112 all have a "Complete Pin Setting" control switch 30107.

[0046] The connector pin drive / acquisition status setting section 301 also includes a "Complete physical connection" confirmation control switch 30113, a "Start status acquisition" control switch 30114, a "Start output drive" control switch 30115, and a "Stop output drive and acquisition" control switch 30116, all of which are used to control the working status of the detection device.

[0047] The component detection status display section 302 inside the disk enclosure includes:

[0048] The circuit breaker status indicator 30201, busbar status indicator 30202, fuse status indicator 30203, relay status indicator 30204, and contactor status indicator 30205 are each equipped with a component status normal indicator 30206 and a component status fault indicator 30207 on one side, for the corresponding tested component status.

[0049] It also includes a working status indicator 30208, which is located on one side of the "Start Status Acquisition" control switch 30114, the "Start Output Drive" control switch 30115, and the "Stop Output Drive and Acquisition" control switch 30116, and is used to display the working status of the corresponding control switch; a battery power alarm indicator 30209, which is used to display the power information of the device; and a battery charging indicator 30210, which is used to display the charging status of the device.

[0050] The present invention also provides a method for detecting faults in an aircraft, comprising the following steps:

[0051] S1. First, check the charge level of battery 20 to ensure that battery 20 is fully charged before the test.

[0052] Check the battery power warning indicator 30209 to ensure that the battery 20 is fully charged. If the battery 20 is low on power and needs to be charged, connect the charging port 10 to an external power source and observe the battery charging indicator 30210 to complete the charging process.

[0053] S2. Connect connector 40 to integrated panel 60 physically, turn on work switch 50, click "Complete physical connection" to confirm control switch 30113, and ensure normal connection.

[0054] S3. Click on the definition settings modules for GND (30106), contactor pins (30108), relay pins (30109), busbar pins (30110), fuse pins (30111), and circuit breaker pins (30112) respectively to complete the pin definition settings for the components to be tested.

[0055] S4. In the connector pin drive status setting module 30101 of the detection display 30, select the connector pin to be detected, and set the high and low levels and the duration of the level of the connector pin in the pin status setting / acquisition module 30103 to complete the status setting of the connector pin as needed.

[0056] S5. Click the “Start Status Acquisition” control switch 30114 to obtain the current status of the circuit breaker, busbar, fuse, relay and contactor components.

[0057] S6. Click the "Start Output Drive" control switch 30115 to start the output drive. Observe the component status normal indicator 30206 and component status fault indicator 30207. Obtain information from the circuit breaker status indicator 30201, busbar status indicator 30202, fuse status indicator 30203, relay status indicator 30204, and contactor status indicator 30205 to determine the health status of the tested component.

[0058] S7. Click the "Stop Output Drive and Acquisition" control switch 30116, turn off the working switch 50, disconnect the physical connection between connector 40 and integrated panel 60, and complete this component fault detection.

[0059] Therefore, the present invention employs the above-mentioned fault detection device and method for aircraft. By installing and docking with the interface of the aircraft integrated panel, it can promptly obtain the health status of relays and contactors in the integrated panel when the aircraft is not powered on, thereby realizing rapid detection and accurate location of faults in the aircraft integrated panel, enabling rapid elimination of aircraft power supply faults and reducing maintenance costs.

[0060] Finally, it should be noted that the above embodiments are only used to illustrate the technical solutions of the present invention and not to limit them. Although the present invention has been described in detail with reference to preferred embodiments, those skilled in the art should understand that modifications or equivalent substitutions can still be made to the technical solutions of the present invention, and these modifications or equivalent substitutions cannot cause the modified technical solutions to deviate from the spirit and scope of the technical solutions of the present invention.

Claims

1. A fault detection device for an aircraft, characterized in that: The device includes a detection device body, which is equipped with a charging port, a battery, a detection display, a connector, and a working switch. The detection display is electrically connected to the connector, the connector being used for mating with the integrated panel enclosure, and the detection display includes: The connector pin drive / acquisition status setting section is used to set the working status of the connector; The component detection status display section inside the enclosure is used to display the pin drive / acquisition status and component detection results; The connector pin drive / acquisition status setting section includes: A connector pin drive status setting module, which includes several connector pin indicators for selecting different connector pins; The pin status setting / acquisition module includes high / low level setting and level duration setting, which are used to set the high / low level and time of the input drive signal, respectively. The GND definition and setting module is used to define and set the GND of the connector; The GND definition and setting modules for contactors, relays, busbars, fuses, and circuit breakers are all equipped with a "Complete Pin Setting" control switch. The connector pin drive / acquisition status setting section also includes a "Complete Physical Connection" confirmation control switch, a "Start Status Acquisition" control switch, a "Start Output Drive" control switch, and a "Stop Output Drive and Acquisition" control switch, all of which are used to control the working status of the detection device.

2. The fault detection device for an aircraft according to claim 1, characterized in that: The charging port is installed inside the main body of the detection device and is electrically connected to the battery.

3. The fault detection device for an aircraft according to claim 1, characterized in that: The battery is installed inside the main body of the detection device and is electrically connected to the charging port, the detection display and the connector.

4. The aircraft fault detection device according to claim 1, characterized in that: The component detection status display section inside the disk enclosure includes: The circuit breaker status indicator, busbar status indicator, fuse status indicator, relay status indicator, and contactor status indicator are provided, and each of the circuit breaker status indicator, busbar status indicator, fuse status indicator, relay status indicator, and contactor status indicator is provided with a component status normal indicator and a component status fault indicator on one side, for the status of the corresponding tested components. It also includes a working status indicator light, which is located on one side of the "Start Status Acquisition" control switch, the "Start Output Drive" control switch, and the "Stop Output Drive and Acquisition" control switch, and is used to display the working status of the corresponding control switch; Battery level warning indicator, used to display the device's battery level information; Battery charging indicator, used to display the charging status of the device.

5. The detection method of the aircraft fault detection device according to claim 4, characterized in that, Includes the following steps: S1. First, check the battery charge to ensure that the battery is fully charged before the test. S2. Connect the connector to the integrated panel box physically, turn on the working switch, click "Complete Physical Connection" to confirm the control switch, and ensure a normal connection; S3. Click the definition settings modules for GND, contactor pins, relay pins, busbar pins, fuse pins, and circuit breaker pins respectively to complete the pin definition settings for the components to be tested. S4. In the connector pin driver status setting module of the display, select the connector pin to be tested, and in the pin status setting / acquisition module, set the high and low level and the duration of the level of the connector pin, and complete the status setting of the connector pin as needed. S5. Click the "Start Status Acquisition" control switch to obtain the current status of the circuit breaker, busbar, fuse, relay and contactor components; S6. Click the "Start Output Drive" control switch to start the output drive. Observe the component status normal indicator and component status fault indicator, obtain the information of circuit breaker status indication, busbar status indication, fuse status indication, relay status indication, and contactor status indication, and determine the health status of the tested component. S7. Click the "Stop Output Drive and Acquisition" control switch to turn off the working switch, disconnect the physical connection between the connector and the integrated panel, and complete this component fault detection.

6. The detection method of the aircraft fault detection device according to claim 5, characterized in that: In step S1, check the battery power alarm indicator to ensure that the battery is fully charged. If the battery power is insufficient, it needs to be charged. Connect the charging port to an external charging power source, observe the battery charging indicator, and complete the charging process.

Images