Circuit and practical training device for simulating failure of aircraft tail white navigation light
By designing a circuit and training device to simulate the malfunction of the aircraft tail white navigation light, the problem that traditional training benches cannot fully simulate aircraft system circuit malfunctions has been solved, achieving efficient troubleshooting and low-cost fault point measurement.
Patent Information
- Authority / Receiving Office
- CN · China
- Patent Type
- Patents(China)
- Current Assignee / Owner
- CHINA SOUTHERN AIRLINES CO LTD
- Filing Date
- 2024-04-30
- Publication Date
- 2026-07-31
AI Technical Summary
In existing technologies, the identification and troubleshooting of aircraft system circuit faults are inefficient. Traditional training benches cannot fully simulate specific system circuit faults, and the measurement process is complicated, time-consuming, and costly.
Design a circuit and training device for simulating the fault of the white navigation light on the tail of an aircraft, including a fault simulation module, a fault response module, a light group module and relays, etc. The fault signal is controlled through a human-machine interface display screen, so that the fault point can be directly measured without disassembling the circuit.
It improves the efficiency of troubleshooting aircraft tail white navigation lights, reduces costs and time consumption, and enables direct measurement and simulation of multiple fault points.
Smart Images
Figure CN118538072B_ABST
Abstract
Description
Technical Field
[0001] This application relates to the field of circuit technology, and in particular to a circuit and training device for simulating a malfunction of an aircraft tail white navigation light. Background Technology
[0002] In existing technologies, based on practical experience in civil aviation maintenance, faults in the circuit components and interconnections of various aircraft systems have consistently been frequent and difficult problems encountered by frontline maintenance personnel. Furthermore, the identification of aircraft system circuit diagrams, fault measurement and analysis, and standard circuit repair remain weaknesses for frontline maintenance staff. Traditional training benches for circuit measurement and troubleshooting use limited circuitry, only allowing for the mechanical setting of a few simple, fixed faults, without comprehensive coverage of specific system circuits. More importantly, measurement requires disassembling and reassembling the circuit, a cumbersome, time-consuming, and inefficient process that results in significant wear and tear on circuit components and severely limits reversibility requirements. Summary of the Invention
[0003] To address the aforementioned technical problems, this application proposes a circuit and training device for simulating a malfunction of an aircraft tail white navigation light.
[0004] This application provides a circuit for simulating a malfunction of an aircraft tail white navigation light, including:
[0005] The first fault simulation module includes a first switching unit and a second switching unit;
[0006] A fault response module, wherein a first terminal of the fault response module is electrically connected to one end of the first switching unit, and a second terminal of the fault response module is electrically connected to one end of the second switching unit; and,
[0007] The lamp assembly module has its first terminal electrically connected to the second terminal of the fault response module, and its third terminal electrically connected to the first terminal of the fault response module.
[0008] Furthermore, it also includes a second fault simulation module, which comprises a first transformer and a second transformer; wherein,
[0009] The first terminal of the first transformer is electrically connected to the first terminal of the lamp module, the second terminal of the first transformer is electrically connected to the second terminal of the lamp module, the third terminal of the first transformer is electrically connected to the second terminal of the fault response module, and the fourth terminal of the first transformer is grounded through a pin.
[0010] The first terminal of the second transformer is electrically connected to the third terminal of the lamp module, the second terminal of the second transformer is electrically connected to the fourth terminal of the lamp module, the third terminal of the second transformer is electrically connected to the first terminal of the fault response module, and the fourth terminal of the second transformer is grounded through a pin.
[0011] Furthermore, it also includes a first relay, the first end of which is electrically connected to the third end of the second transformer, and the second end of which is electrically connected between the first end of the fault response module and one end of the first switching unit.
[0012] Furthermore, it also includes a second relay, the first end of which is electrically connected to the third end of the first transformer, and the second end of which is electrically connected between the second end of the fault response module and one end of the second switching unit.
[0013] Furthermore, the fault response module includes a first fault switch, a second fault switch, and a third fault switch; wherein,
[0014] The first terminal of the first fault switch is electrically connected to the first terminal of the fault response module, the second terminal of the first fault switch is electrically connected to the first terminal of the third fault switch, the second terminal of the third fault switch is electrically connected to one end of the coil of the first relay, and the other end of the coil of the first relay is grounded.
[0015] The first terminal of the second fault switch is electrically connected to the second terminal of the fault response module, the second terminal of the second fault switch is electrically connected to one end of the coil of the second relay, and the other end of the coil of the second relay is grounded.
[0016] Furthermore, the lamp module includes a first bulb and a second bulb; wherein,
[0017] The two ends of the first bulb are respectively connected to the third and fourth ends of the lamp assembly module;
[0018] The two ends of the second bulb are respectively connected to the first end and the second end of the lamp module.
[0019] This application embodiment also provides a training device for simulating a malfunction of an aircraft tail white navigation light, including:
[0020] The circuit described in any of the above for simulating a malfunction of an aircraft tail white navigation light;
[0021] A display screen for human-computer interaction, the display screen having a fault signal controller, the fault signal controller being communicatively connected to the circuitry used to simulate a fault in the aircraft's tail white navigation light; and...
[0022] The test bench body, the circuit for simulating the malfunction of the aircraft tail white navigation light, and the display screen are all located on the test bench body.
[0023] Furthermore, the display screen is mounted on the platform body to define a receiving cavity for accommodating the circuitry used to simulate a fault in an aircraft tail white navigation light. The display screen is configured to receive user-input commands to control the fault signal controller to generate a corresponding fault signal.
[0024] Furthermore, the circuit for simulating the malfunction of the aircraft tail white navigation light is connected to the socket of the dark box via a plug, and the dark box is electrically connected to the fault signal controller and is located on the test bench body.
[0025] Furthermore, the circuit used to simulate a malfunction of the aircraft tail white navigation light is fixed to the test bench body with screws.
[0026] In summary, the embodiments of this application have at least the following beneficial effects:
[0027] Using the embodiments of this application, as many fault points as possible related to the white navigation light on the aircraft tail can be simulated, and all of these fault points can be directly measured without disassembling the circuit and / or other components, thereby improving troubleshooting efficiency and reducing troubleshooting costs. Attached Figure Description
[0028] Figure 1 This is a schematic diagram of the structure of a circuit for simulating a malfunction of an aircraft tail white navigation light, provided in an embodiment of this application;
[0029] Figure 2 This is a circuit diagram of a circuit used to simulate a malfunction of the white navigation light on an aircraft tail, provided in an embodiment of this application. Detailed Implementation
[0030] 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 some embodiments of this application, and not all 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.
[0031] In the description of this application, the terms "first," "second," "third," etc., are used for descriptive purposes only and should not be construed as indicating or implying relative importance or implicitly specifying the number of indicated technical features. Therefore, a feature defined with "first," "second," "third," etc., may explicitly or implicitly include one or more of that feature. In the description of this application, unless otherwise stated, "a plurality of" means two or more. In the description of this application, the term "comprising" and its variations are open-ended, meaning "including but not limited to." The term "based on" means "at least partially based on." The term "according to" means "at least partially according to." The term "one embodiment" means "at least one embodiment"; the term "another embodiment" means "at least one additional embodiment"; the term "some embodiments" means "at least some embodiments."
[0032] In the description of this application, it should be noted that, unless otherwise expressly specified and limited, the terms "installation," "connection," and "linking" should be interpreted broadly. For example, they can refer to a fixed connection, a detachable connection, or an integral connection; they can refer to a mechanical connection or an electrical connection; they can refer to a direct connection or an indirect connection through an intermediate medium; and they can refer to the internal connection between two components. Those skilled in the art can understand the specific meaning of the above terms in this application based on the specific circumstances.
[0033] In the description of this application, it should be noted that, unless otherwise defined, all technical and scientific terms used in this application have the same meaning as commonly understood by one of ordinary skill in the art. The terminology used in this application is for the purpose of describing specific embodiments only and is not intended to limit the application. Those skilled in the art can understand the specific meaning of the above terms in this application based on the specific circumstances.
[0034] See Figure 1 and Figure 2 The diagrams shown are a structural schematic and a circuit diagram of a circuit for simulating a malfunction of an aircraft tail white navigation light, according to embodiments of this application. The circuit for simulating a malfunction of an aircraft tail white navigation light includes:
[0035] The first fault simulation module includes a first switching unit 1LA and a second switching unit 2LA;
[0036] A fault response module 3LA, wherein a first terminal of the fault response module 3LA is electrically connected to one terminal of the first switching unit 1LA, and a second terminal X8 of the fault response module 3LA is electrically connected to one terminal of the second switching unit 2LA; and...
[0037] The lamp module 15LA has its first terminal X52 electrically connected to the second terminal X8 of the fault response module 3LA, and its third terminal X56 electrically connected to the first terminal of the fault response module 3LA.
[0038] Specifically, in this embodiment, the other end of the first switching unit 1LA and the other end of the second switching unit 2LA are respectively connected to an external power supply. The following illustrates the implementation principle of several fault numbers set in this embodiment, which can be used to determine how to conduct troubleshooting training using this embodiment.
[0039] Fault No. A1: The circuit used to simulate the fault of the aircraft tail white navigation light can be configured to control the first switch unit 1LA to trip in response to the A1 fault signal output by the fault signal controller, so that the power switch of the fault response module 3LA is selected to 1. At this time, the first terminal of the fault response module 3LA will be disconnected, which will disconnect the input current of the third terminal X56 of the lamp module 15LA, thus causing the lamp module 15LA to not light up.
[0040] Fault No. A2: The circuit used to simulate the fault of the aircraft tail white navigation light can be configured to control the second switch unit 2LA to trip in response to the A2 fault signal output by the fault signal controller, so that the power selection 2 of the fault response module 3LA is selected. At this time, the second terminal X8 of the fault response module 3LA will be disconnected, which will disconnect the input current of the first terminal X52 of the lamp module 15LA, thus causing the lamp module 15LA to not light up.
[0041] Fault No. A3: The circuit used to simulate a fault in the aircraft tail white navigation light can be configured to control a line fault (e.g., disconnect) from one end of the first switch unit 1LA to the first end of the fault response module 3LA in response to the fault signal output A3 from the fault signal controller, so that the power switch of the fault response module 3LA is selected to 1. At this time, the first end of the fault response module 3LA will be disconnected, which will also disconnect the input current of the third end X56 of the lamp module 15LA, thus causing the lamp module 15LA to not light up.
[0042] Fault No. A4: The circuit used to simulate a fault in the aircraft tail white navigation light can be configured to control a line fault (e.g., disconnect) from one end of the second switch unit 2LA to the second end X8 of the fault response module 3LA in response to the A4 fault signal output by the fault signal controller, so that the power switch 2 of the fault response module 3LA is selected. At this time, the second end X8 of the fault response module 3LA will be disconnected, which will disconnect the input current of the first end X52 of the lamp module 15LA, thus causing the lamp module 15LA to not light up.
[0043] For example, the embodiments of this application can be applied to the simulated troubleshooting of the tail white navigation light circuit of an A320 aircraft.
[0044] In one optional embodiment, a second fault simulation module 13LA is further included, the second fault simulation module 13LA comprising a first transformer and a second transformer; wherein,
[0045] The first terminal X51 of the first transformer is electrically connected to the first terminal X52 of the lamp module 15LA, the second terminal X53 of the first transformer is electrically connected to the second terminal X54 of the lamp module 15LA, the third terminal X44 of the first transformer is electrically connected to the second terminal X8 of the fault response module 3LA, and the fourth terminal X46 of the first transformer is grounded through a pin.
[0046] The first terminal X55 of the second transformer is electrically connected to the third terminal X56 of the lamp module 15LA. The second terminal X57 of the second transformer is electrically connected to the fourth terminal X58 of the lamp module 15LA. The third terminal X48 of the second transformer is electrically connected to the first terminal of the fault response module 3LA. The fourth terminal X50 of the second transformer is grounded through a pin.
[0047] Specifically, in the embodiments of this application, the implementation principle of several fault numbers set in the embodiments of this application is shown below. The implementation principle can be used to determine how to use the embodiments of this application for troubleshooting training.
[0048] Fault No. B6: In this embodiment, the pin connected to the fourth terminal X46 of the first transformer is normally disconnected, meaning the fourth terminal X46 of the first transformer is not grounded. The circuit used to simulate a fault in the aircraft tail white navigation light can be configured to control the pin connected to the fourth terminal X46 of the first transformer (i.e., ...) in response to the fault signal B6 output by the fault signal controller. Figure 2 When pin 5 of the first transformer is turned on, that is, the fourth terminal X46 of the first transformer is grounded, so that the power switch of the fault response module 3LA is selected 2. At this time, the second terminal X8 of the fault response module 3LA will be disconnected, which will disconnect the input current of the first terminal X52 of the lamp module 15LA, thus causing the lamp module 15LA to not light up.
[0049] Fault No. B7: In this embodiment, the pin connected to the fourth terminal X50 of the second transformer is normally disconnected, meaning the fourth terminal X50 of the second transformer is not grounded. The circuit used to simulate a fault in the aircraft tail white navigation light can be configured to control the pin connected to the fourth terminal X50 of the second transformer (i.e., ...) in response to the B7 fault signal output by the fault signal controller. Figure 2When pin 2 of the first transformer is turned on, the fourth terminal X50 of the second transformer is grounded, so that the power switch of the fault response module 3LA is selected as 1. At this time, the first terminal of the fault response module 3LA will be disconnected, which will disconnect the input current of the third terminal X56 of the lamp module 15LA, thus causing the lamp module 15LA to not light up.
[0050] Fault No. A8: The circuit used to simulate the fault of the aircraft tail white navigation light can be configured to respond to the A8 fault signal output by the fault signal controller, control the primary circuit of the first transformer to open (an open circuit occurs inside the primary winding of the transformer), so that the power switch of the fault response module 3LA is selected 2. At this time, the second terminal X8 of the fault response module 3LA will be disconnected, which will disconnect the input current of the first terminal X52 of the lamp module 15LA, thus causing the lamp module 15LA to not light up.
[0051] Fault No. A9: The circuit used to simulate the fault of the aircraft tail white navigation light can be configured to respond to the A9 fault signal output by the fault signal controller, control the secondary circuit of the first transformer to open (an open circuit occurs inside the secondary winding of the transformer), so that the power switch of the fault response module 3LA is selected 2. At this time, the second terminal X8 of the fault response module 3LA will be disconnected, which will disconnect the input current of the first terminal X52 of the lamp module 15LA, thus causing the lamp module 15LA to not light up.
[0052] Fault No. A10: The circuit used to simulate a fault in the aircraft tail white navigation light can be configured to respond to the A10 fault signal output by the fault signal controller, control the primary ground of the first transformer to be disconnected (the connection between the primary winding and the grounding system is disconnected or broken), so that the power switch of the fault response module 3LA is selected 2. At this time, the second terminal X8 of the fault response module 3LA will be disconnected, which will disconnect the input current of the first terminal X52 of the lamp module 15LA, thus causing the lamp module 15LA to not light up.
[0053] Fault No. A11: The circuit used to simulate a fault in the aircraft tail white navigation light can be configured to control the secondary ground of the first transformer to be disconnected in response to the A11 fault signal output by the fault signal controller (the connection between the secondary winding and the grounding system is disconnected or broken), so that the power switch of the fault response module 3LA is selected 2. At this time, the second terminal X8 of the fault response module 3LA will be disconnected, which will disconnect the input current of the first terminal X52 of the lamp module 15LA, thus causing the lamp module 15LA to not light up.
[0054] Fault No. A12: The circuit used to simulate the fault of the aircraft tail white navigation light can be configured to respond to the A12 fault signal output by the fault signal controller, control the primary circuit of the second transformer to open (an open circuit occurs inside the primary winding of the transformer), so that the power switch of the fault response module 3LA is selected to 1. At this time, the first terminal of the fault response module 3LA will be disconnected, which will also disconnect the input current of the third terminal X56 of the lamp module 15LA, thus causing the lamp module 15LA to not light up.
[0055] Fault No. A13: The circuit used to simulate a fault in the aircraft tail white navigation light can be configured to respond to the A13 fault signal output by the fault signal controller, control the secondary winding of the second transformer to open (an open circuit occurs inside the secondary winding of the transformer), so that the power switch of the fault response module 3LA is selected to 1. At this time, the first terminal of the fault response module 3LA will be disconnected, which will disconnect the input current of the third terminal X56 of the lamp module 15LA, thus causing the lamp module 15LA to not light up.
[0056] Fault No. A14: The circuit used to simulate a fault in the aircraft tail white navigation light can be configured to respond to the A14 fault signal output by the fault signal controller, control the primary ground of the second transformer to be disconnected (the connection between the primary winding and the grounding system is disconnected or broken), so that the power switch of the fault response module 3LA is selected to 1. At this time, the first terminal of the fault response module 3LA will be disconnected, which will disconnect the input current of the third terminal X56 of the lamp module 15LA, thus causing the lamp module 15LA to not light up.
[0057] Fault No. A15: The circuit used to simulate a fault in the aircraft tail white navigation light can be configured to control the secondary ground of the second transformer to be disconnected in response to the A15 fault signal output by the fault signal controller (the connection between the secondary winding and the grounding system is disconnected or broken), so that the power switch of the fault response module 3LA is selected to 1. At this time, the first terminal of the fault response module 3LA will be disconnected, which will also disconnect the input current of the third terminal X56 of the lamp module 15LA, thus causing the lamp module 15LA to not light up.
[0058] In an optional embodiment, a first relay 6LA is further included, wherein a first terminal X40 of the first relay 6LA is electrically connected to a third terminal X48 of the second transformer, and a second terminal X34 of the first relay 6LA is electrically connected between a first terminal of the fault response module 3LA and a terminal of the first switching unit 1LA.
[0059] It should be noted that in the embodiments of this application, under fault number A1 or fault number A3, the second terminal X34 of the first relay 6LA will have no power input, which will cause the third terminal X48 of the second transformer to have no power input, and further cause the input current of the third terminal X56 of the lamp module 15LA to be disconnected, thereby causing the lamp module 15LA to not light up.
[0060] In an optional embodiment, a second relay 7LA is further included, wherein a first terminal X30 of the second relay 7LA is electrically connected to a third terminal X44 of the first transformer, and a second terminal X24 of the second relay 7LA is electrically connected between a second terminal X8 of the fault response module 3LA and a terminal of the second switching unit 2LA.
[0061] It should be noted that in the case of fault number A2 or fault number A4 in this embodiment of the application, the second terminal X24 of the second relay 7LA will have no power input, which will cause the third terminal X44 of the first transformer to have no power input, and further cause the input current of the first terminal X52 of the lamp module 15LA to be disconnected, thereby causing the lamp module 15LA to not light up.
[0062] Specifically, in the embodiments of this application, the implementation principle of several fault numbers set in the embodiments of this application is shown below. The implementation principle can be used to determine how to use the embodiments of this application for troubleshooting training.
[0063] Fault No. A18: The circuit used to simulate a fault in the aircraft tail white navigation light can be configured to control a fault (e.g., disconnect) in the line from one end of the second switch unit 2LA to the second relay 7LA in response to the fault signal output A18 from the fault signal controller, so that the power switch 2 of the fault response module 3LA is selected. At this time, the second terminal X8 of the fault response module 3LA will be disconnected, which will disconnect the input current of the first terminal X52 of the lamp module 15LA, thus causing the lamp module 15LA to not light up.
[0064] In one optional implementation, the fault response module 3LA includes a first fault switch A, a second fault switch D, and a third fault switch B; wherein,
[0065] The first terminal of the first fault switch A is electrically connected to the first terminal of the fault response module 3LA, the second terminal X14 of the first fault switch A is electrically connected to the first terminal X10 of the third fault switch B, the second terminal X20 of the third fault switch B is electrically connected to one terminal X36 of the coil of the first relay 6LA, and the other terminal X42 of the coil of the first relay 6LA is grounded.
[0066] The first terminal X8 of the second fault switch D is electrically connected to the second terminal X8 of the fault response module 3LA, the second terminal X18 of the second fault switch D is electrically connected to one end X26 of the coil of the second relay 7LA, and the other end X32 of the coil of the second relay 7LA is grounded.
[0067] It should be noted that, in the embodiments of this application, the first fault switch A refers to... Figure 2 The fault response module 3LA shown includes 1A, 2A, and 3A. When 1A and 3A of the first fault switch A are connected, it indicates that the first fault switch A is open (i.e., the second terminal X14 of the first fault switch A is open). When 1A and 2A of the first fault switch A are connected, it indicates that the first fault switch A is on (i.e., the second terminal X14 of the first fault switch A is on). The second fault switch D refers to... Figure 2 The fault response module 3LA shown includes 1D, 2D, and 3D. When 1D and 2D of the second fault switch D are connected, it indicates that the second fault switch D is open (i.e., the second terminal X18 of the second fault switch D is open). When 1D and 3D of the second fault switch D are connected, it indicates that the second fault switch D is on (i.e., the second terminal X18 of the second fault switch D is on). The third fault switch B refers to... Figure 2 The fault response module 3LA shown has 1B, 2B, and 3B. When 1B and 3B of the third fault switch B are connected, it means that the third fault switch B is open (at this time, the second terminal X20 of the third fault switch B is open). When 1B and 2B of the third fault switch B are connected, it means that the third fault switch B is on (at this time, the second terminal X20 of the third fault switch B is on).
[0068] In one optional embodiment, the lamp module 15LA includes a first bulb and a second bulb; wherein,
[0069] The two ends of the first bulb are respectively connected to the third end X56 and the fourth end X58 of the lamp module 15LA;
[0070] The two ends of the second bulb are respectively connected to the first end X52 and the second end X54 of the lamp module 15LA.
[0071] Specifically, in the embodiments of this application, the implementation principle of several fault numbers set in the embodiments of this application is shown below. The implementation principle can be used to determine how to use the embodiments of this application for troubleshooting training.
[0072] Fault No. A16: The circuit used to simulate a fault in the aircraft tail white navigation light can be configured to control the second bulb to malfunction in response to the A16 fault signal output by the fault signal controller, so that the switch selection 2 of the fault response module 3LA is activated, at which time the lamp module 15LA does not light up.
[0073] Fault No. A17: The circuit used to simulate a fault in the aircraft tail white navigation light can be configured to control the first bulb to malfunction in response to the A17 fault signal output by the fault signal controller, so that the switch of the fault response module 3LA is selected to 1, at which time the lamp module 15LA is not lit.
[0074] This application embodiment also provides a training device for simulating a malfunction of an aircraft tail white navigation light, including:
[0075] The circuit described in any of the above for simulating a malfunction of an aircraft tail white navigation light;
[0076] A display screen for human-computer interaction, the display screen having a fault signal controller, the fault signal controller being communicatively connected to the circuitry used to simulate a fault in the aircraft's tail white navigation light; and...
[0077] The test bench body, the circuit for simulating the malfunction of the aircraft tail white navigation light, and the display screen are all located on the test bench body.
[0078] For example, the display screen can be a first display screen with touch function, a second display screen composed of buttons and a display, etc.
[0079] It should be noted that the fault signal controller in this embodiment can be used to set corresponding fault modes (e.g., the various fault numbers mentioned above) for the circuit used to simulate the fault of the aircraft tail white navigation light according to the user input instructions received by the display screen.
[0080] In one alternative embodiment, the display screen is mounted on the stand body to define a receiving cavity for accommodating the circuitry used to simulate a fault in an aircraft tail white navigation light. The display screen is configured to receive user-input commands to control the fault signal controller to generate a corresponding fault signal.
[0081] It should be noted that the fault signal generated by the fault signal controller in the embodiments of this application can be used to instruct the circuit used to simulate the fault of the aircraft tail white navigation light to enter the corresponding fault mode (e.g., the various fault numbers mentioned above).
[0082] In one optional embodiment, the circuit for simulating a fault in the aircraft tail white navigation light is connected to a socket in a dark box via a plug, and the dark box is electrically connected to the fault signal controller and is mounted on the test bench body.
[0083] It is understood that, in this embodiment of the application, the circuit used to simulate the malfunction of the aircraft tail white navigation light is electrically connected to the fault signal controller through the dark box.
[0084] For example, the plug may be a threaded plug.
[0085] In one alternative implementation, the circuit for simulating a malfunction of the aircraft tail white navigation light is fixed to the test bench body by screws.
[0086] In summary, the embodiments of this application have at least the following beneficial effects:
[0087] Using the embodiments of this application, as many fault points as possible related to the white navigation light on the aircraft tail can be simulated, and all of these fault points can be directly measured without disassembling the circuit and / or other components, thereby improving troubleshooting efficiency and reducing troubleshooting costs.
[0088] Through the above description of the embodiments, those skilled in the art can clearly understand that this application can be implemented by means of software plus necessary hardware platforms, or it can be implemented entirely by hardware. Based on this understanding, all or part of the technical solutions of this application that contribute to the background technology can be embodied in the form of a software product. This computer software product can be stored in a storage medium, such as ROM / RAM, magnetic disk, optical disk, etc., and includes several instructions to cause a computer device (which may be a personal computer, server, or network device, etc.) to execute the methods described in various embodiments or some parts of the embodiments of this application.
[0089] The above description is the preferred embodiment of this application. It should be noted that for those skilled in the art, several improvements and modifications can be made without departing from the principle of this application, and these improvements and modifications are also considered to be within the scope of protection of this application.
Claims
1. A circuit for simulating a failure of an aircraft tail white navigation light, comprising: The simulation troubleshooting applied to the white tail light circuit of the A320 aircraft includes: The first fault simulation module includes a first switching unit and a second switching unit; A fault response module, wherein a first terminal of the fault response module is electrically connected to one end of the first switching unit, and a second terminal of the fault response module is electrically connected to one end of the second switching unit; and, A lamp assembly module, wherein the first end of the lamp assembly module is electrically connected to the second end of the fault response module, and the third end of the lamp assembly module is electrically connected to the first end of the fault response module; It also includes a second fault simulation module, which comprises a first transformer and a second transformer; wherein, The first terminal of the first transformer is electrically connected to the first terminal of the lamp module, the second terminal of the first transformer is electrically connected to the second terminal of the lamp module, the third terminal of the first transformer is electrically connected to the second terminal of the fault response module, and the fourth terminal of the first transformer is grounded through a pin. The first terminal of the second transformer is electrically connected to the third terminal of the lamp module, the second terminal of the second transformer is electrically connected to the fourth terminal of the lamp module, the third terminal of the second transformer is electrically connected to the first terminal of the fault response module, and the fourth terminal of the second transformer is grounded through a pin. It also includes a first relay, the first end of which is electrically connected to the third end of the second transformer, and the second end of which is electrically connected between the first end of the fault response module and one end of the first switching unit; It also includes a second relay, the first end of which is electrically connected to the third end of the first transformer, and the second end of which is electrically connected between the second end of the fault response module and one end of the second switching unit.
2. The circuit for simulating a malfunction of an aircraft tail white navigation light as described in claim 1, characterized in that, The fault response module includes a first fault switch, a second fault switch, and a third fault switch; wherein... The first terminal of the first fault switch is electrically connected to the first terminal of the fault response module, the second terminal of the first fault switch is electrically connected to the first terminal of the third fault switch, the second terminal of the third fault switch is electrically connected to one end of the coil of the first relay, and the other end of the coil of the first relay is grounded. The first terminal of the second fault switch is electrically connected to the second terminal of the fault response module, the second terminal of the second fault switch is electrically connected to one end of the coil of the second relay, and the other end of the coil of the second relay is grounded.
3. The circuit for simulating a failure of an aircraft tail navigation light according to any one of claims 1-2, characterized in that, The lamp module includes a first bulb and a second bulb; wherein... The two ends of the first bulb are respectively connected to the third and fourth ends of the lamp assembly module; The two ends of the second bulb are respectively connected to the first end and the second end of the lamp module.
4. A training device for simulating a failure of an aircraft tail navigation light, characterized in that, include: The circuit for simulating a white navigation light malfunction on an aircraft tail as described in any one of claims 1-2; A display screen for human-computer interaction, the display screen having a fault signal controller, the fault signal controller being communicatively connected to the circuitry used to simulate a fault in the aircraft's tail white navigation light; and... The test bench body, the circuit for simulating the malfunction of the aircraft tail white navigation light, and the display screen are all located on the test bench body.
5. The training device for simulating a malfunction of an aircraft tail white navigation light as described in claim 4, characterized in that, The display screen is mounted on the platform body to define a receiving cavity for accommodating the circuit for simulating a fault in an aircraft tail white navigation light. The display screen is configured to receive user input commands to control the fault signal controller to generate a corresponding fault signal.
6. The training device for simulating the malfunction of the aircraft tail navigation light according to claim 5, characterized in that, The circuit for simulating a fault in the white navigation light of an aircraft tail is connected to a socket in a dark box via a plug. The dark box is electrically connected to the fault signal controller and is mounted on the test bench.
7. The training device for simulating a malfunction of a rear navigation light of an aircraft according to any one of claims 4 to 6, characterized in that The circuit used to simulate a malfunction of the aircraft tail white navigation light is fixed to the test bench body with screws.