Civil aviation maintenance circuit analog training equipment

Abstract

This application discloses a simulation training device for civil aviation maintenance circuits, comprising: a test bench; a central control console disposed within the test bench; and a simulated fault circuit detachably installed within the test bench and communicatively connected to the central control console. The simulated fault circuit includes: a control switch module, a first terminal of which is connected to a first external power supply; a first relay, the first and second terminals of which are respectively connected to the second terminal of the control switch module; a second relay, the first terminal of which is grounded, and the second terminal of which is connected to the third terminal of the first relay; and a fault response module, the first terminal of which is connected to the fourth terminal of the first relay, and the second terminal of which is grounded. This device can simulate circuit fault points in some systems of an aircraft, and these fault points can be directly measured, thereby improving troubleshooting efficiency and reducing troubleshooting costs.

Description

Technical Field

[0001] This application relates to the field of circuit technology, and in particular to a simulation training device for civil aviation maintenance circuits. 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 simulation training device for civil aviation maintenance circuits, which can simulate circuit fault points in some systems of an aircraft. These fault points can be directly measured, thereby improving troubleshooting efficiency and reducing troubleshooting costs.

[0004] To achieve the above objectives, embodiments of this application provide a simulation training device for civil aviation maintenance circuits, comprising:

[0005] The stand itself;

[0006] The central control panel is located within the main body of the platform; and,

[0007] The simulated fault circuit is detachably installed in the chassis body and communicates with the central control console;

[0008] The simulated fault circuit includes:

[0009] A control switch module, wherein a first terminal of the control switch module is used to connect to a first external power source;

[0010] A first relay, wherein the first end and the second end of the first relay are respectively connected to the second end of the control switch module;

[0011] A second relay, wherein the first terminal of the second relay is grounded, and the second terminal of the second relay is connected to the third terminal of the first relay; and,

[0012] A fault response module, wherein the first terminal of the fault response module is connected to the fourth terminal of the first relay, and the second terminal of the fault response module is grounded.

[0013] Furthermore, the simulated fault circuit also includes:

[0014] The first switch is connected between the first terminal of the control switch module and the first external power supply.

[0015] Second switch;

[0016] The third relay has a first terminal connected to the third terminal of the control switch module, a second terminal of the third relay for connecting to the first external power supply via the first trip switch, and a third terminal of the third relay for connecting to the second external power supply via the second trip switch.

[0017] An aircraft engine simulation module is configured to simulate the operating state of an aircraft engine and control the third relay according to the operating state.

[0018] Furthermore, the simulated fault circuit also includes:

[0019] The test switch module includes a first test switch unit and a second test switch unit. The second terminal of the second relay is connected to the third terminal of the first relay through the first test switch unit. The first terminal of the control switch module is connected to the first terminal of the first relay through the second test switch unit.

[0020] Furthermore, the simulated fault circuit also includes:

[0021] Third switch;

[0022] Fourth switch;

[0023] A fault indicator light, one end of which is used to connect to a third external power supply via the third trip switch 17;

[0024] The current detection module includes:

[0025] A logic gate, wherein the first input terminal of the logic gate is used to connect to a fourth external power supply via the fourth jumper switch;

[0026] A current detection switch, one end of which is connected to the other end of the fault indicator light, and the other end of which is grounded; the controlled end of the current detection switch is connected to the output terminal of the logic gate; and,

[0027] A current sensing coil, one end of which is connected to the second input terminal of the logic gate, and the other end of which is grounded. At least a portion of the coil is arranged adjacent to the circuit to be detected, which is at least a portion of the circuit between the first terminal of the fault response module and the fourth terminal of the first relay.

[0028] The current sensing coil is configured to generate a current and output it to the second input terminal of the logic gate when a current is detected in the circuit to be detected, so that the logic gate can determine the control signal required to be output by its own output terminal.

[0029] Furthermore, the other end of the fault indicator light is connected to the fifth terminal of the first relay, and one end of the current detection switch is connected to the sixth terminal of the first relay.

[0030] Furthermore, the simulation training equipment also includes:

[0031] A basic component symbol panel is provided on the surface of the test bench body. The surface of the basic component symbol panel opposite to the test bench body is provided with multiple basic component symbol measurement points that correspond one-to-one with all preset fault measurement points in the simulated fault circuit. Each basic component symbol measurement point is used to synchronously simulate the current and / or voltage of the corresponding fault measurement point.

[0032] Furthermore, the center console is configured as follows:

[0033] Receive control commands input by the user, and set a fault state for at least one of the preset fault measurement points according to the control commands; and / or,

[0034] Query information related to the preset fault measurement point.

[0035] Furthermore, the central control unit includes a host computer with a display.

[0036] Furthermore, the simulation training equipment also includes a storage device located on the platform body.

[0037] Furthermore, the simulated fault circuit is detachably mounted in the test bench body using screws.

[0038] In summary, the embodiments of this application have at least the following beneficial effects:

[0039] By using the embodiments of this application, it is possible to simulate circuit fault points in some systems of an aircraft, and these fault points can be directly measured, thereby improving troubleshooting efficiency and reducing troubleshooting costs. Attached Figure Description

[0040] Figure 1 This is a schematic diagram of the structure of a simulation training device for civil aviation maintenance circuits provided in an embodiment of this application;

[0041] Figure 2 This is a schematic diagram of the simulated fault circuit provided in the embodiments of this application. Detailed Implementation

[0042] 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.

[0043] 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."

[0044] 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.

[0045] 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.

[0046] See Figure 1 This shows a schematic diagram of the structure of a simulation training device for civil aviation maintenance circuits provided in an embodiment of this application, and see also... Figure 2 The diagram shows a structural schematic of the simulated fault circuit 300 provided in an embodiment of this application. The simulation training equipment for the civil aviation maintenance circuit includes:

[0047] The platform body is 100;

[0048] The central control console 200 is located within the platform body 100; and,

[0049] The simulated fault circuit 300 is detachably installed inside the test bench body 100 and communicates with the central control console 200;

[0050] The simulated fault circuit 300 includes:

[0051] A control switch module S1, wherein the first terminal 3NO of the control switch module S1 is used to connect to a first external power supply 115VAC;

[0052] The first relay K1, with its first terminal X1 and second terminal C2 connected to the second terminal 3C of the control switch module S1;

[0053] The second relay R595 has its first terminal C1 grounded and its second terminal C2 connected to the third terminal X2 of the first relay K1; and,

[0054] The fault response module M171 has its first terminal 1 connected to the fourth terminal C3 of the first relay K1, and its second terminal 6 grounded.

[0055] It should be noted that in this embodiment, the first terminal X1 and the third terminal X2 of the first relay K1 are the two ends of the coil of the first relay K1, and the second terminal C2 and the fourth terminal C3 are the two ends of the first contact of the first relay K1. When the control switch module S1 is in the ON position, the 115V AC power will pass through the control switch module S1 → the second relay R595 → ground, so that the first relay K1 is energized and closed, and the 115V AC power supplied to the fault response module M171 through the first contact of the first relay K1 (the two ends are the second terminal C2 and the fourth terminal C3) is turned off, so that the fault response module M171 indicates the fault.

[0056] It should be noted that in this embodiment, the second relay R595 can be an air-to-ground relay, used to detect whether the aircraft has left the ground (C2 closes to C3, indicating AIR) or is in contact with the ground (C2 closes to C1, indicating GND). When the air-to-ground relay R595 remains in the air (i.e., away from the ground), K1 remains de-energized, thereby allowing 115V AC power to be supplied to the fault response module M171 via the first contact of the first relay K1 (the two ends are the second terminal C2 and the fourth terminal C3), causing the fault response module M171 to indicate a fault.

[0057] It is understood that the simulated fault circuit 300 is communicatively connected to the central control console 200. One or more circuit elements in the simulated fault circuit 300 can be configured to respond to fault commands from the central control console 200, setting their own fault state so that the simulated fault circuit 300 is in the fault condition required by the user, allowing the user to use the simulated fault circuit 300 for troubleshooting training. For example:

[0058] The line 9 between the first terminal 3NO of the control switch module S1 and the first external power supply 115VAC can be configured to be disconnected;

[0059] The line 13 between the first terminal 1 of the fault response module M171 and the fourth terminal C3 of the first relay K1 can be configured to be disconnected, and / or the second terminal 6 of the fault response module M171 can be disconnected from the ground 12 to which it is connected.

[0060] After the above settings are configured, a simulated fault circuit 300 that simulates the corresponding fault can be obtained, allowing users to measure the simulated fault circuit 300 using testing instruments, thereby achieving the purpose of troubleshooting training. However, it should be understood that this embodiment can also configure related fault states for other circuit elements and / or lines in the simulated fault circuit 300, thereby simulating various required fault conditions, and is not limited to the examples above.

[0061] For example, the fault response module M171 can be a sensor located inside the aircraft, such as a TAT (Total Air Temperature).

[0062] In an optional implementation, the simulated fault circuit 300 further includes:

[0063] The first switch C238 connects the first terminal 3NO of the control switch module S1 to the first external power supply 115VAC.

[0064] Second jumper switch C1946;

[0065] The third relay R1070 has its first terminal A1 connected to the third terminal 3NC of the control switch module S1, its second terminal A2 connected to the first external power supply 115VAC via the first trip switch C238, and its third terminal X1 connected to the second external power supply 28VDC via the second trip switch C1946.

[0066] Aircraft engine simulation modules R1071, R1072, M1808 and / or M1809 are configured to simulate the operating state of an aircraft engine and control the third relay R1070 according to the operating state.

[0067] It should be noted that in this embodiment, the first terminal A1 and the second terminal A2 of the third relay R1070 are the two ends of the contacts of the third relay R1070, and the third terminal X1 and the fourth terminal X2 are the two ends of the coil of the third relay R1070. The third relay R1070 is connected to the aircraft engine simulation module through the fourth terminal X2, so that the aircraft engine simulation module can control the third relay R1070 by adjusting the current flowing through the coil of the third relay R1070. When the control switch module S1 is in the AUTO position, the second terminal 3C and the third terminal 3NC of the control switch module S1 are connected. At this time, the 115V AC power supplied to the fault response module M171 is controlled by the third relay R1070, and the operation of the third relay R1070 is controlled by the operation of the aircraft engine simulation module. When any engine in the aircraft engine simulation module is running, R1070 is energized, so that the 115V AC power is supplied to the fault response module M171.

[0068] In this embodiment, a fault can be set in the following location:

[0069] Line 15 between the first terminal A1 of the third relay R1070 and the third terminal 3NC of the control switch module S1;

[0070] Line 5 between the second terminal A2 of the third relay R1070 and the first trip switch C238;

[0071] Line 8 between the third terminal X1 of the third relay R1070 and the second trip switch C1946;

[0072] Fault point 1 is set on the first trip switch C238;

[0073] Fault point 4 is set on the second trip switch C1946.

[0074] In an optional implementation, the simulated fault circuit 300 further includes:

[0075] The test switch module S8 includes a first test switch unit and a second test switch unit. The second terminal C2 of the second relay R595 is connected to the third terminal X2 of the first relay K1 through the first test switch unit. The first terminal 3NO of the control switch module S1 is connected to the first terminal X1 of the first relay K1 through the second test switch unit.

[0076] In an optional implementation, the simulated fault circuit 300 further includes:

[0077] Third jumper switch C317;

[0078] Fourth switch C569;

[0079] The fault indicator light TEMP PROBE is used to connect a third external power supply 28V / 16V DC via the third trip switch C317.

[0080] The current detection module includes:

[0081] The logic gate AND1, the first input terminal of which is used to connect to a fourth external power supply 28VDC through the fourth jumper switch C569;

[0082] A current detection switch K2, one end of which is connected to the other end of the fault indicator light, and the other end of which is grounded; the controlled terminal of the current detection switch K2 is connected to the output terminal of the logic gate AND1; and,

[0083] A current sensing coil L1, one end of which is connected to the second input terminal of the logic gate AND1, and the other end of which is grounded. At least a portion of the coil of the current sensing coil L1 is arranged adjacent to the line to be detected, which is at least a portion of the line between the first terminal 1 of the fault response module M171 and the fourth terminal C3 of the first relay K1.

[0084] The current sensing coil L1 is configured to generate a current and output it to the second input terminal of the logic gate AND1 when a current is detected in the circuit to be detected, so that the logic gate AND1 can determine the control signal required to be output by its own output terminal.

[0085] In this embodiment, the presence of current in the circuit under test can be detected by the current sensing coil L1 (i.e., determining whether the fault response module M171 has current input), thereby indicating whether the current detection switch K2 is turned on or off, so that the fault indicator light displays the corresponding status. For example, this logic gate can be an AND gate.

[0086] In this embodiment, a fault can be set in the following location:

[0087] Fault point 2 is located on the third trip switch C317;

[0088] Fault point 3 is located on the fourth trip switch C569;

[0089] Line 7 between the first input of logic gate AND1 and the fourth jumper switch C569;

[0090] Line 6 between one end of the fault indicator light and the third trip switch C317.

[0091] In one optional implementation, the other end of the fault indicator light is connected to the fifth terminal A2 of the first relay K1, and one end of the current detection switch K2 is connected to the sixth terminal A3 of the first relay K1.

[0092] It should be noted that, in this embodiment, the fifth terminal A2 and the sixth terminal A3 of the first relay K1 are the two ends of the second contact of the first relay K1, which is controlled by the coil of the first relay K1 and is turned on or off simultaneously with the first contact. This is because when the first contact is off, the fault response module M171 will not be powered by the first external power supply 115VAC, so the current detection module does not need to perform current detection on the circuit to be tested, thereby disconnecting the power supply to both the current detection module and the fault indicator.

[0093] In one optional implementation, the simulation training equipment further includes:

[0094] A basic component symbol panel 400 is disposed on the surface of the test bench body 100. The surface of the basic component symbol panel 400 opposite to the test bench body 100 is provided with a plurality of basic component symbol measurement points corresponding one-to-one with all preset fault measurement points in the simulated fault circuit 300. Each basic component symbol measurement point is used to synchronously simulate the current and / or voltage of the corresponding fault measurement point.

[0095] It should be noted that the surface of the basic component symbol panel 400 in this embodiment can be provided with multiple basic component symbol measurement points. Each basic component symbol measurement point can lead out a wire to the corresponding fault measurement point, so that the basic component symbol measurement point can synchronously simulate the current and / or voltage of the corresponding fault measurement point, so that the user can measure the current and / or voltage of the fault measurement point by directly measuring the basic component symbol measurement point.

[0096] The fault measurement points in this embodiment may include any one or more of the points mentioned above that can be used to set faults, which will not be elaborated further here.

[0097] Additionally, in some cases, see Figure 2 In this embodiment, the fault measurement points may also include common ground fault points 10 to 55, which are respectively connected to points 23, 39, 32, 33, 40 and 35 in the simulated fault circuit 300 to simulate the ground fault situation of each of the above points.

[0098] In one alternative implementation, the center console 200 is configured as follows:

[0099] Receive control commands input by the user, and set a fault state for at least one of the preset fault measurement points according to the control commands; and / or,

[0100] Query information related to the preset fault measurement point.

[0101] For example, after the central control console 200 of this embodiment is powered on, it can enter the administrator system to complete the teacher information entry and related settings, then enter the teacher system to complete the student information entry and related settings (such as setting exam or training questions and going online), and then enter the student system to start training or exams (instructing students to measure relevant circuits to determine fault points, mark faults on relevant circuit diagrams on the touch control screen of the central control console 200, so that the faults are resolved (if necessary), and submit the exam papers together after all students have completed the exams (or automatically end when the time is up), and finally the system automatically evaluates, records and displays the scores.

[0102] The central control software configured in the central control console 200 of this embodiment mainly consists of three parts: an instructor control system, a student operating system, and a resource station. It can perform single-device training or simultaneous training on multiple devices according to actual conditions, offering high flexibility. It possesses numerous functions such as information retrieval, instructor and student account management, setting exam and training fault questions, fault point marking and troubleshooting, and automatic system evaluation. Each line construction training device is equipped with a resource station function, providing operating specifications, instructions, and other related electronic materials. It should also have a technical data update function, allowing instructors to update technical data in a timely manner.

[0103] This embodiment allows external devices running Android, HarmonyOS, Windows, Apple, and other operating systems to connect to the central control system of this platform, replacing the functions of the central control console 200 and achieving cross-platform and cross-device interaction. These external devices can be mobile devices such as laptops and tablets. This embodiment also supports remote login for students to access, view, and download resources from the resource site; and remote login for instructors to perform operations such as fault setting for training and examinations, and student management. The combination of multiple devices in this embodiment can achieve a master-slave relationship, where one host controls multiple slave devices, interconnected via their own wireless LAN. The central control console 200 in this embodiment is equipped with a cross-system data interface. Through this interface, student and instructor role information can be easily and quickly imported into the central control console 200, while student training information and examination results can be easily and quickly exported to other systems.

[0104] In one alternative implementation, the central control unit 200 includes a host computer with a display.

[0105] Optionally, the simulation training equipment in this embodiment may further include a power supply module for supplying power to the simulated fault circuit 300 and / or the central control console 200.

[0106] In one optional embodiment, the simulation training equipment further includes a storage device 500 disposed on the platform body 100.

[0107] For example, the storage device 500 in this embodiment may have three drawer-type and three pull-door-type storage compartments. The drawer-type storage compartments can store documents and small tools; the pull-door-type storage compartments can hold large equipment and three replaceable module storage areas.

[0108] In one alternative implementation, the simulated fault circuit 300 is detachably mounted within the test bench body 100 by screws.

[0109] In summary, the embodiments of this application have at least the following beneficial effects:

[0110] By using the embodiments of this application, it is possible to simulate circuit fault points in some systems of an aircraft, and these fault points can be directly measured, thereby improving troubleshooting efficiency and reducing troubleshooting costs.

[0111] 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.

[0112] 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. An analog training device for civil aviation maintenance circuitry, characterized in that, include: The stand itself; The central control panel is located within the main body of the platform. as well as, The simulated fault circuit is detachably installed in the chassis body and communicates with the central control console; The simulated fault circuit includes: A control switch module, wherein a first terminal of the control switch module is used to connect to a first external power source; A first relay, wherein the first end and the second end of the first relay are respectively connected to the second end of the control switch module; A second relay, wherein the first terminal of the second relay is grounded, and the second terminal of the second relay is connected to the third terminal of the first relay; and, A fault response module, wherein the first terminal of the fault response module is connected to the fourth terminal of the first relay, and the second terminal of the fault response module is grounded; The simulated fault circuit also includes: Third switch; Fourth switch; A fault indicator light, one end of which is used to connect to a third external power supply via the third trip switch 17; The current detection module includes: A logic gate, wherein the first input terminal of the logic gate is used to connect to a fourth external power supply via the fourth jumper switch; A current detection switch, one end of which is connected to the other end of the fault indicator light, and the other end of which is grounded; the controlled end of the current detection switch is connected to the output terminal of the logic gate; and, A current sensing coil, one end of which is connected to the second input terminal of the logic gate, and the other end of which is grounded. At least a portion of the coil is arranged adjacent to the circuit to be detected, which is at least a portion of the circuit between the first terminal of the fault response module and the fourth terminal of the first relay. The current sensing coil is configured to generate a current and output it to the second input terminal of the logic gate when a current is detected in the circuit to be detected, so that the logic gate can determine the control signal required to be output by its own output terminal. The other end of the fault indicator light is connected to the fifth terminal of the first relay, and one end of the current detection switch is connected to the sixth terminal of the first relay. The first and third ends of the first relay are the two ends of the first relay coil, and the second and fourth ends are the two ends of the first contact of the first relay. The fifth and sixth terminals of the first relay are respectively the two ends of the second contact of the first relay. The second contact is controlled by the coil of the first relay and is turned on or off simultaneously with the first contact.

2. The simulation training equipment for civil aviation maintenance circuits as described in claim 1, characterized in that, The simulated fault circuit also includes: The first switch is connected between the first terminal of the control switch module and the first external power supply. Second switch; The third relay has a first terminal connected to the third terminal of the control switch module, a second terminal of the third relay for connecting to the first external power supply via the first trip switch, and a third terminal of the third relay for connecting to the second external power supply via the second trip switch. An aircraft engine simulation module is configured to simulate the operating state of an aircraft engine and control the third relay according to the operating state.

3. The simulation training equipment for civil aviation maintenance circuits as described in claim 2, characterized in that, The simulated fault circuit also includes: The test switch module includes a first test switch unit and a second test switch unit. The second terminal of the second relay is connected to the third terminal of the first relay through the first test switch unit. The first terminal of the control switch module is connected to the first terminal of the first relay through the second test switch unit.

4. The simulation training equipment for civil aviation maintenance circuits as described in claim 1, characterized in that, The simulation training equipment also includes: A basic component symbol panel is provided on the surface of the test bench body. The surface of the basic component symbol panel opposite to the test bench body is provided with multiple basic component symbol measurement points that correspond one-to-one with all preset fault measurement points in the simulated fault circuit. Each basic component symbol measurement point is used to synchronously simulate the current and / or voltage of the corresponding fault measurement point.

5. The simulation training equipment for civil aviation maintenance circuits as described in claim 4, characterized in that, The central control panel is configured as follows: Receive control commands input by the user, and set a fault state for at least one of the preset fault measurement points according to the control commands; and / or, Query information related to the preset fault measurement point.

6. The simulation training equipment for civil aviation maintenance circuits as described in claim 1, characterized in that, The central control unit includes a host computer with a display.

7. The simulation training equipment for civil aviation maintenance circuits as described in claim 1, characterized in that, The simulation training equipment also includes a storage device located on the platform body.

8. The simulation training equipment for civil aviation maintenance circuits as described in claim 1, characterized in that, The simulated fault circuit is detachably mounted in the test bench body using screws.

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