Circuit and practical training device for simulating aircraft standard line fault
By designing circuits used to simulate aircraft standard line failures, the problem of lack of fault simulation capabilities in the existing technology is solved, efficient fault simulation and fault scheduling training is achieved, and the fault scheduling capabilities of trained personnel are improved.
Patent Information
- Application Number
- CN202421440245.1
- Authority / Receiving Office
- CN · China
- Patent Type
- Utility models(China)
- Current Assignee / Owner
- Filing Date
- 2024-06-21
- Publication Date
- 2025-04-25
- Estimated Expiration
- 2034-06-21
AI Technical Summary
The prior art lacks the ability to simulate aircraft standard line failures, resulting in low training efficiency and quality.
A circuit including a divided power input control module, a total power input control module, a connector plug module, a relay module and a status display module is designed to simulate various types of faults in standard aircraft lines.
It realizes efficient simulation and fault removal of aircraft standard line faults. The circuit design is highly consistent with the working principle of the aircraft system and helps to cultivate maintenance personnel's fault removal capabilities.
Smart Images
Figure CN222801296U_ABST
Abstract
Description
Technical Field
[0001] The utility model relates to the technical field of circuit design, in particular to a circuit and a training device for simulating standard line faults of aircraft. Background Art
[0002] The traditional skill circuit measurement and troubleshooting training device has a simple circuit, a small layout, and only sets common simple fixed faults such as short circuit, open circuit, and adhesion. The difficulty of the fault is also the same, which does not conform to the working principle of the aircraft system and the actual maintenance situation. The existing technology lacks circuits that simulate standard aircraft circuit faults, and the teaching efficiency and quality are low during the troubleshooting training process. Utility Model Content
[0003] The technical problem to be solved by the utility model is to provide an intelligent training device and system for standard line construction, which can simulate and troubleshoot various types of aircraft standard line faults, highly conform to the working principle of the aircraft system, and help cultivate the maintenance personnel's troubleshooting ability for aircraft standard lines.
[0004] To solve the above technical problems, the embodiment of the utility model provides a circuit for simulating a standard line fault of an aircraft, comprising a sub-power input control module, a main power input control module, a first connector plug module, a relay module, and a status display module;
[0005] The first end of the divided power input control module is connected to the first DC power supply, and the second end of the divided power input control module is connected to the first end of the relay module through the first connector plug module; the second end of the relay module is connected to the first end of the status display module; the first end of the main power input control module is connected to the second DC power supply, and the second end of the main power input control module is connected to the second input end of the status display module through the first connector plug module.
[0006] As an improvement of the above solution, the sub-power input control module includes a first jump switch and a sub-power switch, and the first jump switch and the sub-power switch are used to control the first DC power supply to be input into the relay module through the first connector plug module.
[0007] As an improvement of the above solution, the main power input control module includes a second jump switch, and the second jump switch controls the second DC power supply to supply power to the status display module through the first connector plug module.
[0008] As an improvement of the above-mentioned scheme, the first connector plug module includes a grounding terminal block and a first connector plug, which inputs the signal of the main power control module into the first connector plug to power the status display module, and respectively inputs the signal of the sub-power control module and the grounding signal generated by the grounding terminal block into the first connector plug to control the operation of the relay module.
[0009] As an improvement of the above solution, the relay module includes a relay, which receives a signal from the first connector plug module, obtains a relay state signal through the relay and inputs it into the state display module.
[0010] As an improvement of the above scheme, the status display module includes a second connector plug, several status lights and several buzzers, which is connected to the relay module and the main power input control module through the second connector plug, and controls the status lights and the buzzer according to the relay status signal.
[0011] As an improvement of the above-mentioned scheme, the circuit for simulating aircraft standard line faults includes a plurality of equal numbers of divided power input control modules and relay modules, the first end of each of the divided power input control modules is connected to the first DC power supply, and the second end of each of the divided power input control modules is connected to the first end of a relay module.
[0012] The present utility model also provides a training device for simulating a standard line fault of an aircraft, comprising:
[0013] The stand body;
[0014] A host computer, the host computer is mounted on the platform body to define a receiving cavity; and
[0015] The circuit for simulating a standard line fault of an aircraft as described in any of the above items is accommodated in the accommodating cavity.
[0016] As an improvement of the above-mentioned scheme, the host computer includes a fault signal controller, which is communicatively connected to the circuit for simulating the standard line fault of the aircraft, and responds to the fault simulation instruction of the host computer to control the circuit for simulating the standard line fault of the aircraft to generate a specified fault.
[0017] As an improvement of the above solution, the circuit for simulating aircraft standard line faults is connected to the socket of the dark box through a plug, and the dark box is electrically connected to the fault signal controller and is arranged on the test stand body.
[0018] In summary, the embodiments of the present invention have at least the following beneficial effects:
[0019] By adopting the embodiment of the utility model, various types of faults of aircraft standard circuits can be simulated and troubleshooted. The design of the circuit is highly consistent with the working principle of the aircraft system, which helps to cultivate the troubleshooting ability of maintenance personnel for aircraft standard circuits. BRIEF DESCRIPTION OF THE DRAWINGS
[0020] Figure 1 It is a structural schematic diagram of a circuit for simulating a standard line fault of an aircraft provided by an embodiment of the utility model;
[0021] Figure 2 It is a circuit diagram of a power supply control module provided by an embodiment of the utility model;
[0022] Figure 3 It is a circuit diagram of a total power control module provided by an embodiment of the utility model;
[0023] Figure 4 It is a circuit diagram of a first connector plug module and a relay module provided by an embodiment of the utility model;
[0024] Figure 5 The utility model is provided in an embodiment of a circuit diagram of a circuit for simulating a standard line fault of an aircraft. DETAILED DESCRIPTION
[0025] The following will be combined with the drawings in the embodiments of the utility model to clearly and completely describe the technical solutions in the embodiments of the utility model. Obviously, the described embodiments are only part of the embodiments of the utility model, not all of the embodiments. Based on the embodiments of the utility model, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the utility model.
[0026] In the description of the specification and claims, it is to be understood that the terms first, second, etc. in the specification and claims are only used for the purpose of describing the same technical features, and cannot be understood as indicating or implying relative importance or implicitly indicating the number of technical features indicated, nor necessarily describing the order or time sequence. The terms are interchangeable where appropriate. Therefore, a feature defined as "first" or "second" may explicitly or implicitly include at least one of the features.
[0027] In the description of this application, it should be noted that, unless otherwise clearly specified and limited, the terms "installed", "connected", and "connected" should be understood in a broad sense, for example, it can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection or an electrical connection; it can be a direct connection, or it can be indirectly connected through an intermediate medium, or it can be the internal communication of two components. For ordinary technicians in this field, the specific meanings of the above terms in this application can be understood according to specific circumstances.
[0028] See also Figure 1 , the embodiment of the utility model provides a circuit 10 for simulating a standard line fault of an aircraft, comprising a sub-power input control module 11, a main power input control module 12, a first connector plug module 13, a relay module 14, and a status display module 15;
[0029] The first end of the divided power input control module 11 is connected to the first DC power supply, and the second end of the divided power input control module 11 is connected to the first end of the relay module 14 through the first connector plug module 13; the second end of the relay module 14 is connected to the first end of the status display module 15; the first end of the main power input control module 12 is connected to the second DC power supply, and the second end of the main power input control module 12 is connected to the second input end of the status display module 15 through the first connector plug module 13.
[0030] In a specific implementation, the aircraft standard circuit can be simulated through the power input control module 11, the main power input control module 12, the first connector plug module 13, the relay module 14, and the status display module 15, and a specified fault can be generated on the circuit. The circuit is highly consistent with the working principle of the aircraft system. Through the circuit, the trainees can locate the fault of the aircraft standard circuit, which helps to improve the troubleshooting ability of the trainees.
[0031] See also Figure 2 The embodiment of the utility model provides a circuit diagram of a power supply input control module 11. The power supply input control module 11 includes a first jump switch S11 and a power supply switch S12, and the first jump switch S11 and the power supply switch S12 control the first DC power supply to be input to the relay module through the first connector plug module 12.
[0032] In a specific implementation, the training personnel can be trained on the disassembly and assembly of the first jump switch S11 through the divided power input control module 11; the designated faults can also be set for the first jump switch S11 and the divided power switch S12 respectively, so that the training personnel can determine the fault type through measurement and eliminate the fault, so that the divided power input control module 11 can resume normal operation.
[0033] See also Figure 3 The embodiment of the utility model provides a circuit diagram of a main power control module. The main power input control module 12 includes a second jump switch S21, and the second jump switch S21 controls the second DC power supply to supply power to the status display module 14 through the first connector plug module 13.
[0034] In a specific implementation, the main power input control module 12 can be used to train trainees on the disassembly and assembly of the second jump switch S21; a specified fault can also be set for the second jump switch S21, so that trainees can determine the fault type through measurement and eliminate the fault, so that the main power input control module 12 can resume normal operation.
[0035] As a preferred embodiment, the first connector plug module includes a grounding terminal block and a first connector plug, which inputs the signal of the main power control module into the first connector plug to power the status display module, and respectively inputs the signal of the sub-power control module and the grounding signal generated by the grounding terminal block into the first connector plug to control the operation of the relay module.
[0036] In a specific implementation, the training personnel can complete the disassembly and assembly of the first connector plug and the grounding terminal block, the crimping and pushing and pulling training of the corresponding pins of the first connector plug; and can also measure the fault type of the first connector plug.
[0037] As a preferred embodiment, the circuit for simulating aircraft standard line failure includes a plurality of identical number of divided power input control modules and relay modules, the first end of each of the divided power input control modules is connected to the first DC power supply, and the second end of each of the divided power input control modules is connected to the first end of a relay module.
[0038] It should be noted that the first connector plug in the first connector plug module 13 includes a plurality of pins. When the circuit includes a plurality of sub-power input control modules and relay modules of the same number, each sub-power input control module can be electrically connected to a corresponding relay module through the same first connector plug. For example, the first sub-power input control module is electrically connected to the first relay module through the pins 1 and 2 of the first connector plug, the second sub-power input control module is electrically connected to the second relay module through the pins 3 and 4 of the first connector plug, and the main power control module is electrically connected to the status display module 15 through the pin 5 of the first connector plug. Alternatively, each sub-power input control module is electrically connected to the relay module through a plurality of first connector plugs, both of which are reflected in the actual aircraft standard circuit, and the specific number and placement of the first connector plugs do not affect the beneficial effects achieved by the present invention.
[0039] As a preferred implementation, the relay module includes a relay, which receives a signal from the first connector plug module, obtains a relay state signal through the relay, and inputs the signal into the state display module.
[0040] In a specific implementation, the training personnel can complete the disassembly and measurement training of the relay; and can also measure the fault type of the relay J1.
[0041] For example, see Figure 4 , the embodiment of the utility model provides a circuit diagram of a first connector plug module 13 and a relay module 14. The first connector plug module includes a grounding wiring block and a first connector plug C1, which inputs the signal of the main power control module 12 into the pin 3 of the first connector plug C1, supplies power to the status display module 15, and inputs the signal of the sub-power control module 11 and the grounding signal generated by the grounding wiring block into the pin 2 and the pin 1 of the first connector plug C1 respectively, to control the operation of the relay module 14. The relay module includes a relay J1, which receives the signal of the first connector plug module 13, obtains the relay state signal through the relay J1 and inputs it to the status display module 15. The relay J1 includes five contacts, A1-A3, D1-D3 and X1-X2.
[0042] When the sub-power switch S2 of the sub-power control module 11 is in the OFF position, the DC sub-power reaches the contact X1 of the relay J1 through the first connector plug C1, and then reaches the contact X2 through the electromagnetic coil, and returns to the grounding point at the No. 1 pin of the first connector plug C1. Since the sub-power switch S2 is in the OFF position at this time, a closed-loop circuit cannot be formed, so the relay J1 does not work, the contact A2 is engaged with the contact A3, and the contact D2 is engaged with the contact D3.
[0043] When the sub-power switch S2 of the sub-power control module 11 is in the ON closed position, the DC sub-power reaches the contact X1 of the relay J1 through the first connector plug C1, and then reaches the contact X2 through the electromagnetic coil, and returns to the grounding point at the No. 1 pin of the first connector plug C1. Since the sub-power switch S2 is in the ON closed position at this time, a closed-loop circuit is formed, so the relay J1 works normally, the contact A2 is engaged with the contact A1, and the contact D2 is engaged with the contact D1.
[0044] As a preferred embodiment, the status display module 14 includes a second connector plug, several status lights and several buzzers, which is connected to the relay module and the main power input control module through the second connector plug, and controls the status lights and the buzzer according to the relay status signal.
[0045] For example, see Figure 5 , the utility model provides a circuit diagram of a circuit for simulating a standard line fault of an aircraft.
[0046] The first DC power supply and the second DC power supply are both 24V DC power supplies, and the circuit includes three sub-power input control modules and three relay modules. The three relay modules and the main power input control module are all electrically connected to the first connector plug module, the first sub-power input control module is electrically connected to the first relay module through pins 1 and 2 of the first connector plug C1, the second sub-power input control module is electrically connected to the second relay module through pins 3 and 4 of the first connector plug C1, the third sub-power input control module is electrically connected to the third relay module through pins 5 and 6 of the first connector plug C1, and the main power input control module is electrically connected to the pin 10 of the second connector plug C2 of the status display module through the pin 7 of the first connector plug C1. The contacts A3, A1, and D1 of the first relay J1 of the first sub-power input control module are electrically connected to the pins 1, 2, and 3 of the second connector plug C2 of the status display module, respectively; the contacts A3, A1, and D1 of the second relay J2 of the second sub-power input control module are electrically connected to the pins 4, 5, and 6 of the second connector plug C2 of the status display module, respectively; the contacts A3, A1, and D1 of the third relay J2 of the third sub-power input control module are electrically connected to the pins 7, 8, and 9 of the second connector plug C2 of the status display module, respectively; the main power input control module is electrically connected to the pin 10 of the second connector plug through the pin 7 of the first connector plug C1.
[0047] When the power supply switch S12 is in the OFF position, the DC power supply reaches the contact X1 of the relay J1 through the first connector plug C1, and then reaches the contact X2 through the electromagnetic coil. The grounding point at the No. 1 pin of the first connector plug C1 cannot form a closed-loop circuit. At this time, the status light L1 lights up, the status light L2 goes out, the buzzer FM1 does not flash and there is no buzzing sound.
[0048] When the sub-power switch S2 of the sub-power control module 11 is in the ON closed position, the DC sub-power reaches the contact X1 of the relay J1 through the first connector plug C1, and then reaches the contact X2 through the electromagnetic coil. The grounding point at the No. 1 pin of the first connector plug C1 forms a closed-loop circuit. At this time, the status light L1 is off, the status light L2 is on, and the buzzer FM1 flashes and buzzes.
[0049] In actual application, the training personnel can judge whether each module of the circuit is working normally by the on and off of the status light and the status of the buzzer. Furthermore, different colored status lights can be used to indicate the status of the power switch and relay module, for example, status lights L1, L3 and L5 are green status lights, and status lights L2, L4 and L6 are red status lights. When a fault occurs, the faulty module and fault type are determined by measurement.
[0050] The circuit for simulating aircraft standard line faults provided by the embodiment of the utility model can realize the simulation of aircraft standard lines and can generate specified faults on the lines. The circuit is highly consistent with the working principle of the aircraft system. Through the circuit, training personnel can locate faults on aircraft standard lines, which helps to improve the troubleshooting ability of training personnel.
[0051] The embodiment of the utility model further provides a training device for simulating a standard line fault of an aircraft, and the training device for simulating a standard line fault of an aircraft comprises:
[0052] The stand body;
[0053] A host computer, the host computer is mounted on the platform body to define a receiving cavity; and
[0054] The circuit for simulating a standard line fault of an aircraft as described in any one of the above items is accommodated in the accommodating cavity.
[0055] As a preferred embodiment, the host computer includes a fault signal controller, which is communicatively connected to the circuit for simulating aircraft standard line faults and responds to fault simulation instructions of the host computer to control the circuit for simulating aircraft standard line faults to generate a specified fault.
[0056] It should be noted that the fault signal controller can control the circuit used to simulate the aircraft standard line fault to produce a specified fault, and can simulate faults such as the relay, the first connector plug, the second connector plug and line-related wires, and produce fault types such as excessive wire resistance, open circuit and relay contact failure.
[0057] Preferably, the circuit for simulating aircraft standard line fault is connected to the socket of the dark box through a plug, and the dark box is electrically connected to the fault signal controller and is arranged on the platform body.
[0058] The training device for simulating aircraft standard circuit faults provided by the embodiment of the utility model can simulate the aircraft standard circuit and generate specified faults on the circuit. The circuit is highly consistent with the working principle of the aircraft system. Through the circuit, trainees can locate faults on the aircraft standard circuit, which helps to improve the troubleshooting ability of trainees.
[0059] A person skilled in the art can understand that all or part of the processes in the above-mentioned embodiments can be implemented by instructing the relevant hardware through a computer program, and the program can be stored in a computer-readable storage medium, and when the program is executed, it can include the processes of the embodiments of the above-mentioned methods. The storage medium can be a disk, an optical disk, a read-only memory (ROM) or a random access memory (RAM), etc.
[0060] The above is a preferred embodiment of the present invention. It should be pointed out that a person skilled in the art can make several improvements and modifications without departing from the principle of the present invention. These improvements and modifications are also considered to be within the protection scope of the present invention.
Claims
1. A circuit for simulating a standard line fault of an aircraft, characterized in that: It includes a sub-power input control module, a main power input control module, a first connector plug module, a relay module, and a status display module; The first end of the divided power input control module is connected to the first DC power supply, and the second end of the divided power input control module is connected to the first end of the relay module through the first connector plug module; the second end of the relay module is connected to the first end of the status display module; the first end of the main power input control module is connected to the second DC power supply, and the second end of the main power input control module is connected to the second input end of the status display module through the first connector plug module.
2. A circuit for simulating a standard line fault of an aircraft as claimed in claim 1, characterized in that: The sub-power input control module includes a first jump switch and a sub-power switch, and controls the first DC power supply to be input to the relay module through the first connector plug module through the first jump switch and the sub-power switch.
3. A circuit for simulating a standard line fault of an aircraft as claimed in claim 2, characterized in that: The main power input control module includes a second jump switch, and the second jump switch controls the second DC power supply to supply power to the status display module through the first connector plug module.
4. A circuit for simulating a standard line fault of an aircraft as claimed in claim 3, characterized in that: The first connector plug module includes a grounding terminal block and a first connector plug, which inputs the signal of the main power control module into the first connector plug to power the status display module, and inputs the signal of the sub-power control module and the grounding signal generated by the grounding terminal block into the first connector plug to control the operation of the relay module.
5. A circuit for simulating a standard line fault of an aircraft as claimed in claim 4, characterized in that: The relay module includes a relay, which receives a signal from the first connector plug module, obtains a relay state signal through the relay, and inputs the signal into the state display module.
6. A circuit for simulating a standard line fault of an aircraft as claimed in claim 5, characterized in that: The status display module includes a second connector plug, a plurality of status lights and a plurality of buzzers, and is connected to the relay module and the main power input control module through the second connector plug, and controls the status lights and the buzzer according to the relay status signal.
7. A circuit for simulating a standard line fault of an aircraft as claimed in claim 1, characterized in that: The circuit for simulating aircraft standard line faults includes a plurality of equal numbers of divided power input control modules and relay modules, wherein the first end of each divided power input control module is connected to a first DC power supply, and the second end of each divided power input control module is connected to the first end of a relay module.
8. A training device for simulating aircraft standard line faults, characterized in that: include: The stand body; A host computer, the host computer is mounted on the platform body to define a receiving cavity; and A circuit for simulating a standard line fault of an aircraft as described in any one of claims 1 to 7, wherein the circuit is accommodated in the accommodating cavity.
9. A training device for simulating aircraft standard line faults as claimed in claim 8, characterized in that: The host computer includes a fault signal controller, which is communicatively connected to the circuit for simulating standard aircraft line faults and responds to fault simulation instructions from the host computer to control the circuit for simulating standard aircraft line faults to generate a specified fault.
10. A training device for simulating aircraft standard line faults as claimed in claim 9, characterized in that: The circuit for simulating the standard line fault of an aircraft is connected to the socket of the dark box through a plug, and the dark box is electrically connected to the fault signal controller and is arranged on the platform body.