CN219105350U - Fault signal simulation device - Google Patents
Fault signal simulation device Download PDFInfo
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- CN219105350U CN219105350U CN202320160863.XU CN202320160863U CN219105350U CN 219105350 U CN219105350 U CN 219105350U CN 202320160863 U CN202320160863 U CN 202320160863U CN 219105350 U CN219105350 U CN 219105350U
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
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- Y02P—CLIMATE CHANGE MITIGATION TECHNOLOGIES IN THE PRODUCTION OR PROCESSING OF GOODS
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Abstract
The application discloses fault signal simulation device specifically includes: the device comprises a control module, at least one execution module and at least one switching module; the execution module comprises a network unit and a switch unit; the control module is in communication connection with the network unit through a preset local area network; the control module is used for providing circuit control signals for the aircraft to be tested; the execution module is used for controlling on-off of at least one line to be tested of the aircraft to be tested according to the circuit control signal so as to simulate a fault signal; the network unit is electrically connected with the input end of the switch unit; the output end of the switch unit is electrically connected with the first connecting end of the switching module; the second connecting end of the switching module is electrically connected with the circuit to be tested. The technical scheme of the application improves the reliability of the simulation test and reduces the waste of human resources.
Description
Technical Field
The application relates to the technical field of aircraft manufacturing, in particular to a fault signal simulation device.
Background
In modern transportation, air transportation is widely preferred by users because of the advantages of long travel and short time. In air transportation, the safety performance of an aircraft is the most important, so that various performances of the aircraft need to be checked and tested both in the aircraft manufacturing process and in the aircraft overhaul and maintenance process to prevent the aircraft from malfunctioning in the air or to detect the capability of the aircraft to cope with the malfunctioning.
In the ground test link, fault problems possibly existing during the flight of the aircraft are often simulated by adopting a fault simulation mode, so that the performance of the aircraft in coping with the fault problems is checked through the simulation faults. Currently, when simulating an air probe heating fault of an aircraft, related technicians generally adopt an entity switch to replace a heating controller to connect a circuit to be tested on the aircraft for simulating fault signals. However, the method is complex in connection, consumes labor, and has low reliability, and the physical switch cannot feed back the signal connection condition and is easy to cause mechanical failure.
Disclosure of Invention
The application provides a fault signal simulation device to improve the reliability of simulation test and reduce the waste of human resources.
According to an aspect of the present application, there is provided a fault signal simulation apparatus, the apparatus including: the device comprises a control module, at least one execution module and at least one switching module; the execution module comprises a network unit and a switch unit;
the control module is in communication connection with the network unit through a preset local area network;
the control module is used for providing circuit control signals for the aircraft to be tested;
the execution module is used for controlling on-off of at least one line to be tested of the aircraft to be tested according to the circuit control signal so as to simulate a fault signal;
the network unit is electrically connected with the input end of the switch unit;
the output end of the switch unit is electrically connected with the first connecting end of the switching module;
the second connecting end of the switching module is electrically connected with the circuit to be tested.
According to another aspect of the present application, the output of the switching unit includes a ground port; the output of the switch unit is electrically connected with the first connection end of the transfer module, and the switch unit comprises:
the grounding port is electrically connected with the first connecting end of the switching module;
correspondingly, the second connection end of the switching module is electrically connected with the circuit to be tested, and the switching module comprises:
the second connecting end of the switching module is electrically connected with the ground wire of the airplane to be tested.
According to a further aspect of the application, the switching unit comprises at least one electrical switch;
the electrical switch is used for being closed or opened according to the circuit control signal.
According to yet another aspect of the application, the execution module is a network relay.
According to yet another aspect of the present application, the line under test is a warming controller line of an atmospheric data probe of an aircraft under test.
According to still another aspect of the application, the control module is an upper computer.
According to yet another aspect of the application, the number of the switching modules is the same as the number of the lines to be tested.
According to yet another aspect of the present application, the patching module is a patching cable.
According to yet another aspect of the present application, the preset local area network is built by a preset router.
The technical scheme of the embodiment of the application improves the reliability of the simulation test and reduces the waste of human resources.
It should be understood that the description of this section is not intended to identify key or critical features of the embodiments of the application or to delineate the scope of the application. Other features of the present application will become apparent from the description that follows.
Drawings
In order to more clearly illustrate the technical solutions of the embodiments of the present application, the drawings that are needed in the description of the embodiments will be briefly introduced below, and it is obvious that the drawings in the following description are only some embodiments of the present application, and that other drawings may be obtained according to these drawings without inventive effort for a person skilled in the art.
FIG. 1 is a schematic diagram of a fault signal simulation apparatus provided according to an embodiment of the present application;
FIG. 2 is a schematic diagram of a fault signal simulation apparatus provided according to an embodiment of the present application;
FIG. 3 is a schematic diagram of a fault signal simulation apparatus provided according to an embodiment of the present application;
fig. 4 is a schematic diagram of a line transfer provided according to an embodiment of the present application;
fig. 5 is a schematic diagram of a monitoring interface of a control terminal according to an embodiment of the present application.
Detailed Description
In order to make the present application solution better understood by those skilled in the art, the following description will be made in detail and with reference to the accompanying drawings in the embodiments of the present application, it is apparent that the described embodiments are only some embodiments of the present application, not all embodiments. All other embodiments, which can be made by one of ordinary skill in the art based on the embodiments herein without making any inventive effort, shall fall within the scope of the present application.
It should be noted that the terms "first," "second," and the like in the description and claims of the present application and the above figures are used for distinguishing between similar objects and not necessarily for describing a particular sequential or chronological order. It is to be understood that the data so used may be interchanged where appropriate such that embodiments of the present application described herein may be implemented in sequences other than those illustrated or otherwise described herein. Furthermore, the terms "comprises," "comprising," and "having," and any variations thereof, are intended to cover a non-exclusive inclusion, such that a process, method, system, article, or apparatus that comprises a list of steps or elements is not necessarily limited to those steps or elements expressly listed but may include other steps or elements not expressly listed or inherent to such process, method, article, or apparatus.
Fig. 1 is a schematic diagram of a fault signal simulation device provided in an embodiment of the present application, where the present embodiment may be applicable to a situation where an aircraft performs a fault signal simulation in ground inspection. As shown in fig. 1, the apparatus includes: a control module 100, at least one execution module 200, and at least one switch module 300; the execution module 200 includes a network unit 210 and a switch unit 220; wherein, the liquid crystal display device comprises a liquid crystal display device,
the control module 100 is in communication connection with the network unit 210 through a preset local area network; the control module 100 is used for providing circuit control signals for the aircraft to be tested; optionally, the control module 100 may be an upper computer, and the upper computer may include, but is not limited to, a terminal device such as a computer or a mobile phone. Alternatively, the preset local area network may be constructed by a preset router;
the execution module 200 is used for controlling on-off of at least one line to be tested of the aircraft to be tested according to the circuit control signal so as to simulate a fault signal; wherein the input terminals of the network unit 210 and the switch unit 220 are electrically connected; the output end of the switch unit 220 is electrically connected with the first connection end of the switching module 300; the execution module may be associated hardware, such as a relay, etc., with a line on-off control switch.
The second connection end of the adapting module 300 is electrically connected to the circuit to be tested.
It should be noted that, the control module is connected with the execution module through a preset local area network, and performs information transmission interaction with the execution module through the preset local area network, where not only can an instruction be sent to the execution module, but also a feedback signal of the execution module, such as whether a circuit is connected or not, can be received. The switching module can be a cable for switching the physical interface, an integrated switching head and the like. In the use scenario of the embodiment of the application, the aircraft to be tested performs ground test, and in order to verify the coping capability (processing performance) of the aircraft to fault signals, technicians simulate possible faults of the aircraft by influencing the on-off of certain lines or changing original signals and the like.
Alternatively, the line to be measured may be a warming controller line of an atmospheric data probe of the aircraft to be measured.
In the prior art, related technicians use crocodile clips to clamp part of wires in the wires or other positions of a heating controller body which can trigger the change of the signals of the wires through the wires of the heating controller which are respectively connected with an atmospheric data probe on an airplane to be tested, and the on-off or grounding of the wires is controlled through a physical ship-shaped switch to simulate faults. However, since the on-board heating controllers are located at different positions, it takes a lot of manpower and time to perform the manual connection, respectively. In addition, when the simulated fault is switched, a technician is required to reconnect the circuit of each heating controller at a different position again, so that the wiring is complicated and labor is very consumed. Moreover, the physical boat-shaped switch is arranged at different places due to different positions of the heating controller, so that technicians cannot intuitively and clearly observe the simulation situation of the fault signal.
In the embodiment of the application, the switching module is connected with a circuit to be tested in the aircraft, and the switching module is connected to the heating sensors at different positions of the aircraft through the circuit to be tested. The execution module is connected with the transfer module, and comprises a switch unit, and optionally, the switch unit can comprise at least one electrical switch; the electrical switch is used for being closed or opened according to the circuit control signal. The execution module further comprises a network unit, which is used for interacting with the control module in the environment of the preset local area network so as to receive the circuit control signal of the control module and feed back the circuit control signal to the control module so as to realize the signal of the on-off or the off-off. Therefore, a technician can intuitively observe the connection state of each heating controller of the airplane through the control module, and know what kind of fault is specifically simulated.
Alternatively, the execution module 200 may be a network relay.
The execution module and the control module are interacted through a preset local area network, the control module can be a terminal with a network communication function, and is connected with the network relay through the local area network to control the on-off or grounding of the circuit. Optionally, the number of the switching modules 300 is the same as the number of the lines to be tested. That is, the control module may control multiple execution modules simultaneously, each of which has a corresponding switching module, and each switching module may correspond to a heating controller.
In particular, as shown in fig. 2, in an alternative embodiment, the output of the switching unit 220 includes a ground port; the output terminal of the switch unit 220 is electrically connected to the first connection terminal of the switching module 300, and includes: the ground port is electrically connected with the first connection end of the switching module 300;
correspondingly, the second connection end of the switching module 300 is electrically connected to the circuit to be tested, and includes: the second connection end of the adapter module 300 is electrically connected to the ground of the aircraft to be tested.
In the prior art, a related technician uses a crocodile clip to connect an external ground wire of an aircraft for grounding, but because different heating controllers are positioned at different positions on the aircraft, grounding connection wires are quite complex, operation is inconvenient, and a connection problem easily exists in a manner that the crocodile clip clamps a wire, so that grounding fails, the technician is unaware, simulation of fault signals is affected, and test failure may finally result.
Therefore, the execution module is reserved with the grounding port, and the execution module is directly connected with the ground wire inside the aircraft, so that quite a lot of wire distribution work can be saved, and the grounding circuit is stable. Optionally, the switching module 300 is a switching cable, and is connected with a line to be tested in the aircraft through the switching cable, so that the manual operation workload of technicians is reduced.
In summary, the device provided by the embodiment of the application can greatly reduce the workload of relevant technicians in the unfolding test, so that the technicians can conveniently and efficiently connect lines in an airplane. The reliability of line connection is improved by directly connecting the internal lines of the aircraft, and the connection state of the lines is determined by the interaction under the preset local area network, so that the state of a fault signal model can be effectively provided for technicians, and the guarantee is provided for the stability of the test.
On the basis of the above embodiments, the embodiment of the present application further provides a preferred embodiment, and also provides a specific embodiment for explaining the technical solution of the present application, aiming at the simulation scenario of the fault signal in the ground test of the aircraft.
As shown in fig. 3, the control terminal (i.e., the control module) communicates with a plurality of execution terminals (i.e., execution modules) through a communication network (i.e., a preset local area network), and each execution terminal is connected to an aircraft internal line of a different warming controller on the aircraft through a patch cable (wire, i.e., a patch module). The schematic illustration of the specific execution terminal and the transit cable is shown in fig. 4, and it should be noted that the several switches (S1-S6) and the several connection ports (Pin 1-Pin 6) shown in fig. 4 are only used as illustrations, and should not be construed as limiting the embodiments of the present application.
Before the device provided by the application is used, the preset router is electrified and started, and the wireless local area network is built. One end of the terminal execution module switching cable is connected with a corresponding wire harness on the airplane, the other end of the terminal execution module switching cable is connected with the corresponding terminal execution module, the terminal execution module is started, the terminal execution module is automatically connected into the wireless local area network within a preset time, and the connection indicator lamp is lighted. The control terminal is started and runs control software, the communication condition of all terminal execution modules is detected through a button refreshing connection/reset switch of a monitoring area (shown in figure 5) of the execution terminal, a state indicator lamp turns green after the detection is passed, all control switches are initialized to be in a closed state, all grounding circuits controlled by the control switches are in an on state, the grounding state in a heating fault signal is simulated, the on-off state switching of the corresponding grounding circuits is realized by changing the control switch state through an execution terminal state setting area, and all switching state switching operations and operation execution results are recorded in a control log and displayed in real time.
In a special case, after the button of the monitoring area of the execution terminal is clicked to refresh the connection/reset switch, the communication between the upper computer and the execution terminal cannot be established within a specified time, the status indicator light remains gray, and the control log displays the related information of the execution terminal that the technician cannot establish the connection.
In another special case, the state of the control switch is changed in the state setting area of the execution terminal, the execution terminal does not feed back the execution result or fails in feedback within a specified time, the control switch of the state setting area of the execution terminal automatically rebounds to the state before being changed, the corresponding indicator light in the monitoring area of the execution terminal turns red, and detailed information of the execution failure of technicians is displayed in the control log.
The embodiment of the application provides a method for solving the problems that a heating fault signal simulation device is unreliable in grounding and inconvenient in switching operation of a switch state in the ground simulation test process of the heating fault state of the probe of the atmospheric data system; the aircraft heating fault signal simulation device is lighter, the installation test time of equipment is shortened, manual operation is saved, and the waste of human resources is avoided; real-time monitoring and recording of the control switch state also provides a guarantee for the effectiveness of the ground test; the wireless and intelligent simulation of the heating fault signal of the air data probe of the airplane provides technical support for the automatic test of the ground function test on site from the wireless controllable angle, and meanwhile, the test efficiency is improved.
The above embodiments do not limit the scope of the application. It will be apparent to those skilled in the art that various modifications, combinations, sub-combinations and alternatives are possible, depending on design requirements and other factors. Any modifications, equivalent substitutions and improvements made within the spirit and principles of the present application are intended to be included within the scope of the present application.
Claims (9)
1. A fault signal simulation apparatus, the apparatus comprising: the device comprises a control module, at least one execution module and at least one switching module; the execution module comprises a network unit and a switch unit;
the control module is in communication connection with the network unit through a preset local area network;
the control module is used for providing circuit control signals for the aircraft to be tested;
the execution module is used for controlling on-off of at least one circuit to be tested of the aircraft to be tested according to the circuit control signal so as to simulate a fault signal;
the network unit is electrically connected with the input end of the switch unit;
the output end of the switch unit is electrically connected with the first connecting end of the switching module;
the second connecting end of the switching module is electrically connected with the circuit to be tested.
2. The apparatus of claim 1, wherein the output of the switching unit comprises a ground port; the output end of the switch unit is electrically connected with the first connection end of the transfer module, and the switch unit comprises:
the grounding port is electrically connected with the first connecting end of the switching module;
correspondingly, the second connection end of the switching module is electrically connected with the circuit to be tested, and the switching module comprises:
and the second connecting end of the switching module is electrically connected with the ground wire of the airplane to be tested.
3. The device according to claim 2, wherein the switching unit comprises at least one electrical switch;
the electrical switch is used for being closed or opened according to the circuit control signal.
4. The apparatus of claim 1, wherein the execution module is a network relay.
5. The apparatus of claim 1, wherein the line under test is a warming controller line of an atmospheric data probe of the aircraft under test.
6. The apparatus of claim 1, wherein the control module is an upper computer.
7. The apparatus of claim 1, wherein the number of switch modules is the same as the number of lines to be tested.
8. The apparatus of claim 1, wherein the patching module is a patching cable.
9. The apparatus of claim 1, wherein the predetermined local area network is constructed by a predetermined router.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202320160863.XU CN219105350U (en) | 2023-01-18 | 2023-01-18 | Fault signal simulation device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202320160863.XU CN219105350U (en) | 2023-01-18 | 2023-01-18 | Fault signal simulation device |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN219105350U true CN219105350U (en) | 2023-05-30 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN202320160863.XU Active CN219105350U (en) | 2023-01-18 | 2023-01-18 | Fault signal simulation device |
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| CN (1) | CN219105350U (en) |
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- 2023-01-18 CN CN202320160863.XU patent/CN219105350U/en active Active
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