CN210534766U - Test equipment of flight control and management computer - Google Patents
Test equipment of flight control and management computer Download PDFInfo
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- CN210534766U CN210534766U CN201921153924.XU CN201921153924U CN210534766U CN 210534766 U CN210534766 U CN 210534766U CN 201921153924 U CN201921153924 U CN 201921153924U CN 210534766 U CN210534766 U CN 210534766U
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Abstract
The utility model discloses a test equipment of flight control and management computer, include: a power test component; the power test assembly comprises a first aviation plug and a power instrument group; the first aerial plug is externally connected with the aerial plug of the electric interface to be tested of the flight control and management computer, and the first aerial plug is matched with the aerial plug of the electric interface to be tested; each power line to be tested of the electrical interface to be tested of the flight control and management computer is respectively connected with a group of insertion cores in the aerial plug of the electrical interface to be tested, and each group of insertion cores of the aerial plug of the electrical interface to be tested is respectively connected with a group of insertion cores of the first aerial plug; the electric power instrument group is connected with each group of inserting cores of the first aerial plug through wires. The utility model discloses the test equipment of a flight control and management computer of implementing can improve the efficiency of software testing to flight control and management computer.
Description
Technical Field
The utility model relates to an aeronautical technical field especially relates to a flight control and management computer's test equipment.
Background
The flight control and management computer is the core part of unmanned aerial vehicle, plays the decisive role to unmanned aerial vehicle's performance and safety, consequently, just seems to be very important to the test of flight control and management computer. Among these, testing of the electrical interface to the flight control and management computer is an important test item.
Because the number of the power lines corresponding to the electrical interface is large, when the electrical interface of the flight control and management computer is tested, one-time electrical parameter detection needs to be performed on each power line in turn. In addition, when testing the voltage or current of the power line, the power meter must be able to contact the conductor inside the closed cable to measure the voltage or current, so the test cable needs to be made by the user, and the test points which can conduct electricity on the test cable are tested one by using the power meter, so that the test of the electrical interface of the flight control and management computer is realized. Obviously, the testing efficiency of the testing mode is low.
Therefore, a testing device for a flight control and management computer is urgently needed to improve the testing efficiency of the flight control and management computer.
SUMMERY OF THE UTILITY MODEL
An object of the embodiment of the utility model is to provide a test equipment of flight control and management computer to improve the efficiency of software testing to flight control and management computer. The specific technical scheme is as follows:
a flight control and management computer test apparatus comprising: a power test assembly, the power test assembly comprising: a first avionics and power instrument cluster;
the first aerial plug is externally connected with the aerial plug of the electric interface to be tested of the flight control and management computer, and the first aerial plug is matched with the aerial plug of the electric interface to be tested; each power line to be tested of the electrical interface to be tested of the flight control and management computer is respectively connected with a group of insertion cores in the aerial plug of the electrical interface to be tested, and each group of insertion cores of the aerial plug of the electrical interface to be tested is respectively connected with a group of insertion cores of the first aerial plug; the electric power instrument group is connected with each group of inserting cores of the first aerial plug through wires.
Optionally, the test apparatus further comprises: a communication test assembly comprising a second aerial receptacle and a first communication interface connector;
the second aerial plug is externally connected with the aerial plug of the communication interface to be tested of the flight control and management computer, and the second aerial plug is matched with the aerial plug of the communication interface to be tested; each communication line to be tested of the communication interface to be tested of the flight control and management computer is respectively connected with a group of insertion cores of the aerial plug of the communication interface to be tested, and each group of insertion cores of the aerial plug of the communication interface to be tested is respectively connected with a group of insertion cores of the second aerial plug;
the first communication interface connector is connected with a first preset plug core group in the second aviation plug through a lead and is externally connected with a test computer through a first cable; the first preset plug core group comprises at least one group of plug cores corresponding to at least one to-be-tested communication line of the to-be-tested communication interface, and the first cable is a cable matched with the first communication interface connector.
Optionally, the communication test assembly further includes: a second communication interface connector;
the second communication interface connector is connected with a second preset plug core group in the second aviation plug through a lead and is externally connected with a preset sensor through a second cable; the second preset plug core group comprises at least one group of plug cores corresponding to at least one to-be-tested communication line of the to-be-tested communication interface, and the second cable is a cable matched with the second communication interface connector.
Optionally, the power test assembly further comprises: a third air inserting;
the third aviation plug is connected with the electric power instrument set through a wire and is externally connected with a simulation load through a third cable matched with the third aviation plug;
wherein the analog load is: and simulating an adjustable load of the flight control and management computer.
Optionally, the test apparatus further comprises: the test computer.
Optionally, the test apparatus further comprises: the predetermined sensor.
Optionally, the power test assembly further comprises: the analog load.
Optionally, the test apparatus further comprises: a fourth air navigation plug and a fifth air navigation plug;
the fourth aviation plug is connected with the electric power instrument set through a wire and is externally connected with the aviation plug of a power supply input interface of the flight control and management computer; the fourth aerial plug is matched with the aerial plug of the power input interface;
and the fifth navigation plug is connected with the fourth navigation plug through a wire and is externally connected with a direct current power supply.
Optionally, the test apparatus further comprises: a voltage converter;
and the voltage input end of the voltage converter is externally connected with an alternating current power supply through a wire, and the voltage output end of the voltage converter is connected with the fourth aviation plug through a wire.
Optionally, the test apparatus further comprises: a plurality of test switches;
each test switch uniquely corresponds to one target insertion core and is connected with the target insertion core in series through a lead; the target insertion core is as follows: one ferrule in the first aerial, one ferrule in the second aerial, or one ferrule in the fourth aerial.
The embodiment of the utility model provides a pair of in flight control and management computer's test equipment, first aviation plug each group lock pin that includes corresponds each electric power circuit that awaits measuring of flight control and management computer, and electric power instrument group links to each other with first all families lock pins of inserting. When the test about the electrical interface is executed to flight control and management computer, only need to dock the electrical interface that awaits measuring of flight control and management computer and the first aviation plug of electric power test subassembly, electric power test subassembly's electric power instrument group can detect each electric power circuit that the electrical interface that awaits measuring includes simultaneously, and need not specially self-control test cable. Therefore, the embodiment of the utility model provides a pair of flight control and management computer's test equipment can show the improvement to flight control and management computer's efficiency of software testing. Of course, it is not necessary for any product or method of the invention to achieve all of the above-described advantages at the same time.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings used in the description of the embodiments or the prior art will be briefly described below, it is obvious that the drawings in the following description are only some embodiments of the present invention, and for those skilled in the art, other drawings can be obtained according to these drawings without creative efforts.
Fig. 1 is a schematic structural diagram of a test device of a flight control and management computer according to an embodiment of the present invention;
fig. 2 is another schematic structural diagram of a testing apparatus of a flight control and management computer according to an embodiment of the present invention;
fig. 3 is another schematic structural diagram of a testing apparatus of a flight control and management computer according to an embodiment of the present invention;
fig. 4 is another schematic structural diagram of a testing apparatus of a flight control and management computer according to an embodiment of the present invention;
fig. 5 is a schematic diagram of a closed loop formed by the analog load, the first aviation plug, the power meter, and the electrical interface to be tested of the flight control and management computer in the testing apparatus of the flight control and management computer according to the embodiment of the present invention;
fig. 6 is another schematic structural diagram of a testing apparatus of a flight control and management computer according to an embodiment of the present invention;
fig. 7 is another schematic structural diagram of a testing apparatus of a flight control and management computer according to an embodiment of the present invention;
fig. 8(a) is a schematic front view of a physical device of a testing device of a flight control and management computer according to an embodiment of the present invention, fig. 8(b) is a schematic back view of the physical device shown in fig. 8(a), and fig. 8(c) is a schematic side view of the physical device shown in fig. 8 (a).
Detailed Description
The technical solutions in the embodiments of the present invention will be described clearly and completely with reference to the accompanying drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only some embodiments of the present invention, not all embodiments. Based on the embodiments in the present invention, all other embodiments obtained by a person skilled in the art without creative work belong to the protection scope of the present invention.
In order to improve the efficiency of software testing to flight control and management computer, the embodiment of the utility model provides a flight control and management computer's test equipment is provided. For convenience of description, the test equipment of the flight control and management computer is hereinafter referred to simply as test equipment.
As shown in fig. 1, a test apparatus 10 of a flight control and management computer provided by an embodiment of the present invention includes a power test assembly 110, where the power test assembly 110 includes a first aviation plug 1102 and a power meter group 1101.
The first aviation plug 1102 is externally connected with an aviation plug of an electrical interface to be tested of a flight control and management computer, and the first aviation plug is matched with the aviation plug of the electrical interface to be tested; each power line to be tested of the electrical interface to be tested of the flight control and management computer is respectively connected with a group of insertion cores in the aerial plug of the electrical interface to be tested, and each group of insertion cores of the aerial plug of the electrical interface to be tested is respectively connected with a group of insertion cores of the first aerial plug;
the power meter cluster 1101 is connected to each cluster insert of the first navigation plug 1102 by a wire.
The embodiment of the utility model provides an in, first aviation plug 1102 specifically is aviation plug or aviation socket, depends on first aviation plug to be used by the external electrical interface that awaits measuring of institute. When the aviation plug used by the electrical interface to be tested externally connected with the first aviation plug 1102 is the aviation plug, the first aviation plug 1102 is the aviation socket matched with the aviation plug; when the aviation plug used by the electrical interface to be tested externally connected to the first aviation plug 1102 is an aviation socket, the first aviation plug 1102 is an aviation plug matched with the aviation socket.
It is understood that the power meter group 1101 may include a plurality of power meters, and each power line to be tested of the electrical interface to be tested of the flight control and management computer may correspond to one or more power meters in the power meter group 1101, so that the power meters can detect the power line to be tested. Correspondingly, each group of the inserting cores in the first aviation plug can correspond to the electric meters and is connected with the electric meters through wires.
In addition, the specific meter types included in the respective electric meters in the electric meter group 1101 may be the same or different. In practical applications, the types of the power meters described above may include: voltmeter, ammeter, wattmeter, multimeter and the like. It should be noted that the types of the power meters shown here are merely examples, and should not be construed as limiting the embodiments of the present invention.
In addition, because the electric power instrument of different grade type is examining the electric power circuit that awaits measuring, can be different with the concrete connected mode of the electric power circuit that awaits measuring, for example, some electric power instruments need establish ties with the electric power circuit that awaits measuring, some electric power instruments need with the electric power circuit that awaits measuring parallelly connected etc. consequently, the embodiment of the utility model provides a to electric power instrument group 1101 and the concrete connected mode of each group's lock pin of first aviation plug 1102, do not further concrete the injecing.
It will be appreciated that the test device also includes a housing. To facilitate connecting the electrical interface under test of the flight control and management computer to the first aerial pod 1102, the first aerial pod 1102 may be disposed on an exterior surface of the housing of the test device. Of course, it is not limited thereto.
It is understood that the electrical interface under test of the flight control and management computer may include a plurality of electrical test assemblies 110, and therefore, the test equipment may include a plurality of electrical test assemblies 110, each electrical test assembly 110 corresponding to one electrical interface under test of the flight control and management computer. Alternatively, the first aviation plug 1102 included in the power test assembly may be multiple, and each first aviation plug 1102 is correspondingly connected with one electrical interface to be tested of the test flight control and management computer.
It should be noted that the number of the power testing assemblies 110 included in the testing device 10 shown in fig. 1 and the number of the first inserts 1102 included in the power testing assemblies 110 are only examples, and should not be construed as limiting the embodiments of the present invention.
In the test equipment of the flight control and management computer provided by the embodiment of the utility model, a first aerial plug is externally connected with the aerial plug of the electrical interface to be tested of the flight control and management computer, and the first aerial plug is matched with the aerial plug of the electrical interface to be tested; each power line to be tested of the electrical interface to be tested of the flight control and management computer is respectively connected with a group of insertion cores in the aerial plug of the electrical interface to be tested, and each group of insertion cores of the aerial plug of the electrical interface to be tested is respectively connected with a group of insertion cores of the first aerial plug. Like this, when carrying out the test about the electrical interface to flight control and management computer, only need to dock the electrical interface that awaits measuring of flight control and management computer and electric test assembly's first aviation plug, electric test assembly's electric power instrument group can detect each electric power circuit that the electrical interface that awaits measuring includes simultaneously, and need not specially self-control test cable. Therefore, the embodiment of the utility model provides a pair of flight control and management computer's test equipment can show the improvement to flight control and management computer's efficiency of software testing.
In order to test the variety, the embodiment of the utility model provides a test equipment of flight control and management computer can also include on the basis that contains electric power test component: a communication test assembly comprising a second aerial receptacle and a first communication interface connector;
the second aerial plug is externally connected with the aerial plug of the communication interface to be tested of the flight control and management computer, and the second aerial plug is matched with the aerial plug of the communication interface to be tested; each communication line to be tested of the communication interface to be tested of the flight control and management computer is respectively connected with a group of insertion cores of the aerial plug of the communication interface to be tested, and each group of insertion cores of the aerial plug of the communication interface to be tested is respectively connected with a group of insertion cores of the second aerial plug;
the first communication interface connector is connected with a first preset plug core group in the second aviation plug through a lead and is externally connected with a test computer through a first cable; the first preset plug core group comprises at least one group of plug cores corresponding to at least one to-be-tested communication line of the to-be-tested communication interface, and the first cable is a cable matched with the first communication interface connector.
A schematic diagram of a test apparatus comprising a communication test assembly is shown in fig. 2. As shown in fig. 2, with respect to the testing device shown in fig. 1, the testing device 10 provided in the embodiment of the present invention may further include a communication testing component 120, where the communication testing component 120 includes a second air socket 1202 and a first communication interface connector 1201.
Here, as to whether the second aviation plug 1202 is an aviation plug or an aviation socket, reference may be made to a specific setting manner of the first aviation plug, and details thereof are not described herein.
It is understood that the first communication interface connector 1201 may include one or more. When the first communication interface connector 1201 includes one, the first predetermined plug core group may be a group of plug cores corresponding to one communication line to be tested of the communication interface to be tested; when the first communication interface connector 1201 includes a plurality of connectors, the first predetermined ferrule group may also include a plurality of groups, each group corresponding to one communication line to be tested of the communication interface to be tested.
In the prior art, since the communication interface to be tested of the flight control and management computer includes a plurality of communication lines to be tested, during testing, a test cable needs to be manufactured for each communication line to be tested, and then connection between the flight control and management computer and the test computer or other auxiliary test equipment is realized through the test cable. Because the number of the communication lines to be tested is large, and each communication line to be tested comprises more than one lead. Therefore, errors are easy to occur when the test cable is manufactured.
The embodiment of the utility model provides an in, direct air-to-air plug with the communication interface that awaits measuring of flight control and management computer is connected with second air-to-air plug 1202, and second air-to-air plug 1202 links to each other with first communication interface connector 1201. Since the first communication interface connectors 1201 are all general communication connectors for computers, the connection between the test device and the test computer can be realized through the first cables matched with the first communication interface connectors 1201, and further, the communication connection between the flight control and management computer and the test computer is realized. At the moment, the control and test of the flight control and management computer can be realized by utilizing an external test computer. Obviously, the embodiment of the utility model provides a test equipment is difficult to the mistake that appears on the line, also need not to make the test cable, further promotion to flight control and management computer's efficiency of software testing.
It will be appreciated that the second pod 1202 may be disposed on an exterior surface of the test device housing for ease of interfacing the test device with the flight control and management computer. Similarly, to facilitate connection of the test computer to the first communication interface connector 1201, the first communication interface connector 1201 may be provided on an outer surface of the housing of the test device. Of course, it is not limited thereto. For example, in another embodiment, the testing device provided in the present invention may further include the testing computer, and at this time, the testing computer belongs to a component of the testing device provided in the embodiment of the present invention, so that the second navigation plug 1202 and/or the first communication interface connector 1201 may also be disposed inside the testing device.
In addition, in order to be compatible with a plurality of connection modes, in the embodiment of the present invention, when the communication test assembly includes a plurality of first communication interface connectors 1201, the type of the first communication interface connectors 1201 may include a plurality of types. For example, the kinds of the first communication interface connector 1201 may include a DB9 connector, a DB25 connector, and the like. Here, DB9 and DB25 are both common communication interface connectors. Of course, the plurality of first communication interface connectors 1201 may also be the same type of connector, for example, the plurality of first communication interface connectors 1201 may each be a DB9 connector or a DB25 connector. It should be noted that the type of the first communication interface connector shown here is only an example, and should not be construed as limiting the embodiments of the present invention.
It can be understood that the communication interface to be tested of the flight control and management computer can include a plurality of, therefore, in the embodiment of the present invention, the communication testing component 120 included in the testing device can also include a plurality of, and each communication testing component 120 corresponds to one communication interface to be tested of the flight control and management computer. Alternatively, the number of the second navigation plug included in the communication testing component 120 may be multiple, and each second navigation plug 1202 is correspondingly connected to one to-be-tested communication interface of the testing flight control and management computer.
It should be noted that the number of communication test assemblies 120 included in the test device 10 of the flight control and management computer shown in fig. 2 and the number of first communication interface connectors 1201 included in each communication test assembly 120 are only examples, and should not be construed as limiting the embodiments of the present invention.
Based on above-mentioned embodiment can see, utilize the utility model discloses flight control and management computer's test equipment that the embodiment provided can also realize the test to the communication aspect of flight control and management computer.
In order to test the variety, the embodiment of the utility model provides an in flight control and management computer's the test equipment communication test assembly can also include: a second communication interface connector;
the second communication interface connector is connected with a second preset plug core group in the second aviation plug through a lead and is externally connected with a preset sensor through a second cable; the second preset plug core group comprises at least one group of plug cores corresponding to at least one communication line to be tested of the aerial plug of the communication interface to be tested, and the second cable is a cable matched with the second communication interface connector.
See fig. 3 for a schematic diagram of a test device comprising a second communication interface connector. As shown in fig. 3, with respect to the testing device shown in fig. 2, in the testing device 10 provided in the embodiment of the present invention, each communication testing component 120 may further include a second communication interface connector 1203; the second communication interface connector 1203 is connected to a second predetermined plug core set in the second navigation plug 1202 through a wire, and is externally connected to a predetermined sensor through a second cable, the second predetermined plug core set includes at least one set of plug cores corresponding to at least one to-be-tested communication line of the to-be-tested communication interface, and the second cable is a cable matched with the second communication interface connector 1203.
Here, the predetermined sensor may be a sensor connectable to the flight control and management computer.
It is understood that the second communication interface connectors 1203 may include one or more, and each second communication interface connector 1203 may be connected to a predetermined sensor. When the second communication interface connector 1203 includes one, the second predetermined plug core group may be a group of plug cores corresponding to one to-be-tested communication line of the to-be-tested communication interface; when the second communication interface connector 1203 includes a plurality of connectors, the second predetermined ferrule group may also include a plurality of groups, each group corresponding to at least one communication line to be tested of the communication interface to be tested.
It will be appreciated that, since there may be a plurality of types of sensors of the flight control and management computer, the type of the second communication interface connector 1203 included in the communication testing assembly 120 may also include a plurality of types in order to better simulate the operation of the flight control and management computer when the various sensors are connected thereto. Of course, when the plurality of predetermined sensors support the same communication interface, each of the second communication interface connectors 1203 included in the communication testing assembly 120 may also be the same.
In practical applications, the communication link with the predetermined sensor also belongs to the communication link of the flight control and management computer. Therefore, when the second navigation plug 1202 is docked with the navigation plug used by the communication interface to be tested and the second communication interface connector 1203 is connected with the predetermined sensor, the communication connection between the predetermined sensor and the flight control and management computer can be realized. At this time, the predetermined sensor may report the sensing data to the flight control and management computer through the test device, and the test computer in the test device may also read the data uploaded by the sensor from the flight control and management computer through communication with the flight control and management computer.
It will be appreciated that the second communication interface connector 1203 may be disposed on an exterior surface of the housing of the test device for the convenience of connecting the predetermined sensor to the second communication interface connector. Of course, it is not limited thereto. For example, in another embodiment, the testing device provided by the embodiment of the present invention may further include the predetermined sensor described above. At this time, these sensors belong to the components in the testing device provided by the embodiment of the present invention, so the second communication interface connector 1203 may be disposed inside the testing device.
It should be noted that the number of the second communication interface connectors 1203 included in the communication testing assembly 120 shown in fig. 3 is only an example, and should not be construed as a limitation to the embodiment of the present invention.
Based on above-mentioned embodiment can be seen, the embodiment of the utility model provides a test equipment can also carry out the simulation test to the application scene of flight control and management computer connection sensor.
On the basis of the test equipment of a flight control and management computer taking any one of the figures 1-3 as a structural example, the embodiment of the invention also provides the test equipment of the flight control and management computer. Specifically, the power test assembly in the test device may further include: a third air inserting; the third aviation plug is connected with the electric power instrument set through a wire and is externally connected with a simulation load through a third cable matched with the third aviation plug; wherein the analog load is: and simulating an adjustable load of the flight control and management computer.
See figure 4 for a schematic of a test apparatus comprising a third aerial pod. As shown in fig. 4, compared to the testing device shown in fig. 3, in the testing device 10 provided in the embodiment of the present invention, the power testing component 110 may further include a third aviation plug 1103; the third navigation plug 1103 is connected to the power instrument cluster 1101 through a wire, and is externally connected to an analog load through a third cable matched with the third navigation plug 1103. The simulation load is: and simulating an adjustable load of the flight control and management computer.
As to whether the third aviation plug 1103 is an aviation plug or an aviation socket, reference may be made to a specific setting manner of the first aviation plug, which is not described herein again.
It will be appreciated that the dummy load is connected to the power meter cluster 1101 through the third pod 1103, the power meter cluster 1101 being connected to the first pod, the first pod being connected to the flight control and management computer, and therefore the dummy load being in communication with the flight control and management computer.
In practical applications, a to-be-tested electrical interface of the analog load, the first aviation plug and the flight control and management computer may form a closed loop, and the power meters in the power meter group 1101 are connected to the closed loop, so that the power parameters and the operating state of the flight control and management computer in various loading states may be tested. For example, as shown in fig. 5, when the power meter assembly 1101 includes an ammeter and a voltmeter, the ammeter is connected in series in the closed loop, and the voltmeter is connected in parallel with the analog load and the electrical interface to be tested, respectively, in fig. 5, a circle containing a letter a represents the ammeter, and a circle containing a letter V represents the voltmeter. Since the ferrules of the first and third aerial sockets 1102 and 1103 are both conductors, the voltage tested by the voltmeter is the voltage of the electrical interface to be tested of the flight control and management computer, and the current tested by the ammeter is the current in the closed loop, i.e. the output current of the electrical interface to be tested of the flight control and management computer.
In practical applications, each power line to be tested of the flight control and management computer may need a corresponding analog load. Thus, the above-mentioned dummy load may be a dummy load vehicle, which may include a plurality of dummy loads.
Correspondingly, in the testing device provided by the embodiment of the present invention, the third aviation plug 1103 may include a plurality of groups of ferrules, each group of ferrules is connected to a group of power meters in the power meter group 1101, the group of power meters is connected to a group of ferrules in the first aviation plug 1102, and the group of ferrules in the first aviation plug 1102 corresponds to a power line to be tested of the flight control and management computer; the set of jack cores in the third aviation plug 1103 is externally connected with a road simulation load of the load vehicle. Thus, the power line to be tested of the flight control and management computer forms a loop with the first aviation plug 1102, the set of power meters, the third aviation plug 1103 and a simulation load.
In addition, to conveniently connect the analog load to the third navigation plug 1103, the third navigation plug 1103 may be disposed on an outer surface of the housing of the test device. Of course, it is not limited thereto. For example, in another embodiment, the test equipment provided by the embodiment of the present invention may further include the above-mentioned dummy load. At this moment, the analog load belongs to a component of the testing device provided by the embodiment of the present invention, so the third aviation plug 1103 can also be disposed inside the testing device.
It should be noted that the number of the third inserts 1103 included in the power testing assembly 110 shown in fig. 4 is only an example, and should not be construed as a limitation to the embodiments of the present invention.
Based on above-mentioned embodiment can be seen, the embodiment of the utility model provides a test equipment can also realize the simulation test under the different tape load circumstances to flight control and management computer.
On the basis of the test equipment of a flight control and management computer taking any one of the figures 1-4 as a structural example, the embodiment of the invention also provides the test equipment of the flight control and management computer. Specifically, the test device may further include: a fourth air navigation plug and a fifth air navigation plug;
the fourth aviation plug is connected with the electric power instrument group through a wire and is externally connected with the aviation plug of a power supply input interface of a flight control and management computer; the fourth aviation plug is matched with the aviation plug of the power input interface;
the fifth aviation plug is connected with the fourth aviation plug through a wire and is externally connected with a direct current power supply.
See figure 6 for a schematic of a test apparatus comprising a fourth and fifth navigation plug. As shown in fig. 6, compared with the testing apparatus shown in fig. 4, the testing apparatus 10 provided in the embodiment of the present invention may further include: a fourth pod 130 and a fifth pod 140; the fourth aviation plug 130 is connected with the 1101 group of electric power instruments through a wire and is externally connected with the aviation plug of a power supply input interface of a flight control and management computer; the fourth aviation plug 130 is matched with the aviation plug of the power input interface; the fifth navigation plug 140 is connected to the fourth navigation plug 130 via a wire and is externally connected to a dc power supply.
The fourth aviation plug 130 is connected to the power meter cluster through a wire, and specifically may be connected to a group of power meters in the power meter cluster 1101. The direct current power supply is provided with the aviation plug matched with the fifth aviation plug. When the fifth aviation plug is externally connected with the aviation plug of the direct current power supply and the electricity of the direct current power supply is sent to the power supply input interface of the flight control and management computer through the fourth aviation plug, the group of power meters can detect the power supply input interface of the flight control and management computer. The dc power supply may specifically include a dc battery or a dc power supply device.
It is understood that the dc power supply in this embodiment is used to supply power to the flight control and management computer, so the voltage of the dc power supply in this embodiment can be configured as the input voltage of the flight control and management computer. In a specific application, the input voltage of the flight control and management computer may be a dc voltage. For example, a DC voltage of 24-28V.
Based on above-mentioned embodiment can see, via the utility model discloses the test equipment that provides can bring following beneficial effect for flight control and management computer power supply: the detection of the power supply input port of the flight control and management computer is realized by utilizing the power meter group of the testing equipment.
On the basis of the test equipment taking the structure as an example in fig. 6, the embodiment of the present invention further provides a test equipment of a flight control and management computer. For the test equipment that fig. 6 shows, the test equipment that the embodiment of the utility model provides can also include: a voltage converter; the voltage input end of the voltage converter is externally connected with an alternating current power supply through a wire, and the voltage output end of the voltage converter is connected with the fourth aviation plug through a wire.
See fig. 7 for a schematic diagram of a test apparatus comprising a voltage converter. As shown in fig. 7, compared to the testing apparatus shown in fig. 6, the testing apparatus 10 provided in the embodiment of the present invention may further include: and a voltage converter 150, wherein a voltage input end of the voltage converter 150 is externally connected with an alternating current power supply through a wire, and a voltage output end of the voltage converter 150 is connected with the fourth aviation plug 130 through a wire.
The alternating current power supply can comprise an alternating current power supply socket of 110V-220V. Therefore, the voltage converter 150 can convert the 110V-220V AC voltage into the input voltage of the flight control and management computer, and send the input voltage to the power input port of the flight control and management computer through the fourth aviation plug 130.
In this embodiment, the flight control and management computer may be powered by the voltage converter 150 after the ac voltage of the ac power supply is converted into the dc voltage and then the fourth aviation plug 130, or may be powered by the fifth aviation plug directly connected to the dc voltage of the dc power supply and then the fourth aviation plug 130. In practical application, one power supply mode can be selected from the two power supply modes to supply power for the flight control and management computer, and the other power supply mode is not connected with an external power supply. For example, when the flight control and management computer is powered by the voltage converter 150 connected to the external ac power supply, the fifth pod 140 may be in a suspended open state, so that even though the fifth pod is connected to the fourth pod, the power input port of the flight control and management computer, the fourth pod and the fifth pod cannot form a power-on loop because the fifth pod is in an open state.
In addition, the embodiment of the present invention provides a power meter and a predetermined sensor in a power meter group, which can have a built-in battery respectively, and the battery can provide a basic operating voltage for the power meter group and the predetermined sensor. Of course, some types of power meter and sensor do not need the power supply, and when the embodiment of the utility model discloses adopt this type of power meter or sensor, power meter or sensor and the equipment that awaits measuring communicate, treat that power meter and sensor just can work. The embodiment of the utility model provides an analog load, both can be passive analog load, also can be active analog load. When the analog load is an active analog load, the working voltage of the analog load can be provided by the alternating current power supply. Similarly, the working voltage of the testing computer in the embodiment of the present invention can also be provided by the ac power supply. It should be noted that the specific power supply mode of each component assembly shown herein is only an example, and should not be construed as limiting the present invention.
On the basis of the test equipment taking the structure of fig. 7 as an example, the embodiment of the invention also provides the test equipment of the flight control and management computer. With respect to the testing device shown in fig. 7, the testing device provided by the embodiment of the present invention may further include a plurality of testing switches. Each test switch uniquely corresponds to one target insertion core and is connected with the target insertion core in series through a lead; the target insertion core is as follows: one ferrule in the first aerial, one ferrule in the second aerial, or one ferrule in the fourth aerial.
In this embodiment, the total number of the plurality of test switches may be less than or equal to: the sum of the number of all first aerial ferrules, the number of all second aerial ferrules, and the number of all fourth aerial ferrules. That is, each ferrule directly connected to the flight control and management computer in the test equipment may be used as a target ferrule to correspond to one test switch, or a part of the ferrules directly connected to the flight control and management computer in the test equipment may be used as target ferrules, and the target ferrules may respectively correspond to one test switch.
In practical application, the open circuit of any one wire in the flight control and management computer can cause different faults. Therefore, by utilizing the test switch, the fault phenomenon when each wire in the flight control and management computer is broken can be simulated, and the fault phenomenon when a plurality of wires are simultaneously broken can also be simulated, so that the simulation test of the fault scene of the flight control and management computer is realized.
Based on above-mentioned embodiment can see, the embodiment of the utility model provides a test equipment can also simulate various faults that flight control and management computer lead wire open circuit arouse.
The following describes, by way of example, a position and a manner of setting components in a test device of a flight control and management computer according to an embodiment of the present invention. Fig. 8(a) is a schematic front view of a physical device of a testing device of a flight control and management computer according to an embodiment of the present invention, fig. 8(b) is a schematic back view of the physical device shown in fig. 8(a), and fig. 8(c) is a schematic side view of the physical device shown in fig. 8 (a).
In practical applications, in order to facilitate the simultaneous viewing of a plurality of power meters, all the power meters included in the test equipment may be collectively disposed on the panel of the test equipment as shown in fig. 8 (a). In order to facilitate the on-off operation of a plurality of test switches simultaneously when simulating the wire break test of the flight control and management computer, all the test switches included in the test equipment may be collectively disposed in one switch box as shown in fig. 8 (a). To facilitate the differentiation between different types of outlets, outlets or communication interface connectors that serve the same purpose may be provided on the same area of the surface of the test device as shown in fig. 8(a), 8(b) and 8 (c). For example, each of the terminal pins connected to the flight control and management computer may be located on the same area of the housing surface. In the interior of the test equipment, some storage spaces for placing the test computer, the predetermined sensor and the analog load may be provided as shown in fig. 8(a), and in addition, when the connection line inside the test equipment or the connection line between the test equipment and the external equipment is long, the interior of the test equipment may also be provided with a position for storing the cable.
The installation positions of the parts included in the entity devices shown in fig. 8(a), 8(b), and 8(c) are merely examples, and should not be construed as limitations of the embodiments of the present invention.
It is noted that, herein, relational terms such as first and second, and the like may be used solely to distinguish one entity from another entity without necessarily requiring or implying any actual such relationship or order between such entities. Also, the terms "comprises," "comprising," or any other variation thereof, are intended to cover a non-exclusive inclusion, such that a device that comprises a list of elements does not include only those elements but may include other elements not expressly listed or inherent to such device. Without further limitation, an element defined by the phrase "comprising an … …" does not exclude the presence of additional like elements in the device.
The above description is only a preferred embodiment of the present invention, and is not intended to limit the scope of the present invention. Any modification, equivalent replacement, or improvement made within the spirit and principle of the present invention shall fall within the protection scope of the present invention.
Claims (10)
1. A test apparatus for a flight control and management computer, comprising: a power test assembly, the power test assembly comprising: a first avionics and power instrument cluster;
the first aerial plug is externally connected with the aerial plug of the electric interface to be tested of the flight control and management computer, and the first aerial plug is matched with the aerial plug of the electric interface to be tested; each power line to be tested of the electrical interface to be tested of the flight control and management computer is respectively connected with a group of insertion cores in the aerial plug of the electrical interface to be tested, and each group of insertion cores of the aerial plug of the electrical interface to be tested is respectively connected with a group of insertion cores of the first aerial plug;
the electric power instrument group is connected with each group of inserting cores of the first aerial plug through wires.
2. The test apparatus of claim 1, further comprising: a communication test assembly comprising a second aerial receptacle and a first communication interface connector;
the second aerial plug is externally connected with the aerial plug of the communication interface to be tested of the flight control and management computer, and the second aerial plug is matched with the aerial plug of the communication interface to be tested; each communication line to be tested of the communication interface to be tested of the flight control and management computer is respectively connected with a group of insertion cores of the aerial plug of the communication interface to be tested, and each group of insertion cores of the aerial plug of the communication interface to be tested is respectively connected with a group of insertion cores of the second aerial plug;
the first communication interface connector is connected with a first preset plug core group in the second aviation plug through a lead and is externally connected with a test computer through a first cable; the first preset plug core group comprises at least one group of plug cores corresponding to at least one to-be-tested communication line of the to-be-tested communication interface, and the first cable is a cable matched with the first communication interface connector.
3. The test apparatus of claim 2, wherein the communication test assembly further comprises: a second communication interface connector;
the second communication interface connector is connected with a second preset plug core group in the second aviation plug through a lead and is externally connected with a preset sensor through a second cable; the second preset plug core group comprises at least one group of plug cores corresponding to at least one to-be-tested communication line of the to-be-tested communication interface, and the second cable is a cable matched with the second communication interface connector.
4. The test apparatus of claim 1, wherein the power test assembly further comprises: a third air inserting;
the third aviation plug is connected with the electric power instrument set through a wire and is externally connected with a simulation load through a third cable matched with the third aviation plug;
wherein the analog load is: and simulating an adjustable load of the flight control and management computer.
5. The test apparatus of claim 2, further comprising: the test computer.
6. The test apparatus of claim 3, further comprising: the predetermined sensor.
7. The test apparatus of claim 4, wherein the power test assembly further comprises: the analog load.
8. The test apparatus of claim 2, further comprising: a fourth air navigation plug and a fifth air navigation plug;
the fourth aviation plug is connected with the electric power instrument set through a wire and is externally connected with the aviation plug of a power supply input interface of the flight control and management computer; the fourth aerial plug is matched with the aerial plug of the power input interface;
and the fifth navigation plug is connected with the fourth navigation plug through a wire and is externally connected with a direct current power supply.
9. The test apparatus of claim 8, further comprising: a voltage converter;
and the voltage input end of the voltage converter is externally connected with an alternating current power supply through a wire, and the voltage output end of the voltage converter is connected with the fourth aviation plug through a wire.
10. The test apparatus of claim 9, further comprising: a plurality of test switches;
each test switch uniquely corresponds to one target insertion core and is connected with the target insertion core in series through a lead; the target insertion core is as follows: one ferrule in the first aerial, one ferrule in the second aerial, or one ferrule in the fourth aerial.
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| CN201921153924.XU CN210534766U (en) | 2019-07-22 | 2019-07-22 | Test equipment of flight control and management computer |
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| CN201921153924.XU CN210534766U (en) | 2019-07-22 | 2019-07-22 | Test equipment of flight control and management computer |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110471805A (en) * | 2019-07-22 | 2019-11-19 | 北京中航智科技有限公司 | A kind of test equipment of flight control and management computer |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110471805A (en) * | 2019-07-22 | 2019-11-19 | 北京中航智科技有限公司 | A kind of test equipment of flight control and management computer |
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Effective date of registration: 20230421 Address after: Room 40, 9th Floor, Building 5, Beihang Wuhu Navigation Innovation Park, Anhui Xinwu Economic Development Zone, Wanzhou District, Wuhu City, Anhui Province, 241119 Patentee after: Wuhu United Aircraft Technology Co.,Ltd. Address before: 100176 1st floor, building 1, No.20, Tongji South Road, Beijing Economic and Technological Development Zone, Daxing District, Beijing Patentee before: BEIJING ZHZ TECHNOLOGY Co.,Ltd. |