CN212341407U - Aviation power supply inspection tester - Google Patents
Aviation power supply inspection tester Download PDFInfo
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- CN212341407U CN212341407U CN202020486153.2U CN202020486153U CN212341407U CN 212341407 U CN212341407 U CN 212341407U CN 202020486153 U CN202020486153 U CN 202020486153U CN 212341407 U CN212341407 U CN 212341407U
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Abstract
An aviation power supply inspection tester comprises a plurality of inspection devices. The aviation power supply inspection tester can detect industrial control of the output power supply of the power supply vehicle; the power supply vehicle can be controlled to output 28.8V, 28.5V is controlled to be converted into 57V, and industrial control is graphically displayed; the controllable power supply vehicle can be controlled to boost the voltage at 0V-70V, and corresponding industrial control and graphical curve display are detected; industrial control of 115V single-phase and three-phase power supplies of the power supply vehicle can be detected, and industrial control is graphically displayed; the power supply starting vehicle can be subjected to on-load working condition detection, and the graphical curve displays industrial control; but intelligent printing detection information guarantees that the supply vehicle is in normal operating mode, ensures in time to discover and the troubleshooting, realizes the good guarantee to the aircraft.
Description
Technical Field
The utility model belongs to the technical field of the aviation power supply, concretely relates to aviation power supply detector.
Background
The aviation power supply can supply energy to various parts in the aviation field. But like ordinary power supplies, aviation power supplies are also subject to failure, so special aviation power supply inspection equipment is required.
SUMMERY OF THE UTILITY MODEL
In order to solve the problem, the utility model provides an aviation power supply inspection tester, include: the outer container has installation space, be provided with panel bracket and sheet metal component mounting structure in the installation space, liquid crystal display subassembly, PT plug, highlight display, exchange three-phase measuring module, discharge control current module, master control circuit module, PT plug sheet metal component, current detection control module, 24V battery power supply management module, customization aluminium base discharge load, current detection control module, double-circuit auto-lock button subassembly, three open the switch subassembly, direct current pointer table module, 115V exchange pointer table module, printer module, aviation plug-in components, signal collection conditioning module, key socket line, power supply module, charging source and operation control processing board have set gradually on the sheet metal component mounting structure respectively with liquid crystal display subassembly the PT plug the highlight display, Exchange three-phase measuring module the control current module that discharges the master control circuit module PT plug sheet metal component the current detection control module 24V battery power supply management module the aluminium base load that discharges of customization current detection control module the double-circuit auto-lock button subassembly three open the switch subassembly direct current pointer table module 115V exchanges pointer table module the printer module the aviation subassembly the power signal gathers and conditions the module the key socket line the power supply module with charging source connects.
Preferably, waterproof sealing rubber strips are arranged at the edges of the joints of the panel bracket and the sheet metal part mounting structure.
Preferably, the sheet metal part mounting structure is provided with an acrylic plate.
Preferably, a sand blasting alumina plate is arranged on the sheet metal part mounting structure.
Preferably, a protective handle is arranged on the sheet metal part mounting structure.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings needed to be 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 inventive exercise.
Fig. 1 is a schematic structural diagram of an aviation power supply inspection tester provided by the utility model.
Detailed Description
In order to make the objects, technical solutions and advantages of the present invention more apparent, the present invention will be described in detail with reference to the accompanying drawings. It should be understood that the description is intended to be illustrative only and is not intended to limit the scope of the present invention. Moreover, in the following description, descriptions of well-known structures and techniques are omitted so as to not unnecessarily obscure the concepts of the present invention.
Referring to fig. 1, in an embodiment of the present application, the present application provides an aviation electrical source inspection tester, including: outer box 1, has installation space, be provided with panel bracket 3 and sheet metal component mounting structure 16 in the installation space, liquid crystal display subassembly 7, PT plug (5, 6, 8, 9), highlight display 10, interchange three-phase measuring module 12, discharge control current module 13, main control circuit module 14, PT plug sheet metal component 15, current detection control module 17, 24V battery power supply management module 19, customization aluminium base discharge load 20, current detection control module 21, double-circuit auto-lock button subassembly (24,25,26, 27, 29, 30), three-way switch subassembly 28, direct current pointer table module 31, 115V exchanges pointer table module 32, printer module 33, aviation plug-in subassembly 34, power signal acquisition and conditioning module 39, key socket line 40, power supply module 41, charging source 42 and operation control processing board 43 have set gradually on the sheet metal component mounting structure 16, the operation control processing board 43 is respectively connected with the liquid crystal display component 7, the PT plugs (5, 6, 8, 9), the highlight display 10, the alternating current three-phase measuring module 12, the discharge control current module 13, the main control circuit module 14, the PT plug sheet metal part 15, the current detection control module 17, the 24V battery power supply management module 19, and the customized aluminum-based discharge load 20 in sequence, the current detection control module 21, double-circuit auto-lock button subassembly (24,25,26, 27, 29, 30), three open the switch subassemblies 28, direct current pointer table module 31 the 115V exchanges pointer table module 32 the printer module 33 aviation plug subassembly 34 power signal gathers and conditions module 39 the key socket line 40 power supply module 41 with charging source 42 connects.
Referring to fig. 1, in the embodiment of the present application, a waterproof sealing rubber strip 4 is disposed at the edge of the joint between the panel bracket 3 and the sheet metal part mounting structure 16. By providing the waterproof sealing rubber strip 4, the sealing property between the panel bracket 3 and the sheet metal part mounting structure 16 can be improved.
Referring to fig. 1, in the embodiment of the present application, an acrylic plate 22 is disposed on the sheet metal part mounting structure 16. By providing the acrylic plate 22, each component can be relatively stably mounted on the sheet metal member mounting structure 16.
As shown in fig. 1, in the embodiment of the present application, a sandblasted alumina plate 23 is provided on the sheet metal member mounting structure 16. By providing the sandblasted alumina plate 23, each component can be relatively stably mounted on the sheet metal member mounting structure 16.
Referring to fig. 1, in the embodiment of the present application, a protective handle 35 is disposed on the sheet metal part mounting structure 16. Through setting up protection hand (hold) 35, can remove whole aviation power supply inspection tester well.
The operation principle of the entire aviation power supply inspection instrument is described below by taking the detection of the 810B battery-powered vehicle as an example.
810B storage battery starting vehicle inspection process
1. The tester is opened, and the PJ-500T plug of the starting vehicle is inserted into the socket and locked.
2. And pressing a main switch of the inspection tester, and displaying the current voltage of the input equipment by the liquid crystal screen. When the input voltage is more than or equal to 29.5V, the normal no-load voltage is obtained, and when the voltage is less than 29V, the no-load voltage of the starting vehicle is too low, so that the vehicle needs to be charged.
3. When the voltage of the starting vehicle is more than or equal to 29V, a load test can be carried out, a load switch is pressed for 2-3 seconds, about 36A current is loaded, and if the voltage is more than or equal to 29.5V in the loading process, the electric quantity of the starting vehicle is sufficient; if the loading voltage is between 29V and 29.5V, the electric quantity is still enough; if the loading voltage is less than 29V, the electric quantity is low, the battery cannot be used, and charging is needed.
4. And printing and archiving various inspection parameters through the printer module 33.
5. And (5) closing the switch of the inspection tester, pulling out the plug and finishing the inspection.
115V three-phase alternating-current power supply inspection process for power supply vehicle
1. The tester is opened and the PJ-500TB plug of the starting vehicle is inserted into the socket and locked.
2. And starting the power supply vehicle and setting the power supply vehicle to be in an alternating current output state.
3. The tester device master switch is pressed, and the liquid crystal display component 7 displays the current input device voltage. The normal state is when the voltage value of each phase of A, B and C is between 112-118V, and the abnormal state is when the voltage value is not in the range, so that the power supply vehicle needs to be checked.
The liquid crystal display component 7 displays the voltages of A-B, B-C and A-C, the voltage value is in a normal state when the voltage value is between 195-205V, and the voltage value is in an abnormal state when the voltage value is not in the range, and the power supply vehicle needs to be checked.
The frequency value is displayed on the screen, the frequency value is in a normal state when the frequency value is 390-410Hz, and the frequency value is in an abnormal state when the frequency value is not in the range, so that the power supply vehicle needs to be checked.
4. The printing items are used to check the parameters and archived.
5. And (5) closing the switch of the inspection tester, pulling out the plug and finishing the inspection.
115V single-phase alternating-current power supply inspection process for power supply vehicle
1. The tester is opened, the PJ-200T plug of the starting vehicle is inserted into the socket and locked.
2. And starting the power supply vehicle and setting the power supply vehicle to be in an alternating current output state.
3. And pressing a main switch of the inspection tester equipment, and displaying the current input equipment voltage by the liquid crystal screen. The normal state is when the phase voltage value is between 112-118V, and the abnormal state is when the voltage value is not in the range, so that the power supply vehicle needs to be checked.
The frequency value is displayed on the screen, the frequency value is in a normal state when the frequency value is 390-410Hz, and the frequency value is in an abnormal state when the frequency value is not in the range, so that the power supply vehicle needs to be checked.
4. Printing each checking parameter and archiving.
5. And (5) closing the switch of the inspection tester, pulling out the plug and finishing the inspection.
28.5V direct current inspection process of power supply vehicle
1. And opening the inspection tester, inserting the PJ-500T plug of the power supply vehicle into the socket, and locking.
2. And starting the power supply vehicle and setting a 28.5V direct current output state.
3. And pressing a main switch of the inspection tester equipment, and displaying the current input equipment voltage by the liquid crystal screen. The normal state is when the voltage value is between 28.5V-30.5V, and the abnormal state is when the voltage value is not in the range, and the power supply vehicle needs to be checked.
4. Printing each checking parameter and archiving.
5. And (5) closing the switch of the inspection tester, pulling out the plug and finishing the inspection.
28.5V/57V direct current inspection process of power supply vehicle
1. And opening the inspection tester, inserting the PJ-800T plug of the power supply vehicle into the socket, and locking.
2. And starting the power supply vehicle and setting a 57V direct current output state.
3. The inspection instrument equipment main switch is pressed. When a key of '28.5V on' is pressed, the power supply vehicle outputs 28.5V direct current voltage, and the liquid crystal screen displays the current voltage of the input equipment. The two paths of voltage values are in a normal state when the voltage values are between 28.5 and 30.5V, and are in an abnormal state when the voltage values are not in the range, and the power supply vehicle needs to be checked.
4. When a '57V on' key is pressed down, the output of the power supply vehicle is converted into high voltage, and the liquid crystal screen displays the current voltage of the input equipment. One path of voltage value is between 28.5V and 30.5V, the other path of voltage value is in a normal state when the voltage value is between 57V and 59V, and the other path of voltage value is in an abnormal state when the voltage value is not in the range, so that the power supply vehicle needs to be checked.
5. Check if the 28.5V and 57V switches switch correctly.
6. Printing of concurrent files of inspection parameters
7. The "57V on" key is turned off. The "28.5V on" button is off.
8. And (5) closing the switch of the inspection tester, pulling out the plug and finishing the inspection.
0-70V direct current boosting inspection process for power supply vehicle
1. And opening the inspection tester, inserting the PJ-800T plug of the power supply vehicle into the socket, and locking.
2. And starting the power supply vehicle and setting a 70V direct current output state.
3. The inspection instrument equipment main switch is pressed. When a key of '70V on' is pressed, the output voltage of the power supply vehicle gradually rises from 0V, the screen displays the current voltage value and displays a rising curve of time and voltage, the voltage rises to 48V within about 15 seconds, rises to 80V within about 18 seconds, and finally the no-load voltage reaches 80-83V, the rising process and the state of the voltage are inspected, and if the abnormal condition exists, the inspection is required.
4. Printing each checking parameter and archiving.
5. The "70V on" button is turned off and the voltage drops back to 0V.
6. And (5) closing the switch of the inspection tester, pulling out the plug and finishing the inspection.
The aviation power supply inspection tester can detect industrial control of the output power supply of the power supply vehicle; the power supply vehicle can be controlled to output 28.8V, 28.5V is controlled to be converted into 57V, and industrial control is graphically displayed; the controllable power supply vehicle can be controlled to boost the voltage at 0V-70V, and corresponding industrial control and graphical curve display are detected; industrial control of 115V single-phase and three-phase power supplies of the power supply vehicle can be detected, and industrial control is graphically displayed; the power supply starting vehicle can be subjected to on-load working condition detection, and the graphical curve displays industrial control; but intelligent printing detection information guarantees that the supply vehicle is in normal operating mode, ensures in time to discover and the troubleshooting, realizes the good guarantee to the aircraft.
It is to be understood that the above-described embodiments of the present invention are merely illustrative of or explaining the principles of the invention and are not to be construed as limiting the invention. Therefore, any modification, equivalent replacement, improvement and the like made without departing from the spirit and scope of the present invention should be included in the protection scope of the present invention. Further, it is intended that the appended claims cover all such variations and modifications as fall within the scope and boundaries of the appended claims or the equivalents of such scope and boundaries.
Claims (5)
1. An aviation power supply inspection tester, comprising: outer container (1), installation space has, be provided with panel bracket (3) and sheet metal component mounting structure (16) in the installation space, sheet metal component mounting structure (16) are gone up and have been set gradually liquid crystal display subassembly (7), PT plug (5, 6, 8, 9), highlight display (10), exchange three-phase measuring module (12), discharge control current module (13), master control circuit module (14), PT plug sheet metal component (15), current detection control module (17), 24V battery power supply management module (19), customization aluminium base discharge load (20), current detection control module (21), double-circuit auto-lock key subassembly (24,25,26, 27, 29, 30), three-way switch subassembly (28), direct current pointer table module (31), 115V exchanges pointer table module (32), printer module (33), aviation plug subassembly (34), Power signal gathers and conditions module (39), key socket line (40), mains operated module (41), charging source (42) and operation control processing board (43), operation control processing board (43) in proper order respectively with liquid crystal display subassembly (7) PT plug (5, 6, 8, 9) highlight display (10) exchange three-phase measuring module (12) discharge control current module (13) master control circuit module (14) PT plug sheet metal component (15) current detection control module (17) 24V battery power supply management module (19) customization aluminium base discharge load (20) current detection control module (21) double-circuit auto-lock button subassembly (24,25,26, 27, 29, 30) three open close subassembly (28) direct current pointer table module (31), 115V exchanges pointer table module (32), printer module (33) aviation plug component (34) power signal gathers and conditions module (39) key socket line (40) power supply module (41) with charging source (42) are connected.
2. The aircraft power inspection tester as claimed in claim 1, characterized in that the edge of the junction of the panel bracket (3) and the sheet metal part mounting structure (16) is provided with a waterproof sealing rubber strip (4).
3. The aircraft power inspection gauge of claim 1, wherein an acrylic plate (22) is provided on the sheet metal component mounting structure (16).
4. The aircraft power inspection gauge of claim 1, wherein a sandblasted alumina plate (23) is provided on the sheet metal component mounting structure (16).
5. The aircraft power inspection gauge of claim 1, wherein a protective handle (35) is provided on the sheet metal component mounting structure (16).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202020486153.2U CN212341407U (en) | 2020-04-03 | 2020-04-03 | Aviation power supply inspection tester |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202020486153.2U CN212341407U (en) | 2020-04-03 | 2020-04-03 | Aviation power supply inspection tester |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN212341407U true CN212341407U (en) | 2021-01-12 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202020486153.2U Active CN212341407U (en) | 2020-04-03 | 2020-04-03 | Aviation power supply inspection tester |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN212341407U (en) |
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2020
- 2020-04-03 CN CN202020486153.2U patent/CN212341407U/en active Active
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