CN214538175U - Aircraft fuel probe test equipment - Google Patents
Aircraft fuel probe test equipment Download PDFInfo
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- CN214538175U CN214538175U CN202022358646.0U CN202022358646U CN214538175U CN 214538175 U CN214538175 U CN 214538175U CN 202022358646 U CN202022358646 U CN 202022358646U CN 214538175 U CN214538175 U CN 214538175U
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- fuel probe
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Abstract
The utility model discloses an aircraft fuel probe test equipment, including be used for with the test box of current analog signal conversion for frequency value, be connected and be used for the probe binding post with fuel probe connection with the test box, set up on the test box and be used for showing the display module of frequency value and be connected and be used for the power binding post who is connected with portable power source with the test box. The utility model discloses an aircraft fuel probe test equipment can simulate aircraft avionics equipment, passes through test equipment with current signal and converts frequency value into to can show fuel probe frequency value in real time, before fuel probe installation oil tank, whether quick location fuel probe breaks down, convenient to carry, easy operation, the convenience detects fuel probe.
Description
Technical Field
The utility model belongs to the technical field of general aviation auxiliary assembly, specifically speaking, the utility model relates to an aircraft fuel probe test equipment.
Background
The fuel probe is installed to the oil tank of aircraft wing, transmits to avionics through the crosslinked line, by the inside treater of avionics, converts analog signal into digital signal and sends to synthesize the display screen, and operating personnel accessible synthesizes the fuel volume of display screen observation aircraft, ensures that the fuel volume that the aircraft actually filled is the same with the numerical value of synthesizing the display. At present, the fuel quantity is generally checked by an operator to assemble the whole aircraft avionics system, and the fuel quantity of the aircraft can be observed on a comprehensive display screen after the system is jointly debugged. Once the fuel probe breaks down, operating personnel need dismantle the aircraft wing, just can change after removing the inside oil tank of wing again, and whole process is consuming time and is laboursome, lacks among the prior art to carrying out the test equipment of quick location trouble before the fuel probe installation oil tank.
SUMMERY OF THE UTILITY MODEL
The utility model discloses aim at solving one of the technical problem that exists among the prior art at least. Therefore, the utility model provides an aircraft fuel probe test equipment, the purpose is convenient to detect the fuel probe.
In order to realize the purpose, the utility model discloses the technical scheme who takes does: aircraft fuel probe test equipment is including being used for converting the test box of current analog signal for frequency value, be connected with the test box and be used for the probe binding post who is connected with the fuel probe, set up on the test box and be used for showing the display module of frequency value and be connected with the test box and be used for the power binding post who is connected with portable power source.
The testing box comprises an anti-reverse connection circuit, a voltage stabilizing module and a fuse, the power supply wiring terminal is electrically connected with the voltage stabilizing module through the anti-reverse connection circuit, the probe wiring terminal is electrically connected with the voltage stabilizing module through the fuse, and the voltage stabilizing module and the probe wiring terminal are electrically connected with the display module.
The reverse connection preventing circuit comprises a first diode and a second diode, wherein the anode of the first diode is electrically connected with the power supply wiring terminal, the cathode of the first diode is electrically connected with the voltage stabilizing module, the anode of the second diode is electrically connected with the voltage stabilizing module, and the cathode of the second diode is electrically connected with the power supply wiring terminal.
The first diode is electrically connected with the power supply wiring terminal and the voltage stabilizing module through an AWG wire.
And the second diode is electrically connected with the power supply wiring terminal and the voltage stabilizing module through an AWG wire.
The voltage stabilizing module is electrically connected with the fuse, the display module and the probe wiring terminal through an AWG lead.
The fuse is electrically connected with the voltage stabilizing module, the display module and the probe wiring terminal through an AWG lead.
The utility model discloses an aircraft fuel probe test equipment can simulate aircraft avionics equipment, passes through test equipment with current signal and converts frequency value into to can show fuel probe frequency value in real time, before fuel probe installation oil tank, whether quick location fuel probe breaks down, convenient to carry, easy operation, the convenience detects fuel probe.
Drawings
The description includes the following figures, the contents shown are respectively:
FIG. 1 is a schematic structural diagram of an aircraft fuel probe test apparatus of the present invention;
FIG. 2 is a top view of the aircraft fuel probe testing apparatus of the present invention;
FIG. 3 is a schematic circuit diagram of the aircraft fuel probe test apparatus of the present invention;
labeled as: 1. a box body; 2. a power supply wiring terminal; 3. a probe wiring terminal; 4. a display module; 5. a first diode; 6. a second diode; 7. a voltage stabilization module; 8. and a fuse.
Detailed Description
The following detailed description of the embodiments of the present invention will be given with reference to the accompanying drawings, for the purpose of helping those skilled in the art to understand more completely, accurately and deeply the conception and technical solution of the present invention, and to facilitate its implementation.
It should be noted that, in the following embodiments, the "first" and "second" do not represent an absolute distinction relationship in structure and/or function, nor represent a sequential execution order, but merely for convenience of description.
As shown in fig. 1-3, the utility model provides an aircraft fuel probe test equipment, including be used for with the test box of current analog signal conversion for frequency value, be connected with the test box and be used for the probe binding post 3 with fuel probe connection, set up on the test box and be used for showing frequency value's display module 4 and be connected with the test box and be used for the power binding post 2 of being connected with portable power source.
Specifically, as shown in fig. 1 to 3, the test box includes a box body 1, an anti-reverse connection circuit, a voltage stabilizing module 7 and a fuse 8, the anti-reverse connection circuit, the voltage stabilizing module 7 and the fuse 8 are disposed inside the box body 1, the box body 1 is of a rectangular structure, the display module 4 is fixedly disposed on one side wall of the box body 1, the power connection terminal 2 is electrically connected with the voltage stabilizing module 7 through the anti-reverse connection circuit, the probe connection terminal 3 is electrically connected with the voltage stabilizing module 7 through the fuse 8, and the voltage stabilizing module 7 and the probe connection terminal 3 are electrically connected with the display module 4.
As shown in fig. 1 to 3, the reverse connection preventing circuit includes a first diode 5 and a second diode 6, an anode of the first diode 5 is electrically connected to the power connection terminal 2, a cathode of the first diode 5 is electrically connected to the voltage stabilizing module 7, an anode of the second diode 6 is electrically connected to the voltage stabilizing module 7, and a cathode of the second diode 6 is electrically connected to the power connection terminal 2. The input voltage of the power supply wiring terminal 2 does not exceed 35V, and when the positive pole and the negative pole of the power supply are connected reversely, the circuit is automatically cut off through the reverse connection prevention circuit of the positive pole and the negative pole of the first diode 5 and the second diode 6. The fuel probe voltage stabilizing circuit uses a +12V direct current voltage stabilizing module 7, and the input voltage which does not exceed 35V is automatically transformed and stabilized to 12V through the voltage stabilizing module 7.
As shown in fig. 3, the first diode 5 is electrically connected to the power connection terminal 2 and the voltage stabilizing module 7 through an awg (american wire gauge) wire. The second diode 6 is electrically connected to the power supply terminal 2 and the regulator block 7 through the AWG wire. The voltage stabilizing module 7 is electrically connected with the fuse 8, the display module 4 and the probe terminal 3 through the AWG lead. The fuse 8 is electrically connected with the voltage stabilizing module 7, the display module 4 and the probe terminal 3 through the AWG lead.
Since the fuel probe load current is less than 1A, when the circuit current exceeds 1A, the circuit is automatically opened through the fuse 8. When the probe wiring terminal 3 is connected to the fuel probe, the display module 4 automatically displays the real-time frequency value.
The input voltage of the voltage stabilizing module 7 is 8-35V, the output voltage is 12V, the current is 4-5A, the work is 60W, the highest conversion efficiency is 96%, and the working temperature is-40 ℃ to +85 ℃.
The display module 4 adopts a high-performance singlechip of Microchip company in America as a central processing unit, and has the characteristics of high reliability, strong anti-interference capability, wide measurement range, high measurement precision, advanced full-synchronous periodic measurement method and the like. The working voltage of the display module 4 is DC12-24V, the working current is 30mA, the working temperature is-30-70 ℃, the frequency measurement precision can reach 0.01% at 25 ℃, the resolution can reach 0.001HZ, the frequency measurement range is 0.15 HZ-100 KHZ, the display digit is 5 digits, and the display refresh rate is more than 3HZ for 3 times/second.
The aircraft fuel probe test equipment with the structure has the following advantages:
1. the fuel probe frequency value is displayed in real time, the carrying is convenient, the operation is simple, the reverse connection prevention of the anode and the cathode of the power supply is realized, the working voltage is always stable at 12V, the overcurrent protection is realized, and the like, so that the operability of the test equipment is greatly simplified;
2. the method comprises the steps of simulating aircraft avionics equipment, converting current signals into frequency values through test equipment, and quickly positioning whether a fuel probe fails or not before the fuel probe is installed on an oil tank.
The invention has been described above by way of example with reference to the accompanying drawings. Obviously, the specific implementation of the present invention is not limited by the above-described manner. Various insubstantial improvements are made by adopting the method conception and the technical proposal of the utility model; or without improvement, the above conception and technical solution of the present invention can be directly applied to other occasions, all within the protection scope of the present invention.
Claims (7)
1. Aircraft fuel probe test equipment, its characterized in that: including the test box that is used for converting current analog signal into frequency value, be connected with the test box and be used for the probe binding post who is connected with the fuel probe, set up on the test box and be used for the display module of display frequency value and be connected with the test box and be used for the power binding post who is connected with portable power source.
2. An aircraft fuel probe testing device according to claim 1, wherein: the testing box comprises an anti-reverse connection circuit, a voltage stabilizing module and a fuse, the power supply wiring terminal is electrically connected with the voltage stabilizing module through the anti-reverse connection circuit, the probe wiring terminal is electrically connected with the voltage stabilizing module through the fuse, and the voltage stabilizing module and the probe wiring terminal are electrically connected with the display module.
3. An aircraft fuel probe testing device according to claim 2, wherein: the reverse connection preventing circuit comprises a first diode and a second diode, wherein the anode of the first diode is electrically connected with the power supply wiring terminal, the cathode of the first diode is electrically connected with the voltage stabilizing module, the anode of the second diode is electrically connected with the voltage stabilizing module, and the cathode of the second diode is electrically connected with the power supply wiring terminal.
4. An aircraft fuel probe testing device according to claim 3, wherein: the first diode is electrically connected with the power supply wiring terminal and the voltage stabilizing module through an AWG wire.
5. An aircraft fuel probe testing device according to claim 3, wherein: and the second diode is electrically connected with the power supply wiring terminal and the voltage stabilizing module through an AWG wire.
6. An aircraft fuel probe testing device according to any one of claims 2 to 5, wherein: the voltage stabilizing module is electrically connected with the fuse, the display module and the probe wiring terminal through an AWG lead.
7. An aircraft fuel probe testing device according to any one of claims 2 to 5, wherein: the fuse is electrically connected with the voltage stabilizing module, the display module and the probe wiring terminal through an AWG lead.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202022358646.0U CN214538175U (en) | 2020-10-21 | 2020-10-21 | Aircraft fuel probe test equipment |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202022358646.0U CN214538175U (en) | 2020-10-21 | 2020-10-21 | Aircraft fuel probe test equipment |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN214538175U true CN214538175U (en) | 2021-10-29 |
Family
ID=78229476
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202022358646.0U Active CN214538175U (en) | 2020-10-21 | 2020-10-21 | Aircraft fuel probe test equipment |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN214538175U (en) |
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2020
- 2020-10-21 CN CN202022358646.0U patent/CN214538175U/en active Active
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| TR01 | Transfer of patent right | ||
| TR01 | Transfer of patent right |
Effective date of registration: 20221115 Address after: 241100 Diamond Road, Anhui Xinwu Economic Development Zone, Wanlu District, Wuhu City, Anhui Province Patentee after: CETC WUHU DIAMOND AIRCRAFT MANUFACTURE Co.,Ltd. Address before: 210000 floor 7, building B4, Jiulong lake international enterprise headquarters park, No. 19, Suyuan Avenue, Jiangning District, Nanjing, Jiangsu Province (Jiangning Development Zone) Patentee before: Nanjing R & D center of CETC Wuhu diamond Aircraft Manufacturing Co.,Ltd. |