CN213109848U - Equipment for testing vacuum closestool on civil aircraft - Google Patents
Equipment for testing vacuum closestool on civil aircraft Download PDFInfo
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- CN213109848U CN213109848U CN202021946260.5U CN202021946260U CN213109848U CN 213109848 U CN213109848 U CN 213109848U CN 202021946260 U CN202021946260 U CN 202021946260U CN 213109848 U CN213109848 U CN 213109848U
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- vacuum pump
- pressure sensor
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Abstract
The utility model discloses a device for testing a vacuum closestool on a civil aircraft, which comprises a water source system, a vacuum source system and an electrical control system, wherein the water source system comprises a water inlet pipeline, a pressure accumulator and a water outlet pipeline; a water inlet valve is arranged on the water inlet pipeline; a flushing switch is arranged on the water outlet pipeline; a first pressure sensor is arranged on the pressure accumulator; the vacuum source system comprises a sewage inlet pipeline, a sewage discharge pipeline, a vacuum tank and a vacuum pump, wherein a vacuum pump shutoff valve is arranged on the vacuum pipeline; the sewage discharge pipeline and the sewage inlet pipeline are both communicated with the vacuum tank; a second pressure sensor is arranged on the vacuum tank; a drain valve is arranged on the drain pipeline; the first pressure sensor and the second pressure sensor are communicated with an electric control system, and the water inlet valve, the vacuum pump and the vacuum pump shutoff valve are all controlled by the electric control system. The utility model discloses it can avoid the vacuum pump to work always through electrical control system control vacuum pump running state.
Description
Technical Field
The utility model belongs to the technical field of test equipment, especially, relate to an equipment that is used for vacuum closestool test on civil aircraft.
Background
At present, a vacuum toilet on a civil aircraft is mainly tested by using a test bench which is provided with a vacuum pump, the vacuum pump always works during testing, and the adjustment of the vacuum degree is adjusted by a throttle valve communicated with the atmosphere. The structure can reach the vacuum degree, but consumes more electric power, and is not energy-saving and environment-friendly; meanwhile, the vacuum pump always operates to generate noise pollution.
SUMMERY OF THE UTILITY MODEL
The utility model aims to solve the technical problem that to the not enough among the above-mentioned prior art, provide an equipment that is used for vacuum closestool test on civil aircraft, it can avoid the vacuum pump to work always through electrical control system control vacuum pump running state.
In order to solve the technical problem, the utility model discloses a technical scheme is: the equipment for testing the vacuum closestool on the civil aircraft comprises a water source system, a vacuum source system and an electrical control system, wherein the water source system comprises a water inlet pipeline, a pressure accumulator and a water outlet pipeline; a water inlet valve is arranged on the water inlet pipeline; a flushing switch is arranged on the water outlet pipeline; a first pressure sensor is arranged on the pressure accumulator;
the vacuum source system comprises a sewage inlet pipeline, a sewage discharge pipeline, a vacuum tank and a vacuum pump connected with the vacuum tank through a vacuum pipeline, and a vacuum pump shutoff valve is installed on the vacuum pipeline; the sewage discharge pipeline and the sewage inlet pipeline are both communicated with the vacuum tank; a second pressure sensor is arranged on the vacuum tank; a drain valve is arranged on the drain pipeline;
the first pressure sensor and the second pressure sensor are communicated with an electric control system, and the water inlet valve, the vacuum pump and the vacuum pump shutoff valve are all controlled by the electric control system.
The above-mentioned apparatus for vacuum toilet test on civil aircraft, the said electrical control system includes controller and power; the power supply is used for supplying power to the controller, the first pressure sensor and the second pressure sensor are in communication connection with the controller, and the water inlet valve, the vacuum pump and the vacuum pump shutoff valve are all controlled by the controller.
The controller is an industrial control computer or a single chip microcomputer.
The controller of the device for testing the vacuum toilet on the civil aircraft is an AT89C52 singlechip.
The above-mentioned equipment for vacuum toilet test on civil aircraft, the electrical control system still includes the pilot lamp, the pilot lamp is controlled by the controller.
Compared with the prior art, the utility model has the following advantage: when in use, the water outlet pipeline is connected to the water inlet end of the vacuum closestool (test piece), and the sewage inlet pipeline is connected to the sewage discharge end of the vacuum closestool; the vacuum pump is started to work through the electric control system, when the vacuum degree in the vacuum tank reaches a set value, the vacuum pump shutoff valve is closed, the vacuum pump is closed, whether the air leakage condition exists in each component of the vacuum closestool can be detected in the process, after the air leakage condition is determined to be solved, the flushing switch can be opened, the water in the pressure accumulator is flushed, and the flushing effect is determined. Compare and have now through choke valve control test, the utility model discloses more convenient and fast, and do not need the vacuum pump to last work.
The technical solution of the present invention is further described in detail by the accompanying drawings and examples.
Drawings
Fig. 1 is a schematic diagram of the pipeline of the present invention.
Fig. 2 is a schematic circuit diagram of the present invention.
Fig. 3 is a schematic block diagram of the circuit of the present invention.
Description of reference numerals:
1-water inlet pipeline; 2-an accumulator; 3, a water outlet pipeline;
4-water inlet valve; 5, a flushing switch; 6-a first pressure sensor;
7-a sewage inlet pipeline; 8, a sewage draining pipeline; 9-vacuum tank;
10-vacuum pipeline; 11-vacuum pump; 12-vacuum pump shut-off valve;
13 — a second pressure sensor; 14-a blow-down valve; 15-a controller;
16-a power supply; 17-indicator light.
Detailed Description
As shown in fig. 1, 2 and 3, the equipment for testing the vacuum toilet bowl on the civil aircraft comprises a water source system, a vacuum source system and an electric control system, wherein the water source system comprises a water inlet pipeline 1, an accumulator 2 and a water outlet pipeline 3; a water inlet valve 4 is arranged on the water inlet pipeline 1; a flushing switch 5 is arranged on the water outlet pipeline 3; a first pressure sensor 6 is arranged on the pressure accumulator 2;
the vacuum source system comprises a sewage inlet pipeline 7, a sewage discharge pipeline 8, a vacuum tank 9 and a vacuum pump 11 connected with the vacuum tank 9 through a vacuum pipeline 10, wherein a vacuum pump shutoff valve 12 is installed on the vacuum pipeline 10; the sewage discharge pipeline 8 and the sewage inlet pipeline 7 are both communicated with the vacuum tank 9; a second pressure sensor 13 is arranged on the vacuum tank 9; a blowdown valve 14 is arranged on the blowdown pipeline 8;
the first pressure sensor 6 and the second pressure sensor 13 are both communicated with an electric control system, and the water inlet valve 4, the vacuum pump 11 and the vacuum pump shutoff valve 12 are all controlled by the electric control system.
In the present embodiment, the electrical control system includes a controller 15 and a power supply 16; the power supply 16 is used for supplying power to the controller 15, the first pressure sensor 6 and the second pressure sensor 13 are in communication connection with the controller 15, and the water inlet valve 4, the vacuum pump 11 and the vacuum pump shutoff valve 12 are all controlled by the controller 15.
In this embodiment, the controller 15 is an AT89C52 single chip microcomputer. The controller 15 may also be an industrial control computer.
In this embodiment, the electrical control system further comprises an indicator light 17, which is controlled by the controller 15. The indicator light is used for marking the start and stop of the vacuum pump 11.
The above, only be the utility model discloses a preferred embodiment, it is not right the utility model discloses do any restriction, all according to the utility model discloses the technical entity all still belongs to any simple modification, change and the equivalent structure change of doing above embodiment the utility model discloses technical scheme's within the scope of protection.
Claims (5)
1. An apparatus for testing a vacuum toilet on a civil aircraft, characterized in that: the system comprises a water source system, a vacuum source system and an electrical control system, wherein the water source system comprises a water inlet pipeline, a pressure accumulator and a water outlet pipeline; a water inlet valve is arranged on the water inlet pipeline; a flushing switch is arranged on the water outlet pipeline; a first pressure sensor is arranged on the pressure accumulator;
the vacuum source system comprises a sewage inlet pipeline, a sewage discharge pipeline, a vacuum tank and a vacuum pump connected with the vacuum tank through a vacuum pipeline, and a vacuum pump shutoff valve is installed on the vacuum pipeline; the sewage discharge pipeline and the sewage inlet pipeline are both communicated with the vacuum tank; a second pressure sensor is arranged on the vacuum tank; a drain valve is arranged on the drain pipeline;
the first pressure sensor and the second pressure sensor are communicated with an electric control system, and the water inlet valve, the vacuum pump and the vacuum pump shutoff valve are all controlled by the electric control system.
2. An apparatus for testing vacuum toilets on civil aircraft according to claim 1, wherein: the electrical control system comprises a controller and a power source; the power supply is used for supplying power to the controller, the first pressure sensor and the second pressure sensor are in communication connection with the controller, and the water inlet valve, the vacuum pump and the vacuum pump shutoff valve are all controlled by the controller.
3. An apparatus for testing vacuum toilets on civil aircraft according to claim 2, wherein: the controller is an industrial control computer or a singlechip.
4. An apparatus for testing vacuum toilets on civil aircraft according to claim 2, wherein: the controller is an AT89C52 singlechip.
5. An apparatus for testing vacuum toilets on civil aircraft according to claim 2, wherein: the electrical control system further includes an indicator light that is controlled by the controller.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202021946260.5U CN213109848U (en) | 2020-09-08 | 2020-09-08 | Equipment for testing vacuum closestool on civil aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202021946260.5U CN213109848U (en) | 2020-09-08 | 2020-09-08 | Equipment for testing vacuum closestool on civil aircraft |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN213109848U true CN213109848U (en) | 2021-05-04 |
Family
ID=75661565
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202021946260.5U Active CN213109848U (en) | 2020-09-08 | 2020-09-08 | Equipment for testing vacuum closestool on civil aircraft |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN213109848U (en) |
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2020
- 2020-09-08 CN CN202021946260.5U patent/CN213109848U/en active Active
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