CN203350004U - Automatic detecting device of cockpit air tight test - Google Patents
Automatic detecting device of cockpit air tight test Download PDFInfo
- Publication number
- CN203350004U CN203350004U CN 201320495823 CN201320495823U CN203350004U CN 203350004 U CN203350004 U CN 203350004U CN 201320495823 CN201320495823 CN 201320495823 CN 201320495823 U CN201320495823 U CN 201320495823U CN 203350004 U CN203350004 U CN 203350004U
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- input end
- output terminal
- cockpit
- control system
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- Testing Of Devices, Machine Parts, Or Other Structures Thereof (AREA)
- Examining Or Testing Airtightness (AREA)
Abstract
The utility model relates to an automatic detecting device of a cockpit air tight test. The outlet of an air source pressure gage is connected with the inlet of an air supply pressure gage through a pressure reducer; the outlet of the pressure reducer is connected with the inlet of an airplane cockpit through a solenoid valve; the outlet of the airplane cockpit is respectively connected with an overflow valve and the inlet of a pressure sensor; the output end of the pressure sensor is connected with the input end of a control system; the output end of the control system is connected with the input end of the solenoid valve. According to the automatic detecting device of the cockpit air tight test, the control system is used for receiving a signal of the cockpit pressure sensor, automatic air supply is realized through analysis, calculation and judgment, self-clocking is realized, the air tightness detection result of the cockpit is automatically analyzed and judged, the operation is simple, the timekeeping precision is high, the tightness detection is accurate, and the use is convenient and rapid.
Description
Technical field
The utility model relates to a kind of aircraft cockpit air tightness detecting system, particularly a kind of passenger cabin tightness test automatic detection device.
Background technology
The pressure cabin of present generation aircraft must be through strict air tight test before dispatching from the factory.Various countries have all stipulated the maximum leakage rate that allows for different machines and different situations.Factory inspection passenger cabin impermeability generally has two kinds of methods at present: discharge method and pressure decline method.Discharge method is directly perceived, approach the real work situation, but test unit is more complicated, and the source of the gas of flow measurement device and continuous working need to be arranged.Pressure decline method is simple, convenient, factory often adopts this method, and its passenger cabin air tight test carries out under surface condition, first adopts outside Manual gas valve to the aircraft cockpit air feed, after certain atmospheric pressure value is arrived in back under pressure, stop air feed, and start to use manual time-keeping, after passenger cabin air pressure drops to certain air pressure, stop timing, calculate like this gas leakage time and air leakage, but can not directly measure leakage rate, need to calculate by transformational relation.
The utility model content
Technical problem to be solved in the utility model is to receive the passenger cabin pressure sensor signal by control system is set in passenger cabin air tight test air supply system, and calculate and judge by analysis, the control solenoid valve opens or closes, and carry out timing according to atmospheric pressure value, whether the impermeability of automatic analysis and judgment passenger cabin detects qualified.
For above-mentioned technical matters, the utility model by the following technical solutions, a kind of passenger cabin tightness test automatic detection device, the outlet of bleed pressure table connects the supply gas pressure table entry by decompressor, it is characterized in that, the outlet of described decompressor connects the entrance of aircraft cockpit by solenoid valve, and the outlet of aircraft cockpit connects respectively the entrance of surplus valve and pressure transducer, the input end of the output terminal connection control system of pressure transducer, the output terminal connected electromagnetic valve input end of control system.
Described control system comprises single-chip microcomputer, the output terminal of described single-chip microcomputer is connected with the input end of display, the input end of single-chip microcomputer is connected with the output terminal of keyboard input, the output terminal of pressure transducer is connected with the input end of single-chip microcomputer by signal regulating device, A/D converter successively, and the output terminal of single-chip microcomputer is connected with the input end of solenoid valve by interface circuit.
The utility model has the advantage of, utilize control system to receive the passenger cabin pressure sensor signal, calculate by analysis judgement, realize automatic feeding, self-clocking, the impermeability testing result of automatic analysis and judgment passenger cabin, simple to operate, accuracy of timekeeping is high, and impermeability detects accurately, easy to use.
The accompanying drawing explanation
Fig. 1 is system block diagram of the present utility model.
Fig. 2 is the composition frame chart of control system 5 in the utility model.
Embodiment
Below in conjunction with drawings and Examples, the utility model is described in further detail, referring to Fig. 1, a kind of passenger cabin tightness test automatic detection device, the outlet of bleed pressure table 1 connects supply gas pressure table 3 entrance by decompressor 2, the outlet of described decompressor 2 connects the entrance of aircraft cockpit 4 by solenoid valve 6, the outlet of aircraft cockpit 4 connects respectively the entrance of surplus valve 8 and pressure transducer 7, the input end of the output terminal connection control system 5 of pressure transducer 7, output terminal connected electromagnetic valve 6 input ends of control system 5.
Further, described control system 5 comprises single-chip microcomputer 51, the output terminal of described single-chip microcomputer 51 is connected with the input end of display 52, the input end of single-chip microcomputer 51 is connected with the output terminal of keyboard input 53, the output terminal of pressure transducer 7 is connected with the input end of single-chip microcomputer 51 by signal regulating device 55, A/D converter 54 successively, and the output terminal of single-chip microcomputer 51 is connected with the input end of solenoid valve 6 by interface circuit 56.
Test operation step of the present utility model is as follows:
1) access source of the gas, and gas source pipe is connected with required pilot system.
2) connect the AC220V external power source, press power switch, power light is bright.Control system 5 enters duty, and now " air pressure demonstration " pilot lamp is bright, and display 52 adopts nixie display, for showing aircraft cockpit 4 internal gas pressures.
3) click " test " button, " air feed " pilot lamp is bright, and gas supply electromagnetic valve 6 is opened, and the 2MPa air to open begins to aircraft cockpit 4 inflations, and display 52 is monitoring aircraft cockpit 4 internal pressures in real time.
4), when force value being detected and be 30.6KPa, system Self-shut electromagnetic valve 6, stop inflation.
5) when monitoring force value and be 29KPa, system is carried out timing automatically, drops to 26.3KPa and stops timing.
Detect completely, system shows that aircraft cockpit 4 internal pressures drop to the 26.3KPa spent time from 29KPa automatically, and " time showing " pilot lamp is bright.
Claims (2)
1. a passenger cabin tightness test automatic detection device, the outlet of bleed pressure table connects the supply gas pressure table entry by decompressor, it is characterized in that, the outlet of described decompressor connects the entrance of aircraft cockpit by solenoid valve, the outlet of aircraft cockpit connects respectively the entrance of surplus valve and pressure transducer, the input end of the output terminal connection control system of pressure transducer, the output terminal connected electromagnetic valve input end of control system.
2. passenger cabin tightness test automatic detection device as claimed in claim 1, it is characterized in that, described control system comprises single-chip microcomputer, the output terminal of described single-chip microcomputer is connected with the input end of display, the input end of single-chip microcomputer is connected with the output terminal of keyboard input, the output terminal of pressure transducer is connected with the input end of single-chip microcomputer by signal regulating device, A/D converter successively, and the output terminal of single-chip microcomputer is connected with the input end of solenoid valve by interface circuit.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 201320495823 CN203350004U (en) | 2013-08-14 | 2013-08-14 | Automatic detecting device of cockpit air tight test |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 201320495823 CN203350004U (en) | 2013-08-14 | 2013-08-14 | Automatic detecting device of cockpit air tight test |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN203350004U true CN203350004U (en) | 2013-12-18 |
Family
ID=49749888
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN 201320495823 Expired - Lifetime CN203350004U (en) | 2013-08-14 | 2013-08-14 | Automatic detecting device of cockpit air tight test |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN203350004U (en) |
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104460659A (en) * | 2014-11-17 | 2015-03-25 | 赵红军 | Military aviation cockpit air adjusting system external field detecting device and method |
| CN105547608A (en) * | 2014-11-03 | 2016-05-04 | 中国飞行试验研究院 | Apparatus for air tightness testing of airplane |
| CN107655638A (en) * | 2017-08-31 | 2018-02-02 | 阜阳扬宇充电设备有限公司 | A kind of power module manufacture air-tightness detection device |
| CN107796574A (en) * | 2017-11-30 | 2018-03-13 | 闫晓红 | A kind of aircraft is airtight to check complex control system and its application method |
| CN113310638A (en) * | 2021-07-05 | 2021-08-27 | 成都斯孚凯科技有限公司 | Cabin airtightness tester control system |
-
2013
- 2013-08-14 CN CN 201320495823 patent/CN203350004U/en not_active Expired - Lifetime
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105547608A (en) * | 2014-11-03 | 2016-05-04 | 中国飞行试验研究院 | Apparatus for air tightness testing of airplane |
| CN104460659A (en) * | 2014-11-17 | 2015-03-25 | 赵红军 | Military aviation cockpit air adjusting system external field detecting device and method |
| CN104460659B (en) * | 2014-11-17 | 2018-02-27 | 赵红军 | A kind of military cockpit air handling system outfield detection method |
| CN107655638A (en) * | 2017-08-31 | 2018-02-02 | 阜阳扬宇充电设备有限公司 | A kind of power module manufacture air-tightness detection device |
| CN107796574A (en) * | 2017-11-30 | 2018-03-13 | 闫晓红 | A kind of aircraft is airtight to check complex control system and its application method |
| CN113310638A (en) * | 2021-07-05 | 2021-08-27 | 成都斯孚凯科技有限公司 | Cabin airtightness tester control system |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CX01 | Expiry of patent term | ||
| CX01 | Expiry of patent term |
Granted publication date: 20131218 |