CN103487219B - A kind of Small General Aircraft passenger cabin and fuel tank integration air tightness detection system - Google Patents
A kind of Small General Aircraft passenger cabin and fuel tank integration air tightness detection system Download PDFInfo
- Publication number
- CN103487219B CN103487219B CN201310459427.3A CN201310459427A CN103487219B CN 103487219 B CN103487219 B CN 103487219B CN 201310459427 A CN201310459427 A CN 201310459427A CN 103487219 B CN103487219 B CN 103487219B
- Authority
- CN
- China
- Prior art keywords
- fuel tank
- passenger cabin
- valve
- signal piping
- pressure detector
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Active
Links
Landscapes
- Examining Or Testing Airtightness (AREA)
Abstract
The present invention relates to a kind of Small General Aircraft passenger cabin and fuel tank integration air tightness detection system, comprise source of the gas, shunt, the airtight signal piping of passenger cabin and the airtight signal piping of fuel tank, and the input end of shunt is connected with source of the gas, the input end of the airtight signal piping of passenger cabin and the airtight signal piping of fuel tank is connected on two output terminals of shunt, and output terminal is respectively used to be connected with passenger cabin and fuel tank; The airtight signal piping of described passenger cabin and the airtight signal piping of fuel tank are provided with pneumatic triple piece, flow control valve, flowmeter, pressure detector A, pneumatic Test Switchboard and pressure detector B all successively, and are provided with vent valve with the link of passenger cabin and fuel tank.Like this, the passenger cabin of aircraft and the integrated air-leakage test of fuel tank can be realized, real time monitoring, powerful, effectively improve the work efficiency of air-leakage test, reduce aircraft development cost, and system architecture is simple, cost of manufacture is low, simple, convenient, is applicable to the air-leakage test of Small General Aircraft.
Description
Technical field
The invention belongs to aircraft air-leakage test technical field, particularly a kind of Small General Aircraft passenger cabin and fuel tank integration air tightness detection system.
Background technology
At present, the air-leakage test of domestic existing aircraft factory to the passenger cabin of aircraft and fuel tank is all adopt different detection systems to separate complete independently, and does not have versatility, and detection time is long, efficiency is slow, substantially increases the cost of aircraft development; These existing air tightness detection equipments are for requiring that the Small General Aircraft of cost control just exists the excess of technology, high in cost of production drawback.Up to the present, domesticly also there is no a kind ofly to be suitable for that this structure of Small General Aircraft is simple, the passenger cabin of highly versatile and the integrated air tightness detection equipment of fuel tank.
Summary of the invention
For solving the above-mentioned problems in the prior art, the invention provides and a kind ofly realize the passenger cabin of aircraft and the integrated air-leakage test of fuel tank, real time monitoring, powerful, work efficiency is high, reduces the cost of aircraft development, and system architecture is simple, cost of manufacture is low, simple, convenient, is applicable to the air tightness detection system of Small General Aircraft.
For solving the problems of the technologies described above, the present invention adopts following technical scheme:
A kind of Small General Aircraft passenger cabin and fuel tank integration air tightness detection system, include source of the gas, shunt, the airtight signal piping of passenger cabin and the airtight signal piping of fuel tank, and the input end of described shunt is connected with described source of the gas, the input end of the airtight signal piping of described passenger cabin and the airtight signal piping of fuel tank is connected on two output terminals of described shunt, and output terminal is respectively used to be connected with passenger cabin and fuel tank; Wherein, the airtight signal piping of described passenger cabin is provided with successively the first pneumatic triple piece, first flow variable valve, first-class gauge, the first pressure detector A, the first pneumatic Test Switchboard and the first pressure detector B, and is provided with first row air valve with the link of described passenger cabin; The airtight signal piping of described fuel tank is provided with successively the second pneumatic triple piece, second adjustable valve, second gauge, the second pressure detector A, the second pneumatic Test Switchboard and the second pressure detector B, and is provided with second row air valve with the link of described fuel tank.
Further, the airtight signal piping of described passenger cabin and the airtight signal piping of fuel tank are also respectively equipped with the first micrometering valve and the second micrometering valve, and described first micrometering valve and the second micrometering valve are located between described first-class gauge and the first pressure detector A, between described second gauge and the second pressure detector A respectively.
Further, the link of the airtight signal piping of described passenger cabin and described passenger cabin is also provided with the first safety shutoff valve and the first safety valve, the input end of described first safety shutoff valve is connected with the airtight signal piping of described passenger cabin and the first safety valve respectively with output terminal; The link of the airtight signal piping of described fuel tank and described fuel tank is also provided with the second safety shutoff valve and the second safety valve, the input end of described second safety shutoff valve is connected with the airtight signal piping of described fuel tank and the second safety valve (49) respectively with output terminal.
Further, described first row air valve and the first safety shutoff valve are located between described first pneumatic Test Switchboard and the first pressure detector B successively; Described second row air valve and the second safety shutoff valve (48) are located between described second pneumatic Test Switchboard and the second pressure detector B successively.
Further, described source of the gas is air compressor machine, and described shunt is distributing T-pipe device.
Further, described air compressor machine is the air compressor machine that can reach 0.7MPa, the pressure relief ranges of described first pneumatic triple piece and the second pneumatic triple piece is 0.05MPa ~ 0.85 MPa, and the range of adjustment of described first flow variable valve and second adjustable valve is 0 ~ 3.5KPa/min.
Further, described first pneumatic Test Switchboard and the second pneumatic Test Switchboard are hand sluice valve, and described first pressure detector A, the first pressure detector B, the second pressure detector A and the second pressure detector B are tensimeter.
Further, described source of the gas also includes the gas source interface for being connected with external air source, and described gas source interface is connected with described shunt by tracheae.
The invention has the beneficial effects as follows:
The present invention passes through technique scheme, the passenger cabin of aircraft and the integrated air-leakage test of fuel tank can be realized, achieve the real time monitoring of airtight detection simultaneously, detection system is powerful, effectively improves the work efficiency of air-leakage test, reduces the cost of aircraft development, and system architecture is simple, cost of manufacture is low, simple, convenient, is applicable to the air-leakage test of Small General Aircraft.
In addition, can accurately control aerated flow value by this first micrometering valve and the second micrometering valve, use more convenient operation, faster; Can be shielded to passenger cabin and fuel tank by the first safety shutoff valve and the first safety valve, the second safety shutoff valve and the second safety valve; guarantee to cause the destruction to passenger cabin and fuel tank because of the hypertonia surprisingly caused; in testing process, the security of passenger cabin and fuel tank is high, and quality is guaranteed.
Accompanying drawing explanation
Fig. 1 is the structural principle schematic diagram of a kind of Small General Aircraft passenger cabin of the present invention and fuel tank integration air tightness detection system embodiment.
Embodiment
In order to make object of the present invention, technical scheme and advantage clearly understand, below in conjunction with drawings and Examples, the present invention is further elaborated.Should be appreciated that specific embodiment described herein only in order to explain the present invention, be not intended to limit the present invention.
As shown in fig. 1:
A kind of Small General Aircraft passenger cabin described in the embodiment of the present invention one and fuel tank integration air tightness detection system, include source of the gas 1, shunt 2, the airtight signal piping of passenger cabin 3 and the airtight signal piping 4 of fuel tank, and the input end of shunt 2 is connected with source of the gas 1, the input end of the airtight signal piping of passenger cabin 3 and the airtight signal piping 4 of fuel tank is connected on two output terminals of shunt 2, and output terminal is respectively used to be connected with passenger cabin 5 and fuel tank 6.Wherein, the airtight signal piping of described passenger cabin 3 is provided with successively the first pneumatic triple piece 31, first flow variable valve 32, first-class gauge 33, first pressure detector A 35, first pneumatic Test Switchboard 36 and the first pressure detector B 30, and is provided with first row air valve 37 with the link of passenger cabin 5, the airtight signal piping of described fuel tank 4 is provided with successively the second pneumatic triple piece 41, second adjustable valve 42, second gauge 43, second pressure detector A 45, second pneumatic Test Switchboard 46 and the second pressure detector B 40, and is provided with second row air valve 47 with the link of fuel tank 6, described source of the gas 1 is the air compressor machine that can reach 0.7MPa, described shunt 2 is distributing T-pipe devices, described first pneumatic triple piece 31 and the second pneumatic triple piece 41 are all primarily of air strainer, reduction valve and oil sprayer composition, its pressure relief ranges is 0.05MPa ~ 0.85 MPa, the range of adjustment of described first flow variable valve 32 and second adjustable valve 42 is 0 ~ 3.5KPa/min, described first pneumatic Test Switchboard 36 and the second pneumatic Test Switchboard 46 are hand sluice valve, described first pressure detector A 35, first pressure detector B 30, second pressure detector A 45 and the second pressure detector B 40 is tensimeter.
The principle of work of Small General Aircraft passenger cabin of the present invention and fuel tank integration air tightness detection system is: be first connected in the air hot air intake of aircraft by the fast plug of airtight for passenger cabin signal piping 3 output terminal, and be threaded with fuel tank vent mouth by airtight for fuel tank signal piping 4 output terminal, then open source of the gas 1 and export 0.7MPa gas, then through shunt 2, gas is divided into two-way and exports, a road airtight signal piping 3 of supply passenger cabin carries out passenger cabin 5 air tightness test, and the airtight signal piping 4 of a road supply tank carries out fuel tank 6 air tightness test, is specially, first pneumatic triple piece 31 of the airtight signal piping 3 of passenger cabin filters, after step-down and oil and water separation, export dry, pure 100kPa gas, when the real-time pressure value that the first pressure detector A 35 shows is 100kPa, open the first pneumatic Test Switchboard 36, inflate to passenger cabin 5, pressurization, and adjust first flow variable valve 32 to control the flow value inflated to passenger cabin 5 simultaneously, control the pressurising speed to passenger cabin 5, make the first pressure detector A 35 consistent with the real-time pressure value (as 38kPa) that the first pressure detector B 30 shows, complete air-leakage test, meanwhile, second pneumatic triple piece 41 of the airtight signal piping 4 of fuel tank filters, after step-down and oil and water separation, export dry, pure 30kPa gas, when the real-time pressure value that the second pressure detector A 45 shows is 30kPa, open the second pneumatic Test Switchboard 46, inflate to fuel tank 6, pressurization, and adjust second adjustable valve 42 to control the flow value inflated to fuel tank 6 simultaneously, control the pressurising speed to fuel tank 6, make the second pressure detector A 45 consistent with the real-time pressure value (as 18kPa) that the second pressure detector B 40 shows, complete air-leakage test, first row air valve 37 and second row air valve 47 is opened, to be discharged fast by the gas in passenger cabin 5 and fuel tank 6 after detection.
Like this, the passenger cabin 5 of aircraft and the integrated air-leakage test of fuel tank 6 can be realized by the present invention, realize the real time monitoring of airtight detection simultaneously, detection system is powerful, effectively improves the work efficiency of air-leakage test, reduces the cost of aircraft development, and system architecture is simple, cost of manufacture is low, simple, convenient, is applicable to the air-leakage test of Small General Aircraft.
In addition, described source of the gas 1 also include gas source interface (show in figure and show) for being connected with external air source, described gas source interface is connected with shunt 2 by tracheae; When source of the gas 1 adopts air compressor machine to provide gas, this gas source interface is closed, otherwise air compressor machine is closed.Even if larger to volume like this, broad-minded aircraft cockpit 5 and fuel tank 6 carry out air-leakage test, also can guarantee sufficient gas, guarantee inflation, pressurising speed.
As the present invention one preferred embodiment, the airtight signal piping of described passenger cabin 3 and the airtight signal piping 4 of fuel tank are also respectively equipped with the first micrometering valve 34 and the second micrometering valve 44, and described first micrometering valve 34 and the second micrometering valve 44 are located between first-class gauge 33 and the first pressure detector A 35, between second gauge 43 and the second pressure detector A 45 respectively.The flow value inflated to passenger cabin 5 and fuel tank 6 accurately can be controlled by this first micrometering valve 34 and the second micrometering valve 44, pressurising speed controls more accurate, more easily control the real-time pressure value consistance that the first pressure detector A 35 and the first pressure detector B 30 show, use more convenient operation, faster.
As the another preferred embodiment of the present invention, the airtight signal piping 3 of described passenger cabin and the link of passenger cabin 5 are also provided with the first safety shutoff valve 38 and the first safety valve 39, and signal piping 3 airtight with passenger cabin and the first safety valve 39 are connected respectively for input end and the output terminal of described first safety shutoff valve 38; The airtight signal piping 4 of described fuel tank and the link of fuel tank 6 are also provided with the second safety shutoff valve 48 and the second safety valve 49, and signal piping 4 airtight with fuel tank and the second safety valve 49 are connected respectively for input end and the output terminal of described second safety shutoff valve 48; And first row air valve 37 and the first safety shutoff valve 38 are located between the first pneumatic Test Switchboard 36 and the first pressure detector B 30 successively; Described second row air valve 47 and the second safety shutoff valve 48 are located between the second pneumatic Test Switchboard 46 and the second pressure detector B 40 successively.Can shield to passenger cabin 5 and fuel tank 6 by opening the first safety shutoff valve 38 and the first safety valve 39, second safety shutoff valve 48 and the second safety valve 49; guarantee to cause the destruction to passenger cabin 5 and fuel tank 6 because of the hypertonia surprisingly caused; in testing process, the security of passenger cabin 5 and fuel tank 6 is high, and quality is guaranteed.
Certainly, air tightness detection system of the present invention is also applied in and detects the impermeability of other different aircraft or different parts, only need according to the air pressure requirement detecting position during detection, the atmospheric pressure value of regulable control different parts, highly versatile, the fuel tank in China's present General Aviation field and passenger cabin air-leakage test have strong demonstration meaning.
The above is the preferred embodiment of the present invention; it should be pointed out that for those skilled in the art, under the premise without departing from the principles of the invention; can also make some improvements and modifications, these improvements and modifications are also considered as protection scope of the present invention.
Claims (7)
1. a Small General Aircraft passenger cabin and fuel tank integration air tightness detection system, it is characterized in that: include source of the gas (1), shunt (2), the airtight signal piping of passenger cabin (3) and the airtight signal piping of fuel tank (4), and the input end of described shunt (2) is connected with described source of the gas (1), the input end of the airtight signal piping of described passenger cabin (3) and the airtight signal piping of fuel tank (4) is connected on two output terminals of described shunt (2), and output terminal is respectively used to be connected with passenger cabin (5) and fuel tank (6); Wherein, the airtight signal piping of described passenger cabin (3) is provided with successively the first pneumatic triple piece (31), first flow variable valve (32), first-class gauge (33), the first pressure detector A (35), the first pneumatic Test Switchboard (36) and the first pressure detector B (30), and is provided with first row air valve (37) with the link of described passenger cabin (5); The airtight signal piping of described fuel tank (4) is provided with successively the second pneumatic triple piece (41), second adjustable valve (42), second gauge (43), the second pressure detector A (45), the second pneumatic Test Switchboard (46) and the second pressure detector B (40), and is provided with second row air valve (47) with the link of described fuel tank (6); The airtight signal piping of described passenger cabin (3) and the airtight signal piping of fuel tank (4) are also respectively equipped with the first micrometering valve (34) and the second micrometering valve (44), and described first micrometering valve (34) and the second micrometering valve (44) are located between described first-class gauge (33) and the first pressure detector A (35), between described second gauge (43) and the second pressure detector A (45) respectively.
2. Small General Aircraft passenger cabin according to claim 1 and fuel tank integration air tightness detection system, it is characterized in that: the airtight signal piping of described passenger cabin (3) and the link of described passenger cabin (5) are also provided with the first safety shutoff valve (38) and the first safety valve (39), and the input end of described first safety shutoff valve (38) is connected with the airtight signal piping of described passenger cabin (3) and the first safety valve (39) respectively with output terminal; The airtight signal piping of described fuel tank (4) and the link of described fuel tank (6) are also provided with the second safety shutoff valve (48) and the second safety valve (49), and the input end of described second safety shutoff valve (48) is connected with the airtight signal piping of described fuel tank (4) and the second safety valve (49) respectively with output terminal.
3. Small General Aircraft passenger cabin according to claim 2 and fuel tank integration air tightness detection system, is characterized in that: described first row air valve (37) and the first safety shutoff valve (38) are located between described first pneumatic Test Switchboard (36) and the first pressure detector B (30) successively; Described second row air valve (47) and the second safety shutoff valve (48) are located between described second pneumatic Test Switchboard (46) and the second pressure detector B (40) successively.
4., according to the Small General Aircraft passenger cabin in claims 1 to 3 described in any one and fuel tank integration air tightness detection system, it is characterized in that: described source of the gas (1) is air compressor machine, described shunt (2) is distributing T-pipe device.
5. Small General Aircraft passenger cabin according to claim 4 and fuel tank integration air tightness detection system, it is characterized in that: described air compressor machine is the air compressor machine that can reach 0.7MPa, the pressure relief ranges of described first pneumatic triple piece (31) and the second pneumatic triple piece (41) is 0.05MPa ~ 0.85MPa, and the range of adjustment of described first flow variable valve (32) and second adjustable valve (42) is 0 ~ 3.5KPa/min.
6. according to the Small General Aircraft passenger cabin in claims 1 to 3 described in any one and fuel tank integration air tightness detection system, it is characterized in that: described first pneumatic Test Switchboard (36) and the second pneumatic Test Switchboard (46) are hand sluice valve, described first pressure detector A (35), the first pressure detector B (30), the second pressure detector A (45) and the second pressure detector B (40) are tensimeter.
7. according to the Small General Aircraft passenger cabin in claims 1 to 3 described in any one and fuel tank integration air tightness detection system, it is characterized in that: described source of the gas (1) also includes the gas source interface for being connected with external air source, described gas source interface is connected with described shunt (2) by tracheae.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201310459427.3A CN103487219B (en) | 2013-09-30 | 2013-09-30 | A kind of Small General Aircraft passenger cabin and fuel tank integration air tightness detection system |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201310459427.3A CN103487219B (en) | 2013-09-30 | 2013-09-30 | A kind of Small General Aircraft passenger cabin and fuel tank integration air tightness detection system |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN103487219A CN103487219A (en) | 2014-01-01 |
| CN103487219B true CN103487219B (en) | 2015-10-28 |
Family
ID=49827618
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201310459427.3A Active CN103487219B (en) | 2013-09-30 | 2013-09-30 | A kind of Small General Aircraft passenger cabin and fuel tank integration air tightness detection system |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN103487219B (en) |
Families Citing this family (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105628305A (en) * | 2014-11-03 | 2016-06-01 | 中国飞行试验研究院 | Airplane air tightness test method |
| CN105711853B (en) * | 2014-12-03 | 2017-09-29 | 中国飞机强度研究所 | A kind of three valves linkage discharge mechanism and method for cockpit air test |
| CN106197892B (en) * | 2016-07-30 | 2018-09-07 | 沧州惠邦重工装备制造有限公司 | A kind of Battery case air tightness detection equipment |
| 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 |
| CN107741292A (en) * | 2017-11-30 | 2018-02-27 | 闫晓红 | A kind of aircraft pressure checking device and its application method |
| CN110763403A (en) * | 2019-11-20 | 2020-02-07 | 广汽乘用车有限公司 | System and method for rapidly detecting air tightness of automobile part |
| CN111504572A (en) * | 2020-05-18 | 2020-08-07 | 湖北汽车工业学院 | System and method for detecting air pressure tightness of cab suspension |
| CN114001873A (en) * | 2021-10-18 | 2022-02-01 | 中航通飞华南飞机工业有限公司 | Air tightness inspection integrated equipment and detection method for aircraft anti-icing and rain-removing system |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN86101658A (en) * | 1986-03-14 | 1987-09-23 | 法国电力公司 | The leak detection of heat interchanger in service |
| US5056554A (en) * | 1987-02-20 | 1991-10-15 | White F Grove | Fluid loss, damage prevention and control system |
| DE4035739A1 (en) * | 1990-11-09 | 1992-05-14 | Semprex Erzeugnisse Fritz Koen | Leakage testing device for valve - uses reciprocating piston for supplying test pressure fed to valve seat |
| CN101517390A (en) * | 2006-10-10 | 2009-08-26 | 因菲康有限公司 | Sniffing leak detector |
| CN102338685A (en) * | 2011-05-18 | 2012-02-01 | 大连理工大学 | Airtightness test device and method for pressure container |
-
2013
- 2013-09-30 CN CN201310459427.3A patent/CN103487219B/en active Active
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN86101658A (en) * | 1986-03-14 | 1987-09-23 | 法国电力公司 | The leak detection of heat interchanger in service |
| US5056554A (en) * | 1987-02-20 | 1991-10-15 | White F Grove | Fluid loss, damage prevention and control system |
| DE4035739A1 (en) * | 1990-11-09 | 1992-05-14 | Semprex Erzeugnisse Fritz Koen | Leakage testing device for valve - uses reciprocating piston for supplying test pressure fed to valve seat |
| CN101517390A (en) * | 2006-10-10 | 2009-08-26 | 因菲康有限公司 | Sniffing leak detector |
| CN102338685A (en) * | 2011-05-18 | 2012-02-01 | 大连理工大学 | Airtightness test device and method for pressure container |
Also Published As
| Publication number | Publication date |
|---|---|
| CN103487219A (en) | 2014-01-01 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN103487219B (en) | A kind of Small General Aircraft passenger cabin and fuel tank integration air tightness detection system | |
| CN202720101U (en) | Pipeline gas tightness detection apparatus | |
| CN202814666U (en) | Comprehensive air tightness test bench | |
| CN203549370U (en) | High-pressure integrated gas supplying device | |
| CN105547608A (en) | Apparatus for air tightness testing of airplane | |
| CN204988892U (en) | Pressure collision test equipment | |
| CN201714898U (en) | Pneumatic automatic airbag adjusting device | |
| CN204269301U (en) | A kind of automobile altitude valve leak-testing apparatus | |
| CN204228364U (en) | A kind of air tightness detection apparatus | |
| CN208331787U (en) | Continuous gas supply superpressure pressure protective device | |
| CN205277998U (en) | Rubber tube check valve detection device | |
| CN202533288U (en) | Automatic air bag air sampler | |
| CN210834054U (en) | Air tightness test device for through passage system | |
| CN203835862U (en) | Air cylinder piston rod locking device | |
| CN103821946A (en) | Automatic air-pressure safety valve for natural gas | |
| CN104295892B (en) | CO2Fluid reservoir supercharge control system | |
| CN203385532U (en) | Pressured on-off system for valve testing stand | |
| CN203731093U (en) | Intelligent device for emptying unqualified gas | |
| CN204903170U (en) | Brake test pipeline atmospheric pressure adjusting device | |
| CN206399602U (en) | A kind of semi-automatic manograph | |
| CN203606090U (en) | Simple outfield airborne radar airtight tester | |
| CN204359768U (en) | A kind of methane transducer calibration equipment | |
| CN204821535U (en) | Frock is adjusted to brake test pipeline atmospheric pressure | |
| CN203785854U (en) | Double chamber detection modulator used for differential pressure type airtight detector | |
| CN110440132A (en) | The used group sealing unit inflated with nitrogen system and method for one kind |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant |