CN103487219A - Small general-purpose plane cockpit and fuel tank integrated gas tightness detecting system - Google Patents
Small general-purpose plane cockpit and fuel tank integrated gas tightness detecting system Download PDFInfo
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- CN103487219A CN103487219A CN201310459427.3A CN201310459427A CN103487219A CN 103487219 A CN103487219 A CN 103487219A CN 201310459427 A CN201310459427 A CN 201310459427A CN 103487219 A CN103487219 A CN 103487219A
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- passenger cabin
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- gas tightness
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Abstract
The invention relates to a small general-purpose plane cockpit and fuel tank integrated gas tightness detecting system. The small general-purpose plane cockpit and fuel tank integrated gas tightness detecting system comprises a gas source, a flow distributor, a cockpit gas tightness detecting pipeline and a fuel tank gas tightness detecting pipeline. The input end of the flow distributor is connected with the gas source. The input end of the cockpit gas tightness detecting pipeline and the input end of the fuel tank gas tightness detecting pipeline are connected to the two output ends of the flow distributor respectively, and the output end of cockpit gas tightness detecting pipeline and the output end of the fuel tank gas tightness detecting pipeline are used for being connected with a cockpit and a fuel tank respectively. The cockpit gas tightness detecting pipeline and the fuel tank gas tightness detecting pipeline are respectively and sequentially provided with a pneumatic triplet, a flow regulating valve, a flowmeter, a pressure detector A, a pneumatic detecting switch and a pressure detector B, the end, connected with the cockpit, of the cockpit gas tightness detecting pipeline is provided with an exhaust valve, and the end, connected with the fuel tank, of the fuel tank gas tightness detecting pipeline and the fuel tank is provided with an exhaust valve. Therefore, the integrated gas tightness detection can be carried out on the cockpit and the fuel tank of a plane, monitoring is carried out in real time, the function is powerful, the working efficiency of gas tightness detection is effectively improved, the develop cost of the plane is reduced, and the system is simple in structure, low in manufacturing cost, easy and convenient to operate, and suitable for carrying out gas tightness detection on small general-purpose planes.
Description
Technical field
The invention belongs to aircraft impermeability detection technique field, particularly a kind of Small General Aircraft passenger cabin and the integrated air tightness detection system of fuel tank.
Background technology
At present, it is all to adopt different detection systems to separate complete independently that domestic existing aircraft factory is detected the impermeability of the passenger cabin of aircraft and fuel tank, and does not have versatility, and detection time is long, efficiency is slow, has greatly increased the cost of aircraft development; These existing air tightness detection equipments just exist the excess of technology, high in cost of production drawback for the Small General Aircraft that requires cost control.Up to the present, domestic also do not have a kind of this simple in structure, the passenger cabin of highly versatile of Small General Aircraft and integrated air tightness detection equipment of fuel tank of being suitable for.
Summary of the invention
For solving the above-mentioned problems in the prior art, the invention provides a kind of integrated impermeability detection that realizes passenger cabin and the fuel tank of aircraft, real time monitoring, powerful, high efficiency, reduced 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 the integrated air tightness detection system of fuel tank, 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 fuel tank with passenger cabin; Wherein, be provided with successively the first pneumatic triple piece, first flow variable valve, first flow meter, the first pressure detector A, the first pneumatic Test Switchboard and the first pressure detector B on the airtight signal piping of described passenger cabin, and be provided with the first row air valve with the link of described passenger cabin; Be provided with successively the second pneumatic triple piece, second adjustable valve, the second flowmeter, the second pressure detector A, the second pneumatic Test Switchboard and the second pressure detector B on the airtight signal piping of described fuel tank, and be provided with the second row air valve with the link of described fuel tank.
Further, also be respectively equipped with the first micrometering valve and the second micrometering valve on the airtight signal piping of described passenger cabin and the airtight signal piping of fuel tank, described the first micrometering valve and the second micrometering valve are located at respectively between described first flow meter and the first pressure detector A, between described the second flowmeter and the second pressure detector A.
Further, also be provided with the first safety shutoff valve and the first safety valve on the link of the airtight signal piping of described passenger cabin and described passenger cabin, the input end of described the first safety shutoff valve is connected with the first safety valve with the airtight signal piping of described passenger cabin respectively with output terminal; Also be provided with the second safety shutoff valve and the second safety valve on the link of the airtight signal piping of described fuel tank and described fuel tank, the input end of described the second safety shutoff valve is connected with the second safety valve (49) with the airtight signal piping of described fuel tank respectively with output terminal.
Further, described first row air valve and the first safety shutoff valve are located between the 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 the 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 the distributing T-pipe device.
Further, described air compressor machine is for reaching the air compressor machine of 0.7MPa, the pressure relief ranges of described the 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, the described first pneumatic Test Switchboard and the second pneumatic Test Switchboard are hand sluice valve, and described the 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, can realize that the passenger cabin of aircraft and the integrated impermeability of fuel tank detect, realized the real time monitoring of airtight detection simultaneously, detection system is powerful, effectively improves the work efficiency that impermeability detects, and has reduced the cost of aircraft development, and system architecture is simple, cost of manufacture is low, simple, convenient, and the impermeability that is applicable to Small General Aircraft detects.
In addition, by this first micrometering valve and the second micrometering valve, can accurately control the aerated flow value, use more convenient operation, faster; By the first safety shutoff valve and the first safety valve, the second safety shutoff valve and the second safety valve, can shield to passenger cabin and fuel tank; guarantee can not cause because of the hypertonia that accident causes the destruction to passenger cabin and fuel tank; in testing process, passenger cabin and fuel tank is safe, and quality is guaranteed.
The 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 the integrated air tightness detection system embodiment of fuel tank.
Embodiment
In order to make purpose of the present invention, technical scheme and advantage clearer, 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, is not intended to limit the present invention.
As shown in fig. 1:
The described a kind of Small General Aircraft passenger cabin of the embodiment of the present invention one and the integrated air tightness detection system of fuel tank, include source of the gas 1, shunt 2, the airtight signal piping 3 of passenger cabin 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 3 of passenger cabin 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 fuel tank 6 with passenger cabin 5.Wherein, be provided with successively the first pneumatic triple piece 31, first flow variable valve 32, first flow meter 33, the pneumatic Test Switchboard 36 of the first pressure detector A 35, first and the first pressure detector B 30 on the airtight signal piping 3 of described passenger cabin, and be provided with first row air valve 37 with the link of passenger cabin 5, be provided with successively the second pneumatic triple piece 41, second adjustable valve 42, the second flowmeter 43, the pneumatic Test Switchboard 46 of the second pressure detector A 45, second and the second pressure detector B 40 on the airtight signal piping 4 of described fuel tank, and be 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 the first pneumatic triple piece 31 and the second pneumatic triple piece 41 are all mainly by air strainer, reduction valve and oil sprayer form, 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, the described first pneumatic Test Switchboard 36 and the second pneumatic Test Switchboard 46 are hand sluice valve, described the 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.
The principle of work of Small General Aircraft passenger cabin of the present invention and the integrated air tightness detection system of fuel tank is: at first the fast plug of airtight signal piping 3 output terminals of passenger cabin is connected in the air hot air intake of aircraft, and airtight signal piping 4 output terminals of fuel tank are threaded with the fuel tank ventilating opening, then open source of the gas 1 output 0.7MPa gas, then through shunt 2, gas is divided into to two-way output, a road is supplied with the airtight signal piping 3 of passenger cabin and is carried out passenger cabin 5 air tightness tests, and the airtight signal piping 4 of a road supply tank carries out fuel tank 6 air tightness tests, is specially, the first pneumatic triple piece 31 of the airtight signal piping 3 of passenger cabin is filtered, after step-down and oil and water separation, output is dry, pure 100kPa gas, when the real-time pressure value of the first pressure detector A 35 demonstrations is 100kPa, open the first pneumatic Test Switchboard 36, to passenger cabin 5, inflated, pressurization, and adjust first flow variable valve 32 to control to the flow value of passenger cabin 5 inflations simultaneously, the pressurising speed of control 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, completing impermeability detects, meanwhile, the second pneumatic triple piece 41 of the airtight signal piping 4 of fuel tank is filtered, after step-down and oil and water separation, output is dry, pure 30kPa gas, when the real-time pressure value of the second pressure detector A 45 demonstrations is 30kPa, open the second pneumatic Test Switchboard 46, to fuel tank 6 inflations, pressurization, and adjust second adjustable valve 42 to control to the flow value of fuel tank 6 inflations simultaneously, the pressurising speed of control 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, completing impermeability detects, open first row air valve 37 and second row air valve 47 after detecting, discharge fast with the gas by passenger cabin 5 and fuel tank 6.
Like this, can realize that by the present invention the passenger cabin 5 of aircraft and the integrated impermeability of fuel tank 6 detect, realize the real time monitoring of airtight detection simultaneously, detection system is powerful, effectively improves the work efficiency that impermeability detects, and has reduced the cost of aircraft development, and system architecture is simple, cost of manufacture is low, simple, convenient, and the impermeability that is applicable to Small General Aircraft detects.
In addition, described source of the gas 1 also include gas source interface for being connected with external air source (figure show show), described gas source interface is connected with shunt 2 by tracheae; When source of the gas 1 adopts air compressor machine that gas is provided, this gas source interface is closed, otherwise air compressor machine is closed.Even so larger, the broad-minded aircraft cockpit 5 of volume and fuel tank 6 are carried out to the impermeability detection, also can guarantee sufficient gas, guarantee inflation, pressurising speed.
As the present invention's one preferred embodiment, also be respectively equipped with the first micrometering valve 34 and the second micrometering valve 44 on the airtight signal piping 3 of described passenger cabin and the airtight signal piping 4 of fuel tank, described the first micrometering valve 34 and the second micrometering valve 44 are located at respectively between first flow meter 33 and the first pressure detector A 35, between the second flowmeter 43 and the second pressure detector A 45.By this first micrometering valve 34 and the second micrometering valve 44, can accurately control to the flow value of passenger cabin 5 and fuel tank 6 inflations, pressurising speed is controlled 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, also be provided with the first safety shutoff valve 38 and the first safety valve 39 on the link of the airtight signal piping 3 of described passenger cabin and passenger cabin 5, the input end of described the first safety shutoff valve 38 is connected with the first safety valve 39 with the airtight signal piping 3 of passenger cabin respectively with output terminal; Also be provided with the second safety shutoff valve 48 and the second safety valve 49 on the link of the airtight signal piping 4 of described fuel tank and fuel tank 6, the input end of described the second safety shutoff valve 48 is connected with the second safety valve 49 with the airtight signal piping 4 of fuel tank respectively with output terminal; 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.By opening the first safety shutoff valve 38 and the first safety valve 39, the second safety shutoff valve 48 and the second safety valve 49 can shield to passenger cabin 5 and fuel tank 6; guarantee can not cause because of the hypertonia that accident causes the destruction to passenger cabin 5 and fuel tank 6; in testing process, passenger cabin 5 and fuel tank 6 is safe, and quality is guaranteed.
Certainly, the impermeability that air tightness detection system of the present invention also is applied in other different aircrafts or different parts is detected, only need be according to the air pressure requirement that detects position during detection, regulating the atmospheric pressure value of controlling different parts gets final product, highly versatile, fuel tank and the detection of passenger cabin impermeability in the present General Aviation of China field 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 also are considered as protection scope of the present invention.
Claims (8)
1. a Small General Aircraft passenger cabin and the integrated air tightness detection system of fuel tank, 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 fuel tank (6) with passenger cabin (5); Wherein, be provided with successively the first pneumatic triple piece (31), first flow variable valve (32), first flow meter (33), the first pressure detector A(35 on the airtight signal piping of described passenger cabin (3)), the first pneumatic Test Switchboard (36) and the first pressure detector B(30), and be provided with first row air valve (37) with the link of described passenger cabin (5); Be provided with successively the second pneumatic triple piece (41), second adjustable valve (42), the second flowmeter (43), the second pressure detector A(45 on the airtight signal piping of described fuel tank (4)), the second pneumatic Test Switchboard (46) and the second pressure detector B(40), and be provided with second row air valve (47) with the link of described fuel tank (6).
2. Small General Aircraft passenger cabin according to claim 1 and the integrated air tightness detection system of fuel tank, it is characterized in that: also be respectively equipped with the first micrometering valve (34) and the second micrometering valve (44) on the airtight signal piping of described passenger cabin (3) and the airtight signal piping of fuel tank (4), described the first micrometering valve (34) and the second micrometering valve (44) are located at respectively described first flow meter (33) and the first pressure detector A(35) between, described the second flowmeter (43) and the second pressure detector A(45) between.
3. Small General Aircraft passenger cabin according to claim 2 and the integrated air tightness detection system of fuel tank, it is characterized in that: also be provided with the first safety shutoff valve (38) and the first safety valve (39) on the link of the airtight signal piping of described passenger cabin (3) and described passenger cabin (5), the input end of described the first safety shutoff valve (38) is connected with the first safety valve (39) with the airtight signal piping of described passenger cabin (3) respectively with output terminal; Also be provided with the second safety shutoff valve (48) and the second safety valve (49) on the link of the airtight signal piping of described fuel tank (4) and described fuel tank (6), the input end of described the second safety shutoff valve (48) is connected with the second safety valve (49) with the airtight signal piping of described fuel tank (4) respectively with output terminal.
4. Small General Aircraft passenger cabin according to claim 3 and the integrated air tightness detection system of fuel tank, it is characterized in that: described first row air valve (37) and the first safety shutoff valve (38) are located at the described first pneumatic Test Switchboard (36) and the first pressure detector B(30 successively) between; Described second row air valve (47) and the second safety shutoff valve (48) are located at the described second pneumatic Test Switchboard (46) and the second pressure detector B(40 successively) between.
5. according to any one described Small General Aircraft passenger cabin and the integrated air tightness detection system of fuel tank in claim 1 to 4, it is characterized in that: described source of the gas (1) is air compressor machine, and described shunt (2) is the distributing T-pipe device.
6. Small General Aircraft passenger cabin according to claim 5 and the integrated air tightness detection system of fuel tank, it is characterized in that: described air compressor machine is for reaching the air compressor machine of 0.7MPa, the pressure relief ranges of described the first pneumatic triple piece (31) and the second pneumatic triple piece (41) is 0.05MPa～0.85 MPa, and the range of adjustment of described first flow variable valve (32) and second adjustable valve (42) is 0～3.5KPa/min.
7. according to any one described Small General Aircraft passenger cabin and the integrated air tightness detection system of fuel tank in claim 1 to 4, it is characterized in that: the described first pneumatic Test Switchboard (36) and the second pneumatic Test Switchboard (46) are hand sluice valve, described the first pressure detector A(35), the first pressure detector B(30), the second pressure detector A(45) and the second pressure detector B(40) be tensimeter.
8. according to any one described Small General Aircraft passenger cabin and the integrated air tightness detection system of fuel tank in claim 1 to 4, it is characterized in that: described source of the gas (1) also includes the gas source interface for being connected with external air source, and described gas source interface is connected with described shunt (2) by tracheae.
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Cited By (7)
| 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 |
| CN105711853A (en) * | 2014-12-03 | 2016-06-29 | 中国飞机强度研究所 | Three-valve linkage unloading device and method for cockpit inflation test |
| CN106197892A (en) * | 2016-07-30 | 2016-12-07 | 沧州惠邦重工装备制造有限公司 | A kind of Battery case air tightness detection equipment |
| CN107741292A (en) * | 2017-11-30 | 2018-02-27 | 闫晓红 | A kind of aircraft pressure checking device and its application method |
| 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 |
| 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 |
| 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 |
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Cited By (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 |
| CN105711853A (en) * | 2014-12-03 | 2016-06-29 | 中国飞机强度研究所 | Three-valve linkage unloading device and method for cockpit inflation test |
| CN106197892A (en) * | 2016-07-30 | 2016-12-07 | 沧州惠邦重工装备制造有限公司 | A kind of Battery case air tightness detection equipment |
| 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 |
| CN107741292A (en) * | 2017-11-30 | 2018-02-27 | 闫晓红 | A kind of aircraft pressure checking device and its application method |
| 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 |
| 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 |
| 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 |
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| CN103487219B (en) | 2015-10-28 |
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