KR101187563B1 - Fuel leak test device for wing fuel tank - Google Patents
Fuel leak test device for wing fuel tank Download PDFInfo
- Publication number
- KR101187563B1 KR101187563B1 KR20100089214A KR20100089214A KR101187563B1 KR 101187563 B1 KR101187563 B1 KR 101187563B1 KR 20100089214 A KR20100089214 A KR 20100089214A KR 20100089214 A KR20100089214 A KR 20100089214A KR 101187563 B1 KR101187563 B1 KR 101187563B1
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- South Korea
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- fuel tank
- pressure
- main wing
- gas
- wing fuel
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- General Physics & Mathematics (AREA)
- Examining Or Testing Airtightness (AREA)
- Aviation & Aerospace Engineering (AREA)
- Engineering & Computer Science (AREA)
- Biochemistry (AREA)
- Analytical Chemistry (AREA)
- General Health & Medical Sciences (AREA)
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Abstract
The main wing fuel tank oil leakage inspection apparatus according to the present invention includes a plurality of seals for shielding a plurality of holes communicating with the inside of the main wing fuel tank; A pressure tester coupled to any one of the plurality of holes, for selectively injecting gas into the main wing fuel tank, and detecting the leakage of the main wing fuel tank by displaying a pressure change of the gas in the main wing fuel tank for a set time; ; It is characterized in that it comprises a storage box to accommodate the plurality of closures and pressure tester inside and to carry and store.
Description
BACKGROUND OF THE INVENTION 1. Field of the Invention [0001] The present invention relates to a main fuel tank leakage test apparatus for inspecting the presence or absence of cracking or damage of a wing fuel tank of a fuselage body.
In general, the fuselage is regularly inspected for cracks and breaks. Among the many parts of the fuselage, the main wing fuel tank is a very important device for the safety of aircraft flight. And takes time.
In other words, the main wing fuel tank is inspected by moving the main wing separated from the fuselage to the test room and performing X-ray test and test liquid penetration test through the test test equipment module to read the fuel tank wear level and crack state. Is completed.
In addition, the inspection is completed, the fuel tank is moved to the assembly building with the main wing and reassembled in the fuselage to finish the crack and damage inspection of the fuel tank.
However, the inspection method of the fuel tank as described above has the following problems.
That is, it takes a long time to inspect, there is a problem that causes manpower waste due to the separation and assembly, transportation and inspection of the main wing.
In addition, there is a problem in that the efficiency of the inspection is deteriorated since a professional manpower for the X-ray test and the test liquid penetration test is required.
In addition, there is a problem that a lot of inspection cost is consumed because expensive inspection equipment is required.
An object of the present invention is to solve the above problems, the air is injected after sealing the inside of the main wing (Wing) fuel tank separated from the body, and the change of air pressure after a certain time is measured The present invention is to provide a main fuel oil leakage inspection device for inspecting fuel tanks for cracks and damages.
Another object of the present invention is to provide a main fuel oil leakage test apparatus which improves portability, improves test workability, eliminates expensive equipment and skilled personnel, and significantly shortens test time.
It is still another object of the present invention to provide a main fuel oil leakage inspection apparatus which enables accurate inspection at a low inspection cost.
The main wing fuel tank oil leakage inspection apparatus according to the present invention includes a plurality of seals for shielding a plurality of holes communicating with the inside of the main wing fuel tank; A pressure tester coupled to any one of the plurality of holes, for selectively injecting gas into the main wing fuel tank, and detecting the leakage of the main wing fuel tank by displaying a pressure change of the gas in the main wing fuel tank for a set time; ; It is characterized in that it comprises a storage box to accommodate the plurality of closures and pressure tester inside and to carry and store.
The pressure tester includes a sealing part inserted into the hole to selectively generate a sealing force, a gas guide part communicating with the inside of the main wing fuel tank through the sealing part, and guiding gas inflow into the main wing fuel tank, and the gas A shielding valve for selectively shielding the guide portion, a safety valve for measuring the pressure generated inside the gas guide portion and selectively opening to maintain the set pressure according to whether the set pressure is exceeded, and inside the main wing fuel tank through the seal portion It characterized in that it comprises a pressure gauge for measuring the pressure of.
The seal is formed of a material having an elastic restoring force, the elastic member is inserted into the hole, the pressing portion for penetrating the elastic member and pressing and compressing the elastic member according to the change of the separation distance, and the rotational force of the pressing portion It comprises a handle for providing.
The pressing unit is characterized in that the hole is sealed by expanding the outer diameter of the elastic member.
Leakage inspection method of the main wing fuel tank using the main wing fuel tank oil leak inspection apparatus according to the present invention, the air inlet installation step of shielding by inserting a seal in a plurality of holes of the main wing fuel tank separated from the body; A tester coupling step of coupling one side of the pressure tester for detecting leakage of the main wing fuel tank to any one of a plurality of holes, and gas injection for opening gas into the main wing fuel tank by opening a shielding valve provided at one side of the pressure tester. And a pressure measuring step of shielding the shielding valve and measuring a difference between the measured pressure and the set pressure of the pressure gauge after the set time elapses, and separating the device from the main fuel tank. It is done.
Before the gas injection step, an initialization step of initializing the pressure gauge and a pressure setting step of setting a set pressure of the safety valve are performed.
The pressure measuring step may be a process of determining whether the main wing fuel tank is leaked according to the difference between the measured pressure and the set pressure.
According to the main wing fuel tank oil leakage inspection device and the inspection method using the same, the air is injected after sealing the inside of the wing fuel tank separated from the fuselage, the air pressure after a certain time has elapsed It is possible to check the fuel tank for cracks and breakage by measuring the change of.
Therefore, there is an advantage that portability is increased, inspection workability is improved, expensive equipment and expert personnel are not required, and inspection time is significantly shortened.
In addition, there is an advantage that can be accurate inspection at a low inspection cost.
1 is a state of use of the main wing fuel tank leakage inspection apparatus according to the present invention.
Figure 2 is a plan view of the storage box is opened in the main fuel oil leakage test apparatus according to the present invention.
Figure 3 is a cross-sectional view showing in detail the closure of one configuration in the main wing fuel tank leakage inspection apparatus according to the present invention.
Figure 4 is a combined state diagram showing in detail a pressure tester as one component in the main wing fuel tank leakage test apparatus according to the present invention.
5 is a process flow chart illustrating a main wing fuel tank leakage inspection method using the main wing fuel tank leakage inspection apparatus according to the present invention.
Hereinafter, the configuration of the main wing fuel tank leakage inspection apparatus (hereinafter referred to as an inspection apparatus) according to the present invention will be described in detail with reference to FIGS. 1 and 2.
1 is a state diagram showing the use of the main fuel oil leakage tester according to the present invention, Figure 2 is a plan view of the storage box is opened in the main fuel oil leakage tester according to the present invention.
As shown in these drawings, the inspection apparatus according to the present invention includes: a plurality of
The
More specifically, since any one of the plurality of holes (Hole) is coupled to the
The
That is, if the pressure in the main wing fuel tank is lowered during the set time, the inside of the main wing fuel tank is sealed by a plurality of
Therefore, the
The
In addition, the
Therefore, the
Hereinafter, a detailed configuration of the
Figure 3 is a cross-sectional view showing in detail the
As shown in the drawing, the
More specifically, the
The
Therefore, the left end of the
The
To this end, the
The first pressing
Accordingly, the first pressing
The left side of the first pressing
The
The second pressing
That is, the second pressing
Therefore, when the first pressing
On the other hand, the
Hereinafter, the configuration of the
Figure 4 is a state diagram showing the details of the
As shown in the drawing, the
To this end, the
The sealing
Accordingly, the
The
The right side portion of the
A
The
Hereinafter, a method of inspecting leakage of the main wing fuel tank using the inspection apparatus configured as described above will be described with reference to FIGS. 1 to 5.
Figure 5 is a process flow chart showing the main wing fuel tank leakage inspection method using the main wing fuel tank leakage inspection apparatus according to the present invention.
First, in order to inspect the leakage of the main fuel fuel tank, a sealing opening installation step (S100) for inserting and shielding the
The seal opening installation step (S100) by inserting the sealing
When the seal installation step (S100) is completed, the outer surface of the
After the seal installation step (S100), the tester coupling step (S200) is carried out. The tester coupling step (S200) is a process of coupling the
When the tester coupling step (S200) is completed, the main wing fuel tank is disconnected from the outside as shown in FIG.
After the gas injection step (S500) is carried out. The gas injection step (S500) is a process of injecting gas into the main wing fuel tank by opening the shielding
At this time, the
That is, before the gas injection step S500, an initialization step S300 for initializing the pressure of the
Thus, even if gas is injected through the gas injection step S500, the
After the gas injection step (S500) is carried out a pressure measurement step (S600). The pressure measuring step (S600) should be a state in which the
That is, since the temperature of the inspection site is high, the gas injected into the main wing fuel tank may expand and increase the pressure, so that the
At the completion of the pressure measurement step (S600), the inspector reads the pressure of the
For example, if there is a difference between the pressure initialized before the gas injection step (S500) and a measured pressure measured after a predetermined time has elapsed, and the measured pressure is lower than the initial pressure, the gas inside the main wing fuel tank is discharged to the outside. It can be seen that cracks and breakage have occurred in the main fuel tank.
After the pressure measuring step (S600), the device separation step (S700) for separating the
When the device separation step (S700) is completed, the separated
The scope of the present invention is not limited to the above-exemplified embodiments, and many other modifications based on the present invention may be made by those skilled in the art within the above technical scope.
100.
140.
143.
145.
147.
200.
220.
240.
252.
300.
340.
380. Holding part F. frame
H. Hall S100. Sealing installation stage
S200. Tester coupling step S300. Initialization stage
S400. Pressure setting step S500. Gas injection stage
S600. Pressure measurement step S700. Device Separation Step
Claims (7)
A sealing part inserted into the hole and selectively generating a sealing force, a gas guide part for communicating gas inside the main wing fuel tank through the sealing part, and guiding gas inflow into the main wing fuel tank, and selectively shielding the gas guide part. A shielding valve to measure the pressure generated inside the gas guide unit, a safety valve selectively opened according to whether the set pressure is exceeded to maintain the set pressure, and a pressure inside the main fuel tank through the sealing part A pressure tester configured to consist of a pressure gauge to detect a leakage of the main fuel fuel tank by displaying a pressure change of the gas inside the main fuel fuel tank for a set time;
It is configured to include a storage box for carrying and storing the plurality of seals and pressure tester therein,
The closure is,
An elastic member formed of a material having an elastic restoring force and fitted into the hole;
A pressing unit penetrating the elastic member and compressing the elastic member by compressing the elastic member according to a change in the separation distance;
Main wing fuel tank leakage test apparatus, characterized in that comprises a handle for providing a rotational force of the pressing portion.
Priority Applications (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
KR20100089214A KR101187563B1 (en) | 2010-09-13 | 2010-09-13 | Fuel leak test device for wing fuel tank |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
KR20100089214A KR101187563B1 (en) | 2010-09-13 | 2010-09-13 | Fuel leak test device for wing fuel tank |
Publications (2)
Publication Number | Publication Date |
---|---|
KR20120027571A KR20120027571A (en) | 2012-03-22 |
KR101187563B1 true KR101187563B1 (en) | 2012-10-04 |
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Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
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KR20100089214A KR101187563B1 (en) | 2010-09-13 | 2010-09-13 | Fuel leak test device for wing fuel tank |
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Families Citing this family (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
CN106800096B (en) * | 2015-11-26 | 2019-06-28 | 中国飞行试验研究院 | Aircraft flammable liquid emission testing method |
KR102102172B1 (en) | 2018-09-19 | 2020-04-21 | 한국항공우주산업 주식회사 | Skin assembly of fuel tank |
Citations (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
KR200249998Y1 (en) * | 1998-12-08 | 2002-04-22 | 김형국 | Valve Leakage Tester |
JP2008309542A (en) * | 2007-06-13 | 2008-12-25 | Shinryo Corp | Fluid pressure tester |
-
2010
- 2010-09-13 KR KR20100089214A patent/KR101187563B1/en active IP Right Grant
Patent Citations (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
KR200249998Y1 (en) * | 1998-12-08 | 2002-04-22 | 김형국 | Valve Leakage Tester |
JP2008309542A (en) * | 2007-06-13 | 2008-12-25 | Shinryo Corp | Fluid pressure tester |
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KR20120027571A (en) | 2012-03-22 |
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