阅读说明：本技术 飞机大翼油箱干舱漏油的氦气查漏工具及方法 (Helium leakage detection tool and method for oil leakage of dry cabin of large-wing oil tank of airplane ) 是由 冯改忠 袁涛 付喜朝 赵加坤 冷逢运 王盼方 于 2020-03-19 设计创作，主要内容包括：一种飞机大翼油箱干舱漏油的氦气法修理工具,包括盖板组件、4号滑轨堵盖、气压表盒、氦气瓶、直接氦气瓶气管、进气管、测压管和氦气检测仪。本发明/发明利用飞机大翼干舱的封闭性结构,拆除干舱接近口的盖板后,在飞机大翼前梁4号滑轨开口处处安装滑轨堵盖,在干舱接近口处安装盖板组件,并在盖板组件上设两个气嘴,一接氦气一接监测表。氦气瓶的高压氦气经过调压后通入密闭的干舱,在压力作用下,氦气通过干舱内的飞机大翼油箱外漏点,经过漏油路径进入到飞机大翼油箱的内漏点,在飞机大翼油箱内部用氦气检测仪确定内漏点的位置,从而根据厂家维护手册完成飞机大翼油箱燃油渗漏的修理。此工具制作简单,检测方便、快速、可靠。(A helium method repairing tool for oil leakage of a dry cabin of an airplane large-wing oil tank comprises a cover plate assembly, a No. 4 sliding rail plug cover, a barometer box, a helium tank, a direct helium tank air pipe, an air inlet pipe, a pressure measuring pipe and a helium detector. The invention/the invention utilizes the closed structure of the large-wing dry cabin of the airplane, after the cover plate of the approach opening of the dry cabin is removed, the slide rail blanking cover is arranged at the opening of the No. 4 slide rail of the front beam of the large wing of the airplane, the cover plate component is arranged at the approach opening of the dry cabin, two air nozzles are arranged on the cover plate component, one is connected with helium and the other is connected with a monitoring meter. High-pressure helium gas of the helium tank is introduced into the closed dry chamber after being subjected to pressure regulation, under the action of pressure, the helium gas enters the inner leakage point of the large-wing aircraft fuel tank through the outer leakage point of the large-wing aircraft fuel tank in the dry chamber through an oil leakage path, and the position of the inner leakage point is determined by a helium gas detector inside the large-wing aircraft fuel tank, so that the repair of fuel oil leakage of the large-wing aircraft fuel tank is completed according to a manufacturer maintenance manual. The tool is simple to manufacture, and convenient, rapid and reliable to detect.)

1. The utility model provides a helium leak hunting instrument of aircraft large wing oil tank dry chamber oil leak which characterized by includes:

a cover plate assembly (1) comprising: the cover plate is manufactured into an integral type or is fixedly superposed by a connecting piece, the cover plate (110) and a positioning block (107) are manufactured into an integral type or are fixedly superposed by the connecting piece, the positioning block is used for positioning corresponding to the shape of a dry cabin access opening (10) on a large-wing front beam (13) of an airplane, the cover plate is larger than the positioning block to form a sealing step, a sealing ring (108) is stuck on the step of the cover plate, and two screw rod sealing bases (111) are fixed on the; two groups of air holes corresponding to each other are formed in the cover plate and the positioning block, and an air inlet nozzle (105A) and a pressure measuring nozzle (105B) are arranged at two air holes in the top surface of the positioning block; two groups of through holes corresponding to each other are formed in the cover plate and the positioning block, the upper and lower parts of each group are provided with through holes, two through hole openings in the top surface of the positioning block are covered with fixing pieces (104) provided with elongated holes, two fixing screws (103) respectively penetrate through the elongated holes in the fixing pieces, the cover plate and the through holes in the positioning block and then are connected with screw sealing bases (111), and the top surface of the positioning block is further fixed with a handle (101) through a connecting piece and a screw cap (112;

a No. 4 slide rail opening blanking cover (2) to nylon makes, and the form is a board that is greater than in No. 4 slide rail opening (11), and its preceding, the centre at back all is equipped with the protruding portion, and preceding protruding portion (22) size corresponds No. 4 slide rail opening with the location, the step then is used for sealing, and the protruding portion convenience of back is handheld:

a barometer box (3) comprising: the split type cuboid box is composed of a front cover (308) and a rear cover (312) and is connected with a connecting piece and a screw base (310), two holes are formed in the front cover, a pressure monitoring meter (301) and a pressure adjusting meter (302) are respectively installed on the front cover, the pressure monitoring meter is connected with one end of a pressure measuring pipe (7) through a gas pipe connector (304), the pressure adjusting meter is installed on a first port of a gas pipe three-way connector (306), a second port of the gas pipe three-way connector is connected with one end of a gas inlet pipe (6) through a gas pipe (307) and a gas pipe connector, a third port of the gas pipe three-way connector is connected to a pressure adjusting valve (303) through a gas pipe, the pressure adjusting valve is connected to one end of a direct helium gas bottle gas pipe (5) through the gas pipe and the gas pipe connector, and the other;

a helium tank (4) supplying helium with a purity of 99.999% connected to the pressure regulating valve through a direct helium tank gas pipe;

a helium detector (9) for detecting the location of the internal leak from the interior of the aircraft's large wing structure fuel tank (8).

2. A helium leakage detection method for oil leakage of a dry cabin of an aircraft large-wing oil tank is characterized by comprising the following steps:

s1, removing an original cover plate of a dry cabin access opening (10) of a dry cabin on a front beam (13) of an airplane, coating sealant on a step (21) of a No. 4 sliding rail opening plug cover (2), extending the sealing sealant into the dry cabin access opening through a large-wing front beam of the airplane, positioning and aligning the No. 4 sliding rail opening (11) by using a positioning boss (22), and bonding the sliding rail plug cover to the No. 4 sliding rail opening through the step from the inside for sealing;

s2, a cover plate assembly 1 is arranged on the dry cabin approach port 10 to seal the dry cabin 12, two groups of through holes are formed in the cover plate assembly, and an air inlet nozzle (105A), a pressure measuring nozzle (105B) and a corresponding air pipe connector (112) are respectively arranged on the through holes;

s3, connecting an air inlet nozzle on the cover plate assembly into a barometer box through an air pipe connector and an air inlet pipe (6), and then connecting a helium tank air pipe (5) to a helium tank (4); a pressure regulating meter (302) and a pressure regulating valve (303) are arranged on a pipeline from the gas pipe of the helium tank to the helium tank;

s4, a pressure measuring air tap on the cover plate assembly is connected into a barometer box through an air pipe connector and a pressure measuring pipe (7) and finally connected to a pressure monitoring meter (301);

s5, enabling helium to reach a pressure regulating valve from a helium tank through a gas pipe, a gas pipe connector and a gas pipe of the helium tank directly, then connecting the helium to an air pressure regulating meter through a gas pipe and gas pipe three-way connector (306), and after the pressure is regulated, enabling the helium to reach an air inlet nozzle of a cover plate assembly (1) through the gas pipe, the gas pipe connector and a gas inlet pipe (6) until the helium is input into a large-wing sealed dry cabin (12) of the airplane;

meanwhile, the pressure monitoring meter is connected with a pressure measuring air tap on the cover plate assembly through an air pipe connector, an air pipe and a pressure measuring pipe, so that the pressure in the large-wing dry cabin of the airplane is monitored, and the damage to the structure of the airplane caused by overlarge pressure is prevented;

s6, helium in the dry cabin passes through an outer leakage point of the large-wing oil tank (8) and reaches the interior of the large-wing oil tank of the airplane through an oil leakage path, and the specific position of the inner leakage point is determined through a helium detector (9), so that the repair of fuel oil leakage of the large-wing oil tank of the airplane is completed according to a manufacturer maintenance manual.

Technical Field

The invention relates to a helium leakage detection tool for oil leakage of a dry cabin of an aircraft large-wing oil tank. The invention also relates to a helium leakage detection method for oil leakage of the dry cabin of the large-wing oil tank of the airplane by using the tool.

Background

As airlines operate aircraft age, tank leak failures become more frequent. Modern civil aircraft mostly adopt structural fuel tank design, and the aircraft is in flight, and the fuel tank must bear certain load. Under the loading condition, the reasons of material deformation and creep, fastener loosening, sealing material aging and deterioration can all lead to the aircraft to appear the fuel leakage trouble, thereby endangering flight safety. The leakage of the oil tank has the characteristics of emergencies, unpredictability, difficult repair and high repair rate, and often causes the stoppage and delay of the airplane, which is a great problem troubling the civil aviation. The key point of the oil tank leakage repair is to accurately find an inner leakage point (namely the actual oil leakage occurrence position inside the airplane oil tank), repair the inner leakage point and solve the leakage fault from the source. At present, no practical and effective solution is available in the industry, and basically, a blow-off method is adopted to search for a leak point in the oil tank so as to finish leak repair, wherein the repair time is 3-7 days.

The large-wing oil tank of the airplane is arranged in the large wing of the airplane, the engine is arranged below the large wing of the airplane, and the dry cabin is a cabin which is positioned in the upper area of the engine and is adjacent to the large-wing oil tank of the airplane, so that the temperature is higher, and a manufacturer designs the dry cabin without oil.

Closest prior art to the invention/invention: and detecting an inner leakage point of the large-wing oil tank of the airplane at the dry cabin position by using an air blowing method, and repairing the inner leakage point by using sealant.

2, product: the method for searching the inner leakage point by the air blowing method is to brush soap water in the large-wing oil tank, load high-pressure air on the outer leakage point to enable the outer leakage point to pass through an oil leakage path, and observe whether continuous bubbles are generated or not so as to determine the position of the inner leakage point.

3, composition and connection relation: a sealed bag is arranged around the outer leakage point, the air nozzle is arranged in the sealed bag, and high-pressure air is connected to the air nozzle through an air pipe.

4, the method: and searching and confirming the position of the outer leakage point, forming a sealing bag around the outer leakage point, placing an air nozzle into the sealing bag, and connecting high-pressure air to the air nozzle through an air pipe. The method comprises the steps of brushing soapy water in a large-wing oil tank, enabling high-pressure air to reach the inside of the large-wing oil tank through an oil leakage path under the action of pressure, observing whether continuous bubbles are generated or not, wherein the position where the bubbles are generated is the position of an inner leakage point, and repairing the inner leakage point by using a sealant.

5, comprising the steps of: confirming the position of an outer leakage point, making a sealing bag, connecting an air nozzle, brushing soapy water, connecting high-pressure air to enable the high-pressure air to reach the inside of the oil tank through an oil leakage path, searching and confirming an inner leakage point, and repairing the inner leakage point.

6, the prior art has the following defects: for oil leakage repair of an oil tank at a common position, the method is simple, quick and effective, but for a dry cabin position, the following defects exist: firstly, due to the structural design problem of a manufacturer, the interior of the dry cabin is difficult to access, and the interior of the dry cabin can only be accessed through a narrow access opening on the front beam, so that the outer leakage point is very difficult to confirm; and even if the outer leakage point is confirmed, the outer leakage point sealing bag cannot be manufactured, and the method for searching the inner leakage point by blowing is severely limited.

Summary of the invention

The invention/invention aims to solve the first technical problem of providing a helium leakage detection tool for oil leakage of a dry cabin of a large-wing oil tank of an airplane.

The invention provides a helium leakage detection method for oil leakage of an aircraft large-wing oil tank dry cabin by using the tool.

The helium leakage detection tool for detecting the leakage of the helium in the dry cabin of the large-wing oil tank of the airplane can effectively avoid the difficulty of difficulty in repairing the dry cabin, find and confirm the leakage point in the oil tank, improve the repairing efficiency and quality of the leaked oil, shorten the repairing period and reduce the repair rate.

To solve the first technical problem, the technical scheme adopted by the invention is as follows:

the utility model provides a helium leak hunting instrument of aircraft large wing oil tank dry chamber oil leak which characterized by includes:

a cover plate assembly 1, comprising: a cover plate 110 and a positioning block 107 which are overlapped are fixed by a connecting piece (or are integrated), the positioning block 107 is used for positioning corresponding to the shape of a dry cabin access opening 10 on a large-wing front beam 13 of an airplane, the cover plate 110 is larger than the positioning block 107 to form a sealing step, a sealing ring 108 is adhered on the step of the cover plate 110, and two screw rod sealing bases 111 are fixed on the bottom surface of the step by the connecting piece; two groups of air holes corresponding to each other are formed in the cover plate 110 and the positioning block 107, and an air inlet nozzle 105A and a pressure measuring nozzle 105B are arranged at two air holes in the top surface of the positioning block 107; two groups of through holes corresponding to each other are formed in the cover plate 110 and the positioning block 107, the two through holes in the top surface of the positioning block 107 are covered with a fixing plate 104 provided with a long hole, two fixing screws 103 are respectively connected with a screw sealing base 111 after penetrating through the long holes in the fixing plate 104, the cover plate 110 and the through holes in the positioning block 107, and the top surface of the positioning block 107 is further fixed with a handle 101 through a connecting piece and a nut 112;

a No. 4 slide rail opening blanking cover 2 is made with nylon, and the form is a board that is greater than No. 4 slide rail opening 11, and its preceding, the middle of back all is equipped with the protruding portion, and preceding protruding portion 22 size is corresponding to No. 4 slide rail opening 11 with the location, the step then is used for sealing, and the protruding portion of back is conveniently handheld:

a barometer box 3, comprising: the split type cuboid box is composed of a front cover 308 and a rear cover 312 and is connected with a connecting piece and a screw base 310, two holes are formed in the front cover 308, a pressure monitoring meter 301 and a pressure adjusting meter 302 are respectively installed on the two holes, the pressure monitoring meter 301 is connected with one end of a pressure measuring pipe 7 through a gas pipe connector 304, the pressure adjusting meter 302 is installed on a first port of the gas pipe three-way connector 306, a second port of the gas pipe three-way connector 306 is connected with one end of a gas inlet pipe 6 through a gas pipe 307 and a gas pipe connector, a third port of the gas pipe three-way connector 306 is connected to a pressure adjusting valve 303 through a gas pipe, the pressure adjusting valve 303 is connected to one end of a direct helium bottle gas pipe 5 through the gas pipe and the gas pipe connector, and the other ends;

a helium tank 4 for supplying helium with a purity of 99.999% and connected to the pressure regulating valve through a direct helium tank pipe 5;

and a helium detector 9 for detecting the position of the internal leak from the interior of the fuel tank of the aircraft wing structure.

To solve the second technical problem, the technical solution adopted by the present invention is as follows:

a helium leakage detection method for oil leakage of a dry cabin of an aircraft large-wing oil tank is characterized by comprising the following steps:

s1, removing an original cover plate of a dry cabin access opening 10 of a dry cabin 12 on a front beam 13 of an airplane, coating sealant on a step 21 of a No. 4 sliding rail opening blocking cover 2, positioning the sealing sealant through the dry cabin access opening 10 of the large-wing front beam of the airplane, aligning the sealing sealant with the No. 4 sliding rail opening 11 by using a positioning boss 22, and bonding the sliding rail blocking cover 2 to the No. 4 sliding rail opening from the inside of an oil tank 12 of the dry cabin through the step 21 for sealing;

s2, mounting a cover plate assembly 1 on the dry cabin approach port 10 to seal the dry cabin 12, wherein two groups of through holes are formed in the cover plate assembly, and an air inlet nozzle 105A, a pressure measuring nozzle 105B and a corresponding air pipe connector 112 are respectively mounted on the through holes;

s3, connecting an air inlet nozzle 105A on the cover plate assembly into a barometer box through an air pipe connector and an air inlet pipe 6, and then connecting a direct helium bottle air pipe 5 to a helium bottle 4; a pressure regulating meter 302 and a pressure regulating valve 303 are arranged on a pipeline from the helium tank gas pipe 5 to the helium tank 4;

s4, connecting a pressure measuring air tap 105B on the cover plate assembly into a barometer box through an air pipe connector and a pressure measuring pipe 7, and finally connecting the barometer box to a pressure monitoring meter 301;

s5, enabling helium to reach a pressure regulating valve 303 from a helium tank 4 through a direct helium tank air pipe 5, an air pipe connector and an air pipe, connecting the helium to an air pressure regulating meter 302 through an air pipe and air pipe three-way connector 306, and after the pressure is regulated, enabling the helium to reach an air inlet nozzle 105A of the cover plate assembly 1 through the air pipe, the air pipe connector and the air inlet pipe 6 until the helium is input into the airplane large-wing sealed dry cabin 12;

meanwhile, the pressure monitoring meter 301 is connected with a pressure measuring air tap 105B on the cover plate assembly 1 through an air pipe connector, an air pipe and a pressure measuring pipe 7, so that the pressure in the large-wing dry cabin 12 of the airplane is monitored, and the damage to the structure of the airplane caused by overlarge pressure is prevented;

s6, helium in the dry cabin 12 passes through an outer leakage point of the large-wing oil tank and reaches the interior of the large-wing oil tank of the airplane through an oil leakage path, and the specific position of the inner leakage point is determined through a helium detector 9, so that the repair of the fuel oil leakage of the large-wing oil tank of the airplane is completed according to a manufacturer maintenance manual.

The invention has the following beneficial effects:

(1) the invention/invention utilizes the closed structure of the aircraft large-wing dry cabin 12, after the cover plate of the approach port 10 of the aircraft large-wing dry cabin is removed, the slide rail blanking cover 2 is arranged at the slide rail opening 11 of the No. 4 slide rail opening of the aircraft large-wing front beam, the cover plate assembly 1 is arranged at the approach port 10 of the dry cabin, and two air nozzles 105 are arranged on the cover plate assembly, one is used for accessing helium with adjustable pressure, and the other is used for accessing the helium pressure monitoring meter 301 of the dry cabin. High-purity high-pressure helium in the helium tank 4 is introduced into the closed dry chamber 12 after pressure regulation, under the action of pressure, the helium passes through an outer leakage point of the airplane large-wing oil tank in the dry chamber 12 and enters an inner leakage point of the airplane large-wing oil tank 8 through an oil leakage path, and a helium detector 9 is used for determining the position of the inner leakage point inside the airplane large-wing oil tank 8, so that the repair of fuel oil leakage of the airplane large-wing oil tank is completed according to a manufacturer maintenance manual. The tool is simple to manufacture, and convenient, rapid and reliable to detect.

(2) The method/the device saves the time for searching the inner leakage point, reduces the time for stopping the airplane, reduces the maintenance cost of the airplane, improves the working efficiency, reduces the potential safety hazard, and provides a powerful guarantee for guaranteeing the continuous airworthiness of the airplane.

Drawings

The invention/invention is described in further detail below with reference to the figures and specific examples:

FIG. 1 is a schematic diagram of the components and connections of the helium repair tool of the present invention;

FIG. 2 is an exploded view of the helium repair tool cover plate assembly of the present invention;

FIG. 3 is a front view of the helium repair tool cover of the present invention;

FIG. 4 is a top view of the helium repair tool cover of the present invention;

FIG. 5 is a left side elevational view of the invention/helium repair tool cover plate erected;

FIG. 6 is a front view of the locating block of the helium repair tool of the present invention;

FIG. 7 is a top view of the locating block of the helium repair tool of the present invention;

FIG. 8 is a left side elevational view of the positioning block of the helium repair tool of the present invention;

FIG. 9 is a front view of the anchor tab of the helium repair tool of the present invention;

FIG. 10 is a top view of the anchor tab of the helium repair tool of the present invention;

FIG. 11 is a left side view of the anchor tab of the helium repair tool of the present invention;

FIG. 12 is a front view of the present invention/helium repair tool set screw;

FIG. 13 is a top view of the present invention/helium repair tool set screw;

FIG. 14 is a left side view of the present invention/helium repair tool set screw;

FIG. 15 is a perspective view of a slide rail blanking cap configuration of the helium repair tool of the present invention;

FIG. 16 is a front view of the slide rail closure of the helium repair tool of the present invention;

FIG. 17 is a top view of the helium repair tool slide rail closure of the present invention;

FIG. 18 is a left side view of the slide rail closure of the helium repair tool of the present invention;

FIG. 19 is an exploded view of the invention/helium repair tool barometer box;

FIG. 20 is a front elevational view of the front cover of the present invention/helium repair tool barometer cassette;

FIG. 21 is a top view of the front cover of the inventive/inventive helium repair tool barometer cassette;

FIG. 22 is a left side elevational view of the front cover of the inventive/inventive helium repair tool barometer cassette;

FIG. 23 is a front elevational view of the rear cover of the helium repair tool barometer cassette of the invention;

FIG. 24 is a top view of the rear cover of the helium repair tool barometer cassette of the invention;

FIG. 25 is a left side view of the rear cover of the helium repair tool barometer cassette of the invention;

FIG. 26 is an assembled perspective view of the helium repair tool cover plate assembly of the present invention;

fig. 27 is an assembled perspective view of the helium repair tool barometer cassette of the invention.

The reference numerals in the figures denote the following:

1-a cover plate assembly; a No. 2-4 sliding rail plug cover; 3-barometer box; 4-helium tank; 5-direct helium tank gas pipe; 6, an air inlet pipe; 7-piezometric tube; 8-large wing oil tank; 9-helium detector; 10-dry chamber access; the No. 11-4 sliding rail is provided with an opening; 12-dry chamber; 13-front beam;

101-a handle; 102-a screw; 103-fixing the screw rod; 104-a fixing sheet; 105A-an air inlet nozzle; 105B-pressure measuring air tap; 106-long rivet; 107-positioning blocks; 108-sealing ring; 109-short rivet; 110-a cover plate; 111-a base; 112-screw cap;

301-pressure monitoring meter; 302-pressure regulation gauge; 303-pressure regulating valve; 304-a gas tube connector; 306-trachea three-way joint; 307-trachea; 308-pressure gauge case front cover; 309-screw; 310-screw base; 311-case rivets; 312-pressure gauge case back cover.

Detailed Description

The helium repairing tool embodiment for oil leakage of the aircraft large wing oil tank dry cabin 12 shown in fig. 1-27 comprises a set of cover plate components 1, a No. 4 sliding rail plug 2, a barometer box 3, a helium tank 4, a direct helium tank air pipe 5, an air inlet pipe 6, a pressure measuring pipe 7 and a helium detector 9.

The cover plate component 1 comprises: a cover plate 110 and a positioning block 107 (or integrated) which are overlapped are fixed by a long connecting rivet 106, the positioning block 107 is used for positioning corresponding to the shape of a dry cabin access opening 10 on a large wing front beam 13 of an airplane, the cover plate 110 is larger than the positioning block 107 to form a sealing step, a sealing ring 108 is stuck on the step of the cover plate 110, and two screw rod sealing bases 111 are fixed on the bottom surface of the cover plate 110 by a short connecting rivet 109; two groups of air holes corresponding to each other are formed in the cover plate 110 and the positioning block 107, and an air inlet nozzle 105A and a pressure measuring nozzle 105B are arranged at two air holes in the top surface of the positioning block 107; two groups of through holes corresponding to each other are formed in the cover plate 110 and the positioning block 107, the two through holes in the top surface of the positioning block 107 are covered with a fixing plate 104 provided with a long hole, two fixing screws 103 are respectively connected with a screw sealing base 111 after penetrating through the long holes in the fixing plate 104, the cover plate 110 and the through holes in the positioning block 107, and the top surface of the positioning block 107 is further fixed with a handle 101 through a connecting piece screw 102 and a nut 112;

a No. 4 slide rail opening blanking cover 2 is made with nylon, and the form is a board that is greater than No. 4 slide rail opening 11, and its preceding, the middle of back all is equipped with the protruding portion, and preceding protruding portion 22 size is corresponding to No. 4 slide rail opening 11 with the location, the step then is used for sealing, and the protruding portion of back is conveniently handheld:

a barometer box 3, comprising: a split cuboid box which is composed of a front cover 308 and a rear cover 312 and is connected by a connecting piece screw 309 and a screw base 310, two holes are arranged on the front cover 308 and are respectively provided with a pressure monitoring meter 301 and a pressure adjusting meter 302, the pressure monitoring meter 301 is connected with one end of a piezometric tube 7 through a gas pipe joint 304, the pressure adjusting meter 302 is arranged on a first port of the gas pipe three-way joint 306, a second port of the gas pipe three-way joint 306 is connected with one end of a gas inlet pipe 6 through a gas pipe 307 and a gas pipe joint, a third port is connected to a pressure adjusting valve 303 through a gas pipe, the pressure adjusting valve 303 is connected with one end of a direct helium gas pipe 5 through a gas pipe and a gas pipe joint, and the other ends of the gas inlet pipe 6 and the piezometric tube 7 are;

a helium tank 4 for supplying helium with a purity of 99.999% and connected to the pressure regulating valve through a direct helium tank pipe 5;

and a helium detector 9 for detecting the position of the internal leak from the interior of the fuel tank of the aircraft wing structure.

The blanking cap 2 is used to seal the No. 4 slide rail opening 11 on the front beam 13. The No. 4 sliding rail opening 11 provides a stroke space for the folding and unfolding of the slat sliding rail of the airplane, and the opening needs to be sealed to seal the whole dry cabin 12. The dry cabin approach opening 10 through the front beam 13 is adhered with the sealant from the inside to the sliding rail opening 11 from No. 4 sliding rail block cover 2 to No. 4, when helium is introduced, the pressure inside the dry cabin 12 enables the sliding rail block cover 2 to be tightly pressed on the front beam 13, and the falling cannot be caused. No. 4 slide rail blanking cover material is nylon, and the quality is light, and convenient to use can not appear corroding, can not cause the damage to the aircraft structure. The size of the positioning part of the blocking cover is matched with the size of the No. 4 sliding rail opening 11 on the front beam 13, and the size of the sealing part is one circle larger than the size of the No. 4 sliding rail opening 11, so that the blocking cover can be tightly attached to the back inner part of the front beam 13 at the No. 4 sliding rail opening and cannot be separated from the No. 4 sliding rail opening 11 under the action of pressure. The rear part of the No. 4 sliding rail plug cover is provided with a convex part for manual operation, and the middle part of the sliding rail plug cover is hollowed out for reducing weight.

The helium pressure adjusting meter 302 on the barometer box 3 is used for displaying the helium pressure which is adjusted by the pressure adjusting valve 303 and then is introduced into the dry cabin 12, and the helium pressure monitoring meter 301 is used for monitoring the helium pressure in the dry cabin 12, so that the destructive damage of the aircraft structure caused by overlarge pressure is prevented.

The probe of the helium detector 9 is very sensitive, can detect helium with tiny concentration, can give an alarm when detecting helium, the instrument display value can change according to the change of the helium concentration, and the position corresponding to the probe is the position of a leakage point when the value reaches the maximum value. Helium passes through an outer leakage point in the dry chamber 12, reaches an inner leakage point in the oil tank of the aircraft large wing structure through a fuel leakage path, seeps out, and the position of the inner leakage point can be detected through a helium detector.

The helium leakage detection method for detecting the oil leakage of the dry cabin of the large-wing oil tank of the airplane by using the tool comprises the following steps of:

s1, removing an original cover plate of a dry cabin access opening 10 of a dry cabin 12 on a front beam 13 of an airplane, coating sealant on a step 21 of a No. 4 sliding rail opening blocking cover 2, positioning and aligning the No. 4 sliding rail opening 11 through the dry cabin access opening 10 of the front beam of the large wing of the airplane by using a positioning boss 22, and bonding the sliding rail blocking cover 2 to the No. 4 sliding rail opening for sealing through the step 21 from the inside of an oil tank 12 of the dry cabin;

s2, mounting a cover plate assembly 1 on the dry cabin approach port 10 to seal the dry cabin 12, wherein two groups of through holes are formed in the cover plate assembly, and an air inlet nozzle 105A, a pressure measuring nozzle 105B and a corresponding air pipe connector 112 are respectively mounted on the through holes;

s3, connecting an air inlet nozzle 105A on the cover plate assembly into a barometer box through an air pipe connector and an air inlet pipe 6, and then connecting a direct helium bottle air pipe 5 to a helium bottle 4; a pressure regulating meter 302 and a pressure regulating valve 303 are arranged on a pipeline from the helium tank gas pipe 5 to the helium tank 4;

s4, connecting a pressure measuring air tap 105B on the cover plate assembly into a barometer box through an air pipe connector and a pressure measuring pipe 7, and finally connecting the barometer box to a pressure monitoring meter 301;

s5, enabling helium to reach a pressure regulating valve 303 from a helium tank 4 through a direct helium tank air pipe 5, an air pipe connector and an air pipe, connecting the helium to an air pressure regulating meter 302 through an air pipe and air pipe three-way connector 306, and after the pressure is regulated, enabling the helium to reach an air inlet nozzle 105A of the cover plate assembly 1 through the air pipe, the air pipe connector and the air inlet pipe 6 until the helium is input into the airplane large-wing sealed dry cabin 12;

meanwhile, the pressure monitoring meter 301 is connected with a pressure measuring air tap 105B on the cover plate assembly 1 through an air pipe connector, an air pipe and a pressure measuring pipe 7, so that the pressure in the large-wing dry cabin 12 of the airplane is monitored, and the damage to the structure of the airplane caused by overlarge pressure is prevented;

s6, helium in the dry cabin 12 passes through an outer leakage point of the large-wing oil tank and reaches the interior of the large-wing oil tank of the airplane through an oil leakage path, and the specific position of the inner leakage point is determined through a helium detector 9, so that the repair of the fuel oil leakage of the large-wing oil tank of the airplane is completed according to a manufacturer maintenance manual.