CN105584744A - Method for vacuum film negative-pressure glue reverse permeation repair of integral fuel tank of airplane - Google Patents
Method for vacuum film negative-pressure glue reverse permeation repair of integral fuel tank of airplane Download PDFInfo
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- CN105584744A CN105584744A CN201410565597.4A CN201410565597A CN105584744A CN 105584744 A CN105584744 A CN 105584744A CN 201410565597 A CN201410565597 A CN 201410565597A CN 105584744 A CN105584744 A CN 105584744A
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- sealing
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Abstract
Disclosed is a method for vacuum film negative-pressure glue reverse permeation repair of an integral fuel tank of an airplane. The method is characterized by comprising the following steps that (1) a standard vacuum pumping nozzle is installed on the proper portion of a vacuum film; (2) non-drying sealing putty is attached to the periphery of the vacuum film; (3) the interior of the integral fuel tank to be repaired is cleaned and brushed with sealing glue; (4) the vacuum film adheres to the glued region, and the non-drying putty on the periphery of the vacuum film is compacted, so that a vacuum cavity is formed, and the situation that a pipe nozzle portion and a non-drying putty layer do not leak air is ensured; and (5) the vacuum cavity is vacuumized, and the vacuum state is kept until the sealing glue solidifies. Furthermore, glue absorption belts are arranged in the vacuum film. Due to the facts that the vacuum film is used for covering the integral fuel tank, and the sealing glue permeates into leaking gaps, air holes and micro-holes in the reverse direction through the negative pressure, the purpose of sealing repair is achieved. The efficiency and the reliability of sealing repair of the integral fuel tank are improved, and the method has quite high popularization and application value in the fields of aviation, spaceflight, automobiles, ships and the like.
Description
Technical field
The present invention relates to fuel tanker process technology, relate to especially a kind of aircraft integral tank vacuum diaphragm negative pressure reverse strike-through method for repairing and mending.
Background technology
In manufacture fields such as Aeronautics and Astronautics, automobile, boats and ships, need to use in a large number various seal cases (tank), except fuel tank, also have many cavity, casing and tank bodies that provide compressed air, hydraulic pressure wet goods to seal. These casings manufacture, use in often there is leakage failure, the method overwhelming majority of repairing be adopt rubber-like sealant or other adhesive are brushed in internal leakage source, blade coating repair. During integral tank is repaired, elevation angle brushing fluid sealant or other adhesive seal while repairing, fluid sealant is conventionally due to gravity factor drippage or trickling, cannot form closely knit a, streamline, face is repaired in level and smooth sealing, can not effectively block internal flaw, fluid sealant brushing or blade coating mode, because inevitable meeting in fluid sealant configuration, construction is with bubble, these bubbles, trachoma cannot be eliminated again in construction, for repairing, can form the defects such as secondary trachoma, pore; For complicated region, the elevation angle, because causing the fluid sealant of blade coating, gravity factor trickles or drippage, and the source of leaks such as the pore causing, trachoma, micropore cannot cover by repaired glue-line completely, and repair efficiency is poor and cannot find reason. At some in particular cases, even occur that repeatedly brushing, blade coating all cannot thoroughly solve repairing problem.
Summary of the invention
For solving the problems of the technologies described above, the invention provides a kind of aircraft integral tank vacuum diaphragm negative pressure reverse strike-through method for repairing and mending, adopt the bleed vacuum diaphragm of ozzle of band fluid sealant oppositely to be infiltrated leak hole to reach sealing repairing effect, the method highly versatile, technical thought and process that sealing effectiveness is good to the sealant layer pressurization of brushing.
A kind of aircraft integral tank vacuum diaphragm negative pressure reverse strike-through method for repairing and mending, is characterized in that: comprise the following steps:
1) vacuumize mouth in standard of installation of vacuum diaphragm;
2) stick a circle non-drying sealant along vacuum diaphragm surrounding;
3) the integral tank inside for the treatment of repairing is cleaned and brushing fluid sealant;
4) then this vacuum diaphragm is pasted in gluing region, the compacting of periphery non-drying putty is made to become a vacuum cavity, ensure that ozzle mouth place and not dry putty layer are air tight;
5) this vacuum cavity is vacuumized, keep vacuum, until sealing glue solidifying.
Further, suction adhesive tape is set in described vacuum diaphragm.
The present invention is owing to taking vacuum diaphragm to cover, and fluid sealant, reaches sealing and repairs object to infiltrating in the gap, pore, micropore of leaking through negative pressure reverse. The present invention improves efficiency and the reliability that integral tank sealing is repaired, and has application value very widely in fields such as Aeronautics and Astronautics, automobile, boats and ships.
Detailed description of the invention
The present invention adopts the bleed vacuum diaphragm of ozzle of band fluid sealant oppositely to be infiltrated leak hole to reach sealing repairing effect to the sealant layer pressurization of brushing, technical scheme as following steps: in the proper site of vacuum diaphragm, a standard is installed and vacuumizes mouth, position is conducive to again inner air fully to be extracted out not affect repairing sealant layer. Under indivedual complex situations, for guarantee air is fully extracted out, can in vacuum diaphragm, proper site increase several suction adhesive tapes as the air duct vacuumizing. Stick a circle non-drying sealant along vacuum diaphragm surrounding. Treat the integral tank inside of repairing and clean, brushing fluid sealant, then pastes this vacuum diaphragm in gluing region, and the compacting of periphery non-drying putty is made to become a vacuum cavity, ensures that ozzle mouth place, dry putty layer etc. are air tight. This vacuum cavity is vacuumized, keep vacuum, until sealing glue solidifying. Vacuum diaphragm is the common airtight plastic sheeting of flexibility, and area is suitably greater than brush coating to be repaired region.
Compared with the prior art, the present invention is owing to taking vacuum diaphragm to cover, and fluid sealant, reaches sealing and repairs object to infiltrating in the gap, pore, micropore of leaking through negative pressure reverse.
The present invention can improve efficiency and the reliability that integral tank sealing is repaired greatly, has application value very widely in fields such as Aeronautics and Astronautics, automobile, boats and ships.
Technique scheme has only embodied the optimal technical scheme of technical solution of the present invention, and those skilled in the art have all embodied principle of the present invention to some variations that wherein some part may be made, within belonging to protection scope of the present invention.
Claims (2)
1. an aircraft integral tank vacuum diaphragm negative pressure reverse strike-through method for repairing and mending, is characterized in that: comprise the following steps:
1) vacuumize mouth in standard of installation of vacuum diaphragm;
2) stick a circle non-drying sealant along vacuum diaphragm surrounding;
3) the integral tank inside for the treatment of repairing is cleaned and brushing fluid sealant;
4) then this vacuum diaphragm is pasted in gluing region, the compacting of periphery non-drying putty is made to become a vacuum cavity, ensure that ozzle mouth place and not dry putty layer are air tight;
5) this vacuum cavity is vacuumized, keep vacuum, until sealing glue solidifying.
2. method according to claim 1, is characterized in that: suction adhesive tape is set in described vacuum diaphragm.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410565597.4A CN105584744A (en) | 2014-10-22 | 2014-10-22 | Method for vacuum film negative-pressure glue reverse permeation repair of integral fuel tank of airplane |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410565597.4A CN105584744A (en) | 2014-10-22 | 2014-10-22 | Method for vacuum film negative-pressure glue reverse permeation repair of integral fuel tank of airplane |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN105584744A true CN105584744A (en) | 2016-05-18 |
Family
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201410565597.4A Pending CN105584744A (en) | 2014-10-22 | 2014-10-22 | Method for vacuum film negative-pressure glue reverse permeation repair of integral fuel tank of airplane |
Country Status (1)
| Country | Link |
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| CN (1) | CN105584744A (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107870068A (en) * | 2016-09-22 | 2018-04-03 | 成都飞机工业（集团）有限责任公司 | A kind of method of non-closed structure rapid vacuumizing |
| CN108221949A (en) * | 2018-02-02 | 2018-06-29 | 上海港湾基础建设（集团）股份有限公司 | Double glue mend film device and method to a kind of vacuum preloading under water |
| CN110667014A (en) * | 2019-09-19 | 2020-01-10 | 哈尔滨飞机工业集团有限责任公司 | Method for repairing air leakage defect of composite material tool |
Citations (6)
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|---|---|---|---|---|
| US3972111A (en) * | 1975-03-13 | 1976-08-03 | Mcdonnell Douglas Corporation | Surface preparation method |
| CN2709150Y (en) * | 2004-06-15 | 2005-07-13 | 中国人民解放军空军装备研究院航空装备研究所 | Portable composite material hot patching device |
| CN1760019A (en) * | 2005-10-03 | 2006-04-19 | 许传金 | Method for repairing damage of vehcile body and parts made from glass fiber reinforced plastic |
| CN101434816A (en) * | 2008-12-15 | 2009-05-20 | 江西洪都航空工业集团有限责任公司 | Vacuum pumping micro-leak repair method |
| CN101936442A (en) * | 2009-07-01 | 2011-01-05 | 北京安科管道工程科技有限公司 | Method for mending steel pipeline polyolefin anticorrosive layer and product obtained by same |
| CN103350552A (en) * | 2013-07-03 | 2013-10-16 | 常熟市金亿复合材料有限公司 | Glass fiber reinforced plastic carriage composite board repair process |
-
2014
- 2014-10-22 CN CN201410565597.4A patent/CN105584744A/en active Pending
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3972111A (en) * | 1975-03-13 | 1976-08-03 | Mcdonnell Douglas Corporation | Surface preparation method |
| CN2709150Y (en) * | 2004-06-15 | 2005-07-13 | 中国人民解放军空军装备研究院航空装备研究所 | Portable composite material hot patching device |
| CN1760019A (en) * | 2005-10-03 | 2006-04-19 | 许传金 | Method for repairing damage of vehcile body and parts made from glass fiber reinforced plastic |
| CN101434816A (en) * | 2008-12-15 | 2009-05-20 | 江西洪都航空工业集团有限责任公司 | Vacuum pumping micro-leak repair method |
| CN101936442A (en) * | 2009-07-01 | 2011-01-05 | 北京安科管道工程科技有限公司 | Method for mending steel pipeline polyolefin anticorrosive layer and product obtained by same |
| CN103350552A (en) * | 2013-07-03 | 2013-10-16 | 常熟市金亿复合材料有限公司 | Glass fiber reinforced plastic carriage composite board repair process |
Non-Patent Citations (1)
| Title |
|---|
| 刘麟瑞，高树生: "《新编建筑工程常用材料手册》", 31 August 1993 * |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107870068A (en) * | 2016-09-22 | 2018-04-03 | 成都飞机工业（集团）有限责任公司 | A kind of method of non-closed structure rapid vacuumizing |
| CN108221949A (en) * | 2018-02-02 | 2018-06-29 | 上海港湾基础建设（集团）股份有限公司 | Double glue mend film device and method to a kind of vacuum preloading under water |
| CN108221949B (en) * | 2018-02-02 | 2023-12-19 | 上海港湾基础建设（集团）股份有限公司 | Vacuum pre-pressing underwater double-adhesive film supplementing device and method |
| CN110667014A (en) * | 2019-09-19 | 2020-01-10 | 哈尔滨飞机工业集团有限责任公司 | Method for repairing air leakage defect of composite material tool |
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Application publication date: 20160518 |