CN102729260A - Protection device for preventing adhesive for composite materials of aircrafts from being vitiated - Google Patents
Protection device for preventing adhesive for composite materials of aircrafts from being vitiated Download PDFInfo
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- CN102729260A CN102729260A CN2012102487643A CN201210248764A CN102729260A CN 102729260 A CN102729260 A CN 102729260A CN 2012102487643 A CN2012102487643 A CN 2012102487643A CN 201210248764 A CN201210248764 A CN 201210248764A CN 102729260 A CN102729260 A CN 102729260A
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- end bearing
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Abstract
The invention discloses a protection device for preventing an adhesive for composite materials of aircrafts from being vitiated, which comprises a shell, a front end cover, a plurality of locking devices, a sealing device and a pair of rubber gloves, wherein the shell is of a cuboid box structure of which the front end is provided with an opening, and the top surface of the shell is provided with a vacuum device interface, an inert gas device interface and a pressure control device; the sealing device is a rubber sealing ring, and is arranged at the opening of the front end of the shell; one end of the front end cover is hinged at the edge of the opening of the front end of the shell, an operating port is respectively formed on the two sides of the lower part of the front end cover, and each operating port is provided with an operating port cover; the plurality of locking devices are arranged at the joint of the opening of the front end of the shell and the front end cover; and the inner side of each operating port is provided with a rubber glove. The protection device disclosed by the invention can effectively reduce the time that a resin adhesive or a curing agent is in contact with the air, so that a problem that the resin adhesive has a chemical reaction because of meeting the air, and then a cross-linking phenomenon is produced untimely, thereby causing that the adhesive is vitiated and can not be used is avoided, therefore, the waste of the adhesive can be avoided, the application time of the resin adhesive can be effectively prolonged, and the cost can be reduced.
Description
Technical field
The invention belongs to the polymer composite processing technique field, particularly relate to the protective device that a kind of adhesive that is used to prevent resin glue, curing agent and formation lost efficacy.
Background technology
Along with the fast development of civil aviaton industry, require the civil aircraft structural material of 21 century to develop towards directions such as low-density, high strength, high tenacity, high temperature resistant, anti-oxidant, anticorrosive, antifatigue and stealthy wave absorbtion are good.In traditional aircraft manufacturing process; Needs use a large amount of rivets that metallic plate is coupled together and constitute some parts; Parts, lifting airscrew, hatch door and floor etc. such as the wallboard of airframe, integral tank, wing; A baby plane just needs up to ten thousand rivets, but will inevitably make the oeverall quality of aircraft heavier like this, and intensity is low.Adhesive is as a kind of macromolecular material; Fields such as packing, building, automobile, electronics, shoemaking, weaving, plastics, timber, health care, space flight and aviation, sea transport have been widely used in; If adopt to glued joint when making above-mentioned these parts and replace riveted joint; Can make that the quality of aircraft alleviates 20%, intensity improves 30%; Simultaneously obviously improve fatigue resistance and corrosion resistance, and have that the fuel-economizing speed-raising increases voyage, aeroperformance is good, technology is simple, reduce cost, sealed insulation, advantage such as smooth surface is attractive in appearance and stress distribution is even.Therefore; At present in the manufacture process of various military aircrafts, civil aircraft; Many positions all adopt adhesive to carry out bonding and sealing (like fuselage bulkhead, rear body covering, cowling, aileron covering, the leading edge of a wing, vertical fin and horizontal tail leading edge, wing root commutator segment, fuel tanker, aircraft window, passenger cabin and dividing plate, pressing plate, fireprotection layer, go out Ren Men, window, pore, pipeline, fuselage door and window, various case lid end face, vertical fin and rudder junction etc.), and the use occasion of adhesive is more and more.
Adhesive commonly used in the aircraft manufacturing process mainly contains: EP/ NBR stick, as rely on oneself-2, J-44-1, SY-13, J-40 and SY-18 etc.; 2. phenolic aldehyde/NBR stick; (be used for bonded metal, nonmetal structure spare like JX-4, J-04, XJ-9, SF-1, X-9, J-01; 20 ℃ of shear strength＞20MPa; 150 ℃ of shear strengths＞9MPa) and J-15 (20 ℃ of shear strength＞29.4MPa, 150 ℃ of shear strength＞15.7MPa, 250 ℃ of shear strengths＞8.0MPa) etc.; 3. ammonia phenolic aldehyde/NBR stick is like J-03 (20 ℃ of shear strength >=20MPa, 150 ℃ of shear strengths >=7MPa) etc.; 4. phenolic aldehyde/EP/ NBR stick is like J-42 etc.; 5. modification EP adhesive, as rely on oneself-4, SL-1 etc.; 6. EP/ gathers the sulphur adhesive, like SY-16 etc.; 7. phenolic aldehyde/acetal/EP adhesive is like SY-32 etc.; 8. phenolic aldehyde/acetal/organic silicon adhesive is as 204 etc.The selection that aviation sticks with glue agent should be looked its main performance and decide with different instructions for uses.
But no matter which kind of adhesive, its main component all contains unsettled reactive group.In addition; The adhesive overwhelming majority is made up of epoxide-resin glue, curing agent, and itself all belongs to the macromolecule quasi-oligomer these raw materials, and reactivity is high and unstable; And because active epoxy radicals is contained at the epoxy resin two ends; In case therefore ingress of air, oxidation reaction all can take place in adhesive, the SO that contains in the air simultaneously
2, CO, oxynitrides and be dissolved in salt in the steam pollutant that grades also there is certain influence in life-span of macromolecule adhesive; When these media get in macromolecule adhesive or its bond; May cause the chain rupture or the Acidity of Aikalinity reaction of macromolecule adhesive; And on bonding interface, also can cause, thereby cause the inefficacy of adhesive by the corrosion of adhesives.Therefore, at present resin glue commonly used all is placed on respectively in the different hermetically sealed cans with curing agent on the aircraft, mixes after opening jar during use, then uses again.In addition, the inefficacy that adhesive in use also can generating material, reason is following:
1) resin glue, curing agent are held jar time length that the back contacts with environment and when receiving extraneous unfavorable factor and influence, all can be made himself bond properties decline;
When 2) two kinds of materials of taking-up are configured, be exposed to the serviceability that airborne time length also can influence the adhesive of formation.To in the handbook of this Boeing and Air Passenger opening of adhesive all being had strict regulation jar setup time.
Owing to there is not special-purpose protector at present, therefore in actual production, some adhesive does not also just use up and had lost efficacy, and the said material major part still is import, and the result causes waste to a certain degree.
Summary of the invention
In order to address the above problem, the object of the present invention is to provide a kind of simple in structure, effective protective device that prevents the inefficacy of aircraft composite adhesive.
In order to achieve the above object, the rubber gloves that prevents protective device housing, drive end bearing bracket, a plurality of locking device, sealing device and a secondary isolated gas that aircraft composite adhesive lost efficacy provided by the invention; Its middle shell is the cuboid box-shaped structure that front end is formed with opening, and vacuum plant interface, inert gas installation interface and pressure control device are installed on the end face; Sealing device is a rubber seal, is arranged on the front opening of housing; One end of drive end bearing bracket is hinged on the front opening edge of housing, and the both sides, bottom are formed with a gathering hole respectively, and an operation flap is installed on each gathering hole; A plurality of locking device standoff distances are installed in the junction of housing front opening and drive end bearing bracket; The installed inside of each gathering hole has a rubber gloves on the drive end bearing bracket.
The top of described drive end bearing bracket also is equipped with an observation panel of being processed by transparent material.
Described housing and drive end bearing bracket adopt transparent organic glass or stainless steel material to process, and thickness is about 5mm.
The time of contact that the protective device that prevents that aircraft composite adhesive lost efficacy provided by the invention can effectively reduce resin glue or curing agent and air; Avoided resin glue because of running into air chemical reaction to take place, thereby produced crosslinkedly too early, the result lost efficacy adhesive and out of use problem; Therefore can avoid the waste of adhesive; And improved the service time of resin glue effectively, reduced cost, improved utilization rate greatly.
Description of drawings
Fig. 1 is the protective device STRUCTURE DECOMPOSITION sketch map that prevents that aircraft composite adhesive lost efficacy provided by the invention.
Fig. 2 is the protective device structural perspective that prevents that aircraft composite adhesive lost efficacy provided by the invention.
The specific embodiment
Below in conjunction with accompanying drawing and specific embodiment the protective device that prevents that aircraft composite adhesive lost efficacy provided by the invention is elaborated.
Like Fig. 1, shown in Figure 2, the protective device that prevents that aircraft composite adhesive lost efficacy provided by the invention comprises the rubber gloves 8 of housing 1, drive end bearing bracket 11, a plurality of locking device 5, sealing device 6 and a secondary isolated gas; Its middle shell 1 is formed with the cuboid box-shaped structure of opening for front end, and vacuum plant interface 2, inert gas installation interface 4 and pressure control device 3 are installed on the end face; Sealing device 6 is a rubber seal, is arranged on the front opening of housing 1; One end of drive end bearing bracket 11 is hinged on the front opening edge of housing 1, and the both sides, bottom are formed with a gathering hole 7 respectively, and an operation flap 10 is installed on each gathering hole 7; A plurality of locking device 5 standoff distances are installed in the junction of housing 1 front opening and drive end bearing bracket 11; The installed inside of each gathering hole 7 has a rubber gloves 8 on the drive end bearing bracket 11.
The top of described drive end bearing bracket 10 also is equipped with an observation panel 9 of being processed by transparent material.
Described housing 1 adopts transparent organic glass or stainless steel material to process with drive end bearing bracket 11, and thickness is about 5mm.
The protective device method for using that prevents that aircraft composite adhesive lost efficacy provided by the invention is set forth as follows at present:
A, at first the vacuum plant interface 2 on the housing 1, inert gas installation interface 4 are linked to each other with vacuum plant, inert gas installation through pipeline respectively by operating personnel;
B, open all locking devices 5 and open drive end bearing bracket 11, the gases in the rubber gloves 8 of isolated gas are tried one's best after the emptying locked operation flap 10;
C, a container is put into housing 1 inside left, afterwards resin glue jar or curing agent jar are put into housing 1 inner right side, accomplish back closed front end lid 11 and housing 1 and drive end bearing bracket 11 are locked with locking device 5;
D, open vacuum device begin to vacuumize; Treat to see that from pressure control device 3 the inner vacuum of housing 1 reaches-close during the setting value of 100KPa vacuum plant; Open valve, charge into inert gas through inert gas installation interface 4 to housing 1 inside, make this gas be full of the inside of housing 1 through pipeline as the gas cylinder of inert gas installation; Reach the balance of external and internal pressure, inert gas comprises: nitrogen (N
2), argon gas (Ar), helium (He), neon (Ne), krypton (Kr), xenon (Xe), be the monatomic of colourless, odorless, gaseous state;
E, open two operation flaps 10, then two hands are passed and put in the rubber gloves 8 from two gathering holes 7 respectively, to guarantee the cleaning of housing 1 internal environment; Open the lid of resin glue jar or curing agent jar, the right hand is picked up resin glue jar or curing agent jar, and left hand is picked up container; Slowly pour into resin glue or curing agent in the container; After taking out in right amount, put down resin glue jar or curing agent jar and cover tight lid, get into to prevent air; The operating process in this stage can be observed through observation panel 9 at any time;
F, hand is taken out from rubber gloves 8, is opened drive end bearing bracket 11, take out container and resin glue jar of having built or curing agent jar, at last with the resin glue in the container or curing agent rapidly and curing agent or resin glue mix can bring into use behind the formation adhesive.
Claims (3)
1. protective device that prevents that aircraft composite adhesive lost efficacy, it is characterized in that: the described protective device that prevents that aircraft composite adhesive lost efficacy comprises housing (1), drive end bearing bracket (11), a plurality of locking device (5), sealing device (6) and a secondary rubber gloves (8) that completely cuts off gas; Its middle shell (1) is formed with the cuboid box-shaped structure of opening for front end, and vacuum plant interface (2), inert gas installation interface (4) and pressure control device (3) are installed on the end face; Sealing device (6) is a rubber seal, is arranged on the front opening of housing (1); One end of drive end bearing bracket (11) is hinged on the front opening edge of housing (1), and the both sides, bottom are formed with a gathering hole (7) respectively, and an operation flap (10) is installed on each gathering hole (7); A plurality of locking devices (5) standoff distance is installed in the junction of housing (1) front opening and drive end bearing bracket (11); The installed inside that drive end bearing bracket (11) is gone up each gathering hole (7) has a rubber gloves (8).
2. the protective device that prevents that aircraft composite adhesive lost efficacy according to claim 1, it is characterized in that: the top of described drive end bearing bracket (10) also is equipped with an observation panel of being processed by transparent material (9).
3. the protective device that prevents that aircraft composite adhesive lost efficacy according to claim 1 is characterized in that: described housing (1) and drive end bearing bracket (11) adopt transparent organic glass or stainless steel material to process, and thickness is 5mm.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2012102487643A CN102729260A (en) | 2012-07-18 | 2012-07-18 | Protection device for preventing adhesive for composite materials of aircrafts from being vitiated |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2012102487643A CN102729260A (en) | 2012-07-18 | 2012-07-18 | Protection device for preventing adhesive for composite materials of aircrafts from being vitiated |
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| CN102729260A true CN102729260A (en) | 2012-10-17 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN2012102487643A Pending CN102729260A (en) | 2012-07-18 | 2012-07-18 | Protection device for preventing adhesive for composite materials of aircrafts from being vitiated |
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Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103831553A (en) * | 2014-03-12 | 2014-06-04 | 中国化学工程第六建设有限公司 | Welding protection tooling |
| CN105443755A (en) * | 2015-11-30 | 2016-03-30 | 中国航空工业集团公司沈阳飞机设计研究所 | Seal design method of separation face of aircraft structure |
| CN106425174A (en) * | 2015-08-12 | 2017-02-22 | 威尔特普技术株式会社 | Laser diode seal cap automatic welding device |
| CN108622649A (en) * | 2018-05-30 | 2018-10-09 | 格林美（武汉）城市矿产循环产业园开发有限公司 | A kind of battery pack feeding system |
| CN110509314A (en) * | 2019-08-16 | 2019-11-29 | 南京博森科技有限公司 | High-accuracy laboratory with constant temperature and constant humidity unit |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN2294108Y (en) * | 1997-05-23 | 1998-10-14 | 西南交通大学 | Vacuum compounding device |
| US20030070404A1 (en) * | 2001-10-12 | 2003-04-17 | Gerry Calabrese | Glove box contamination-proof mail handling |
| JP4169668B2 (en) * | 2003-09-04 | 2008-10-22 | 株式会社美和製作所 | Vacuum glove box |
| CN101406854A (en) * | 2008-11-06 | 2009-04-15 | 上海理工大学 | Vacuum environment control box for preparing nano fluid |
| CN102320046A (en) * | 2011-09-05 | 2012-01-18 | 太原科技大学 | The simple type glove box |
-
2012
- 2012-07-18 CN CN2012102487643A patent/CN102729260A/en active Pending
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN2294108Y (en) * | 1997-05-23 | 1998-10-14 | 西南交通大学 | Vacuum compounding device |
| US20030070404A1 (en) * | 2001-10-12 | 2003-04-17 | Gerry Calabrese | Glove box contamination-proof mail handling |
| JP4169668B2 (en) * | 2003-09-04 | 2008-10-22 | 株式会社美和製作所 | Vacuum glove box |
| CN101406854A (en) * | 2008-11-06 | 2009-04-15 | 上海理工大学 | Vacuum environment control box for preparing nano fluid |
| CN102320046A (en) * | 2011-09-05 | 2012-01-18 | 太原科技大学 | The simple type glove box |
Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103831553A (en) * | 2014-03-12 | 2014-06-04 | 中国化学工程第六建设有限公司 | Welding protection tooling |
| CN106425174A (en) * | 2015-08-12 | 2017-02-22 | 威尔特普技术株式会社 | Laser diode seal cap automatic welding device |
| CN105443755A (en) * | 2015-11-30 | 2016-03-30 | 中国航空工业集团公司沈阳飞机设计研究所 | Seal design method of separation face of aircraft structure |
| CN105443755B (en) * | 2015-11-30 | 2018-06-05 | 中国航空工业集团公司沈阳飞机设计研究所 | A kind of Seal Design method of aircaft configuration parting surface |
| CN108622649A (en) * | 2018-05-30 | 2018-10-09 | 格林美（武汉）城市矿产循环产业园开发有限公司 | A kind of battery pack feeding system |
| CN108622649B (en) * | 2018-05-30 | 2023-11-14 | 武汉动力电池再生技术有限公司 | Battery pack feeding system |
| CN110509314A (en) * | 2019-08-16 | 2019-11-29 | 南京博森科技有限公司 | High-accuracy laboratory with constant temperature and constant humidity unit |
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Application publication date: 20121017 |