CN105221748A - A kind of encapsulating method of aircraft integral tank - Google Patents
A kind of encapsulating method of aircraft integral tank Download PDFInfo
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- CN105221748A CN105221748A CN201510526197.7A CN201510526197A CN105221748A CN 105221748 A CN105221748 A CN 105221748A CN 201510526197 A CN201510526197 A CN 201510526197A CN 105221748 A CN105221748 A CN 105221748A
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- integral tank
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Abstract
The invention discloses a kind of encapsulating method of aircraft integral tank.The encapsulating method feature of described aircraft integral tank is: in wallboard type integral tank assembly process, reach the sealing of fit up gap by the mode that two component modified polysulfide sealant carries out faying surface, fillet seals, carry out the sealing of the detachable lid of fuel tank with low adhesive force modified polysulfide sealing compound.Usefulness of the present invention is: the sealant compositions used in integral tank assembly process is less, and good manufacturability is simple to operate, uses low adhesive force sealing compound to seal, have demolition and maintenance advantage easily at fuel tank detachable part.Fuel tank sealing has corrosion protection, good economy performance, advantage that sealing reliability is high.
Description
Technical field
The invention belongs to fuel tanker technical field of sealing technology, be specifically related to a kind of encapsulating method of aircraft integral tank.
Background technique
The military, civilian aircraft of modern high performance generally utilizes interior of aircraft structure space to arrange fuselage, integral wing tank, is used for increasing aircraft fuel oil reserves, to extend cruising time, increases aircraft range, improves flight performance.Therefore aircraft integral tank structure becomes indispensable constituent element in aeroplane structure design, and easy to use, maintenance, maximum military affairs, interests benefit can be obtained thus.
Seepage, the lighter of aircraft fuel oil can pollute, corrode aircaft configuration and system, seriously can fire together, cause great flying accident.Therefore, the corrosion protection sealing of aircraft integral tank is a vital problem, therefore must carry out meticulously careful structural design to aircraft integral tank, the sealing material of selectivity excellence, adopt strict construction process, to guarantee sealing effect optimization.
Wherein provide a kind of big-and-middle-sized transport airplane integral wing tank sealing corrosion etching method in CN101982247A, but its sealing compound XM22 component more (for Four composition) used, complex process, cure time longer (7-14 days), increase the unreliability of assembling, it adopts coating neutral soap water to solve an assembling difficult problem for fuel tank detachable part as isolating agent simultaneously, there is isolating agent easily to lose efficacy and cause the adhesion problems of detachable block, at present, require higher for the sealing of aircraft integral tank and life problems, said method cannot meet the seal request of current large aircraft integral tank.
Summary of the invention
The object of this invention is to provide a kind of encapsulating method of aircraft integral tank, to solve the shortcoming at least one place in background technique.
Technological scheme of the present invention is: a kind of encapsulating method of aircraft integral tank, it is characterized in that: in wallboard type integral tank assembly process, reach the sealing of fit up gap by the mode that two component modified polysulfide sealant carries out faying surface, fillet seals, carry out the sealing of the detachable lid of fuel tank with low adhesive force modified polysulfide sealing compound.
Alternatively, in wallboard type integral tank assembly process, needing sealing surface to be coated with bonding primary coat, to strengthen the cohesiveencess of sealing compound to ground before the two component modified polysulfide sealant of use.
Alternatively, scribble protective coat in two component modified polysulfide sealant surface brush, to reduce the erosion of microorganism by product to sealing compound, increase the service life.
Alternatively, described pair of component modified polysulfide sealant selects HM116, HM113, PR1422 or P/S870.
Alternatively, HM114 or PR1773 selected by described low adhesive force modified polysulfide sealing compound.
Alternatively, NJD-3 is selected in described bonding primary coat.
Alternatively, described protection protective coat selects BFJ-1650.
Alternatively, the wallboard internal surface of described wallboard type integral tank is coated with corrosion protection priming paint, to reach corrosion-resistant object.Described corrosion protection priming paint can select BFJ-1650.
The invention has the beneficial effects as follows: the sealant compositions used in integral tank assembly process is less, good manufacturability is simple to operate, uses low adhesive force sealing compound to seal, have demolition and maintenance advantage easily at fuel tank detachable part.Fuel tank sealing has corrosion protection, good economy performance, advantage that sealing reliability is high.
Embodiment
For making object of the invention process, technological scheme and advantage clearly, be further described in more detail to the technological scheme in the embodiment of the present invention below.Described embodiment is the present invention's part embodiment, instead of whole embodiments.Be intended to for explaining the present invention, and can not limitation of the present invention be interpreted as.Based on the embodiment in the present invention, those of ordinary skill in the art, not making the every other embodiment obtained under creative work prerequisite, belong to the scope of protection of the invention.Below in conjunction with specific embodiment, the present invention is described in detail.
Embodiment 1:
Fuel tank metal wallboard internal surface through sulfur acid anodizing sprays BFJ-1650 corrosion protection priming paint, thickness 30 ц m, drying at room temperature 1 day; When fuel tank assembles, during faying surface sealing, brush the primary coat of one deck NJD-3 bonding at the gluing position of spray coated corrosion protection priming paint, consumption is 75g/ ㎡, dries under physical environment; Within brushing NJD-3 bonds primary coat 8h, apply HM116 sealing compound, the weight proportion of HM116 sealing compound base cream and sulfuration cream is 100:10, afterwards by wallboard mould assembly; After wallboard mould assembly, at the outer blade coating HM113 sealing compound of wallboard and shaping, the weight proportion of HM113 sealing compound base cream and sulfuration cream is 100:10; Fastening piece installation is carried out within the sealing compound construction time; At fuel tank dismounting lid place, the low adhesive force sealing compound of coating HM114 seals, and the weight proportion of HM114 sealing compound base cream and sulfuration cream is 100:10, carries out sealing compound sulfuration afterwards, sulfuration 5 days under ambient temperature; After sealing compound complete cure, everyly brush BFJ-1650 protective coat with the encapsulant surface of fuel contacts integral tank is inner, after drying, carry out airtight oil pressure test for tightness.
Embodiment 2:
Fuel tank metal wallboard internal surface through sulfur acid anodizing sprays BFJ-1650 corrosion protection priming paint, thickness 25 ц m, drying at room temperature 1 day; When fuel tank assembles, during faying surface sealing, brush the primary coat of one deck NJD-3 bonding at the gluing position of spray coated corrosion protection priming paint, consumption is 70g/ ㎡, dries under physical environment; Within brushing NJD-3 bonds primary coat 8h, apply HM116 sealing compound, the weight proportion of HM116 sealing compound base cream and sulfuration cream is 100:8, afterwards by wallboard mould assembly; After wallboard mould assembly, at the outer blade coating HM113 sealing compound of wallboard and shaping, the weight proportion of HM113 sealing compound base cream and sulfuration cream is 100:8; Fastening piece installation is carried out within the sealing compound construction time; At fuel tank dismounting lid place, the low adhesive force sealing compound of coating HM114 seals, and the weight proportion of HM114 sealing compound base cream and sulfuration cream is 100:8, carries out sealing compound sulfuration afterwards, sulfuration 3 days under ambient temperature; After sealing compound complete cure, everyly brush BFJ-1650 protective coat with the encapsulant surface of fuel contacts integral tank is inner, after drying, carry out airtight oil pressure test for tightness.
Embodiment 3:
Fuel tank metal wallboard internal surface through sulfur acid anodizing sprays BFJ-1650 corrosion protection priming paint, thickness 35 ц m, drying at room temperature 1 day; When fuel tank assembles, during faying surface sealing, brush the primary coat of one deck NJD-3 bonding at the gluing position of spray coated corrosion protection priming paint, consumption is 80g/ ㎡, dries under physical environment; Within brushing NJD-3 bonds primary coat 8h, apply HM116 sealing compound, the weight proportion of HM116 sealing compound base cream and sulfuration cream is 100:12, afterwards by wallboard mould assembly; After wallboard mould assembly, at the outer blade coating HM113 sealing compound of wallboard and shaping, the weight proportion of HM113 sealing compound base cream and sulfuration cream is 100:12; Fastening piece installation is carried out within the sealing compound construction time; At fuel tank dismounting lid place, the low adhesive force sealing compound of coating HM114 seals, and the weight proportion of HM114 sealing compound base cream and sulfuration cream is 100:12, carries out sealing compound sulfuration afterwards, sulfuration 7 days under ambient temperature; After sealing compound complete cure, everyly brush BFJ-1650 protective coat with the encapsulant surface of fuel contacts integral tank is inner, after drying, carry out airtight oil pressure test for tightness.
Finally it is to be noted: above embodiment only in order to technological scheme of the present invention to be described, is not intended to limit.Although with reference to previous embodiment to invention has been detailed description, those of ordinary skill in the art is to be understood that: it still can be modified to the technological scheme described in foregoing embodiments, or carries out equivalent replacement to wherein portion of techniques feature; And these amendments or replacement, do not make the essence of appropriate technical solution depart from the spirit and scope of various embodiments of the present invention technological scheme.
Claims (8)
1. the encapsulating method of an aircraft integral tank, it is characterized in that: in wallboard type integral tank assembly process, reach the sealing of fit up gap by the mode that two component modified polysulfide sealant carries out faying surface, fillet seals, carry out the sealing of the detachable lid of fuel tank with low adhesive force modified polysulfide sealing compound.
2. the encapsulating method of aircraft integral tank according to claim 1, is characterized in that: needing sealing surface to be coated with bonding primary coat before the two component modified polysulfide sealant of use.
3. the encapsulating method of aircraft integral tank according to claim 1, is characterized in that: scribble protective coat in two component modified polysulfide sealant surface brush.
4. the encapsulating method of aircraft integral tank according to claim 1, is characterized in that: described pair of component modified polysulfide sealant selects HM116, HM113, PR1422 or P/S870.
5. the encapsulating method of aircraft integral tank according to claim 1, is characterized in that: HM114 or PR1773 selected by described low adhesive force modified polysulfide sealing compound.
6. the encapsulating method of aircraft integral tank according to claim 2, is characterized in that: NJD-3 is selected in described bonding primary coat.
7. the encapsulating method of aircraft integral tank according to claim 3, is characterized in that: described protective coat selects BFJ-1650.
8. the encapsulating method of aircraft integral tank according to claim 1, is characterized in that: the wallboard internal surface of described wallboard type integral tank is coated with corrosion protection priming paint.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510526197.7A CN105221748A (en) | 2015-08-25 | 2015-08-25 | A kind of encapsulating method of aircraft integral tank |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510526197.7A CN105221748A (en) | 2015-08-25 | 2015-08-25 | A kind of encapsulating method of aircraft integral tank |
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| CN105221748A true CN105221748A (en) | 2016-01-06 |
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| CN201510526197.7A Pending CN105221748A (en) | 2015-08-25 | 2015-08-25 | A kind of encapsulating method of aircraft integral tank |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106043717A (en) * | 2016-05-31 | 2016-10-26 | 中国航空工业集团公司西安飞机设计研究所 | Airplane oil tank opening cap sealing method |
| CN108180285A (en) * | 2017-12-29 | 2018-06-19 | 西安飞机工业（集团）天成航空构件有限责任公司 | A kind of encapsulating method of ground plane experiment fuel tank |
Citations (6)
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|---|---|---|---|---|
| CN101982247A (en) * | 2010-11-15 | 2011-03-02 | 陕西飞机工业（集团）有限公司 | Method for sealing and preventing integral wing tank of large-medium transport from corrosion |
| CN202138536U (en) * | 2011-06-03 | 2012-02-08 | 哈尔滨飞机工业集团有限责任公司 | Integral wing oil tank sealing structure |
| CN103555264A (en) * | 2013-10-11 | 2014-02-05 | 中国航空工业集团公司北京航空材料研究院 | High peeling strength polysulfide sealant and sealing method |
| US20150041592A1 (en) * | 2012-03-26 | 2015-02-12 | Mitsubishi Heavy Industries, Ltd. | Fuel tank, main wing, aircraft fuselage, aircraft, and mobile body |
| CN104369857A (en) * | 2014-10-15 | 2015-02-25 | 中航飞机股份有限公司西安飞机分公司 | Whole oil tank structure of airplane |
| CN104443347A (en) * | 2014-11-19 | 2015-03-25 | 中国航空工业集团公司沈阳飞机设计研究所 | Design method for sealing aircraft skin and skeleton structure |
-
2015
- 2015-08-25 CN CN201510526197.7A patent/CN105221748A/en active Pending
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101982247A (en) * | 2010-11-15 | 2011-03-02 | 陕西飞机工业（集团）有限公司 | Method for sealing and preventing integral wing tank of large-medium transport from corrosion |
| CN202138536U (en) * | 2011-06-03 | 2012-02-08 | 哈尔滨飞机工业集团有限责任公司 | Integral wing oil tank sealing structure |
| US20150041592A1 (en) * | 2012-03-26 | 2015-02-12 | Mitsubishi Heavy Industries, Ltd. | Fuel tank, main wing, aircraft fuselage, aircraft, and mobile body |
| CN103555264A (en) * | 2013-10-11 | 2014-02-05 | 中国航空工业集团公司北京航空材料研究院 | High peeling strength polysulfide sealant and sealing method |
| CN104369857A (en) * | 2014-10-15 | 2015-02-25 | 中航飞机股份有限公司西安飞机分公司 | Whole oil tank structure of airplane |
| CN104443347A (en) * | 2014-11-19 | 2015-03-25 | 中国航空工业集团公司沈阳飞机设计研究所 | Design method for sealing aircraft skin and skeleton structure |
Non-Patent Citations (1)
| Title |
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| 胡琳: "飞机整体油箱密封剂分析", 《民用飞机设计与研究》 * |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106043717A (en) * | 2016-05-31 | 2016-10-26 | 中国航空工业集团公司西安飞机设计研究所 | Airplane oil tank opening cap sealing method |
| CN108180285A (en) * | 2017-12-29 | 2018-06-19 | 西安飞机工业（集团）天成航空构件有限责任公司 | A kind of encapsulating method of ground plane experiment fuel tank |
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Application publication date: 20160106 |