CN104443347A - Design method for sealing aircraft skin and skeleton structure - Google Patents
Design method for sealing aircraft skin and skeleton structure Download PDFInfo
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- CN104443347A CN104443347A CN201410667967.5A CN201410667967A CN104443347A CN 104443347 A CN104443347 A CN 104443347A CN 201410667967 A CN201410667967 A CN 201410667967A CN 104443347 A CN104443347 A CN 104443347A
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Abstract
The invention belongs to the technical field of advanced aeronautical sealing and in particular relates to a design method for sealing an aircraft skin and a skeleton structure. The method comprises the following steps: step 1, preparing for sealing, namely (1) cleaning, and (2) coating first coat; and step 2, (1) inseam sealing, (2) fillet sealing, (3) surface sealing, and (4) fastener sealing. According to the method disclosed by the invention, four combined sealing forms of the aircraft skin and the skeleton structure are adopted, sealing areas cover the joint part of the skin and the skeleton, the joint of a covering cap and a covering frame, the joint of the covering cap and a fastener, and the like, a phenomenon that rainwater, salt mist and other corrosive media flow into or permeate into the body from gaps and overlap parts can be effectively avoided, and the sealing effect is obvious.
Description
Technical field
The invention belongs to the advanced technical field of sealing technology of aviation, be specifically related to a kind of method of designing sealed for aircraft skin and skeleton structure.
Background technology
Aircraft is in use subject to the corrosion of external environment, as salt fog, damp and hot etc.Therefore need to take strict corrosion protection steps, prevent housing construction from corroding, ensure aircaft configuration service life.
Rational sealing can prevent structure interval, gap, hole, cavity, groove, face of joint etc. from entering and building up moisture, salt fog and other Korrosionsmedium effectively.The combination of the detailed design technology such as sealing and draining, ventilation, surfacecti proteon, will make the corrosion of aircaft configuration obtain actv. Prevention and controls.Conventional seals design has only carried out sealing protection to airframe important feature position, as fuel oil tank, airtight cabin and equipment compartment etc., does not carry out effective sealing design to other versions.
Summary of the invention
The present invention seeks to: for Problems existing in above-mentioned background technology, propose a kind of method of designing sealed for aircraft skin and skeleton structure.
Technical scheme of the present invention is: a kind of for aircraft skin and skeleton structure Seal Design method, it is characterized in that: described method adopts advanced modified polysulfide aquaseal to carry out sealing protection to aircraft, and described method comprises:
Step one, prepares before sealing:
1) clean: dip in No. 120 gasoline with clean Kanakin and clean covering and skeleton surface, hang (10 ~ 15) min; Dip in acetone with clean Kanakin again and clean above-mentioned zone, hang (10 ~ 15) min; Cleaning area at least exceeds region 30mm to be sealed;
2) primary coat is coated with: dip in bonding primary coat with clean Kanakin, be coated on region to be sealed, at least hang 15min, primary coat the area of application at least exceeds region 15mm to be sealed;
Step 2, sealing structure:
1) sealing in seam:
1.1) aquaseal is coated with: region coating blade coating type aquaseal to be sealed, aquaseal uniformly continous, thickness (0.5 ~ 0.8) mm;
1.2) assemble: adopt fastener to be linked and packed to covering and skeleton, ensure that aquaseal is evenly extruded in seam;
2) fillet sealing:
Adopt blade coating type modified polysulfide aquaseal to carry out fillet to covering and skeleton inside face edge, process fillet place aquaseal, make it smooth transition and become band, section form is triangle;
3) face seal:
Adopt brush-on-type modified polysulfide aquaseal to carry out brush application to covering and skeleton inside face fastener end, brush twice, cover first pass completely second time, be often one all over interval time and do not glue the phase, construction rear surface is smooth;
4) fastener sealing:
Fastener dip-and-scrap painting type modified polysulfide aquaseal hygrometric state assembles, and connecting bore is played to the effect of sealing, isolation and protection, reduces and delay the generation of fastener connection section position corrosion.
Advantage of the present invention: by adopting four kinds of combination sealing forms to aircraft skin and skeleton structure, sealing area covers covering and skeleton connecting portion, between lid and mouth frame and fastener junction etc., can effectively avoid the corrosive medium such as rainwater, salt fog from gap, overlapping part flow into or infiltrate internal body, significant sealing affection.
Accompanying drawing explanation
Fig. 1 is aircraft wing the 2nd, 3 joint of hanging point Seal Design;
Wherein: sealing in the sealing of 1-fillet, 2-seam, the sealing of 3-fastener, 4-face seal.
Detailed description of the invention
Below in conjunction with accompanying drawing, the specific embodiment of the present invention is described further.
The present invention is a kind of for aircraft skin and skeleton structure Seal Design method, comprising:
One, leakproofing material
Adopt advanced modified polysulfide aquaseal to carry out sealing protection to aircraft, this material has outstanding resistance to elevated temperatures, and maximum operation (service) temperature reaches 150 DEG C, higher at sour environment stability inferior, all can realize good bonding with multiple material.
Two, prepare before sealing
Cleaning: dip in No. 120 gasoline with clean Kanakin and clean covering and skeleton surface, hang (10 ~ 15) min; Dip in acetone with clean Kanakin again and clean above-mentioned zone, hang (10 ~ 15) min.Cleaning area at least exceeds region 30mm to be sealed.
Be coated with primary coat: dip in bonding primary coat with clean Kanakin, be coated on region to be sealed, at least hang 15min, primary coat the area of application at least exceeds region 15mm to be sealed.
Three, sealing structure
1. sealing in seam:
1) aquaseal is coated with: region coating blade coating type aquaseal to be sealed, aquaseal uniformly continous, thickness (0.5 ~ 0.8) mm;
2) assemble: adopt fastener to be linked and packed to covering and skeleton, ensure that aquaseal is evenly extruded in seam.
2. fillet sealing:
Adopt blade coating type modified polysulfide aquaseal to carry out fillet to covering and skeleton inside face edge, process fillet place aquaseal, make it smooth transition and become band, section form is triangle.
3. face seal:
Adopt brush-on-type modified polysulfide aquaseal to carry out brush application to covering and skeleton inside face fastener end, brush twice, cover first pass completely second time, be often one all over interval time and do not glue the phase, construction rear surface is smooth.
4. fastener sealing:
Fastener dip-and-scrap painting type modified polysulfide aquaseal hygrometric state assembles, and connecting bore is played to the effect of sealing, isolation and protection, reduces and delay the generation of fastener connection section position corrosion.
See Fig. 1, it is aircraft wing the 2nd, 3 joint of hanging point Seal Design; Wherein, 1 be fillet sealing, 2 be sealing in seam, 3 seal, 4 be face seal for fastener.
Claims (1)
1. for aircraft skin and a skeleton structure Seal Design method, it is characterized in that: described method adopts advanced modified polysulfide aquaseal to carry out sealing protection to aircraft, and described method comprises:
Step one, prepares before sealing:
1) clean: dip in No. 120 gasoline with clean Kanakin and clean covering and skeleton surface, hang (10 ~ 15) min; Dip in acetone with clean Kanakin again and clean above-mentioned zone, hang (10 ~ 15) min; Cleaning area at least exceeds region 30mm to be sealed;
2) primary coat is coated with: dip in bonding primary coat with clean Kanakin, be coated on region to be sealed, at least hang 15min, primary coat the area of application at least exceeds region 15mm to be sealed;
Step 2, sealing structure:
1) sealing in seam:
1.1) aquaseal is coated with: region coating blade coating type aquaseal to be sealed, aquaseal uniformly continous, thickness (0.5 ~ 0.8) mm;
1.2) assemble: adopt fastener to be linked and packed to covering and skeleton, ensure that aquaseal is evenly extruded in seam;
2) fillet sealing:
Adopt blade coating type modified polysulfide aquaseal to carry out fillet to covering and skeleton inside face edge, process fillet place aquaseal, make it smooth transition and become band, section form is triangle;
3) face seal:
Adopt brush-on-type modified polysulfide aquaseal to carry out brush application to covering and skeleton inside face fastener end, brush twice, cover first pass completely second time, be often one all over interval time and do not glue the phase, construction rear surface is smooth;
4) fastener sealing:
Fastener dip-and-scrap painting type modified polysulfide aquaseal hygrometric state assembles, and connecting bore is played to the effect of sealing, isolation and protection, reduces and delay the generation of fastener connection section position corrosion.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410667967.5A CN104443347A (en) | 2014-11-19 | 2014-11-19 | Design method for sealing aircraft skin and skeleton structure |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410667967.5A CN104443347A (en) | 2014-11-19 | 2014-11-19 | Design method for sealing aircraft skin and skeleton structure |
Publications (1)
| Publication Number | Publication Date |
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| CN104443347A true CN104443347A (en) | 2015-03-25 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201410667967.5A Pending CN104443347A (en) | 2014-11-19 | 2014-11-19 | Design method for sealing aircraft skin and skeleton structure |
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Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105070184A (en) * | 2015-09-15 | 2015-11-18 | 沈阳飞机工业（集团）有限公司 | Method for identifying sample by adopting aircraft sealing technology |
| CN105221748A (en) * | 2015-08-25 | 2016-01-06 | 中国航空工业集团公司西安飞机设计研究所 | A kind of encapsulating method of aircraft integral tank |
| CN108082527A (en) * | 2016-11-22 | 2018-05-29 | 空中客车运作有限责任公司 | For manufacturing the method on the smooth aerodynamic of aircraft component surface |
| CN108533751A (en) * | 2017-03-06 | 2018-09-14 | 陕西飞机工业（集团）有限公司 | A kind of process that seal cap uses |
| CN112391127A (en) * | 2020-10-19 | 2021-02-23 | 上海航翼高新技术发展研究院有限公司 | Self-adhesive tape for protecting V-shaped gap of aircraft skin |
| CN113339311A (en) * | 2021-05-31 | 2021-09-03 | 西南电子技术研究所（中国电子科技集团公司第十研究所） | Preparation method of high-corrosion-resistance air-cooled rack |
Citations (1)
| 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 |
-
2014
- 2014-11-19 CN CN201410667967.5A patent/CN104443347A/en active Pending
Patent Citations (1)
| 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 |
Non-Patent Citations (2)
| Title |
|---|
| 张晓娟等: "HM109-1型密封剂在某直升机上的工程化应用与分析", 《直升机技术》 * |
| 胡琳: "飞机整体油箱密封剂分析", 《民用飞机设计与研究》 * |
Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105221748A (en) * | 2015-08-25 | 2016-01-06 | 中国航空工业集团公司西安飞机设计研究所 | A kind of encapsulating method of aircraft integral tank |
| CN105070184A (en) * | 2015-09-15 | 2015-11-18 | 沈阳飞机工业（集团）有限公司 | Method for identifying sample by adopting aircraft sealing technology |
| CN108082527A (en) * | 2016-11-22 | 2018-05-29 | 空中客车运作有限责任公司 | For manufacturing the method on the smooth aerodynamic of aircraft component surface |
| CN108533751A (en) * | 2017-03-06 | 2018-09-14 | 陕西飞机工业（集团）有限公司 | A kind of process that seal cap uses |
| CN112391127A (en) * | 2020-10-19 | 2021-02-23 | 上海航翼高新技术发展研究院有限公司 | Self-adhesive tape for protecting V-shaped gap of aircraft skin |
| CN113339311A (en) * | 2021-05-31 | 2021-09-03 | 西南电子技术研究所（中国电子科技集团公司第十研究所） | Preparation method of high-corrosion-resistance air-cooled rack |
| CN113339311B (en) * | 2021-05-31 | 2023-08-15 | 西南电子技术研究所（中国电子科技集团公司第十研究所） | Preparation method of high corrosion-resistant air-cooled frame |
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Application publication date: 20150325 |