CN106741830A - A kind of preventing galvanic corrosion method of aircraft skin joint face - Google Patents
A kind of preventing galvanic corrosion method of aircraft skin joint face Download PDFInfo
- Publication number
- CN106741830A CN106741830A CN201611059085.6A CN201611059085A CN106741830A CN 106741830 A CN106741830 A CN 106741830A CN 201611059085 A CN201611059085 A CN 201611059085A CN 106741830 A CN106741830 A CN 106741830A
- Authority
- CN
- China
- Prior art keywords
- pinboard
- covering
- aircraft
- galvanic corrosion
- connecting hole
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Pending
Links
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
- B64C1/06—Frames; Stringers; Longerons ; Fuselage sections
- B64C1/12—Construction or attachment of skin panels
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
- B64C2001/0054—Fuselage structures substantially made from particular materials
- B64C2001/0081—Fuselage structures substantially made from particular materials from metallic materials
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- Prevention Of Electric Corrosion (AREA)
Abstract
The invention provides a kind of preventing galvanic corrosion method of aircraft skin joint face, aircraft skin is fixed on the aircraft matrix for being coated with preventing galvanic corrosion figure layer using the pinboard identical and/or close with aircraft skin material current potential.This method ensure that often the part of dismounting is connected thereto base member holding same material, there is no galvanic corrosion, while reducing the contact area between foreign material, by combining coating technology, can effectively reduce the probability of happening of galvanic corrosion.
Description
Technical field
The invention belongs to the preventing galvanic corrosion field of aircraft, and in particular to a kind of anti-galvanic couple of aircraft skin joint face is rotten
Etching method.
Background technology
Because flying speed is big, agility is high, the type selecting of product structure material is also gradually intended to gently supersonic vehicle
Quantify, relative to materials such as aluminium alloy, structural alloy steels, titanium alloy material is high due to specific strength, specific stiffness, can obtain preferably
Weight loss effect, can greatly improve structure efficiency.
Due to the current potential calibration of titanium alloy, when it is connected composition sub-assembly with other metals, titanium alloy can cause therewith
The galvanic corrosion of other metal materials of contact.By taking TC4 titanium alloys as an example, TC4 titanium alloys connect with structural alloy steel 20CrMnTi
Contact corrosion can be produced when connecing, intensity is reduced.
The content of the invention
The purpose of the present invention：By optimizing structure type, it is combined with coating technology, the anti-galvanic couple for improving product structure is rotten
The ability of erosion.Propose a kind of preventing galvanic corrosion method of aircraft skin joint face.
Technical scheme：
There is provided a kind of preventing galvanic corrosion method of aircraft skin joint face, aircraft skin 1 and pinboard 2 in the method
Titanium alloy material is, covering 1 is identical or different with the titanium alloy trade mark of pinboard 2；Aircraft basal body structure is structural alloy steel
Material；The top and bottom of pinboard 2 are respectively covering contact surface and substrate contact face；
Covering connecting hole and matrix connecting hole are provided with pinboard 2, and covering connecting hole is spaced with matrix connecting hole；
Described method comprises the following steps：
Step one, the coating preventing galvanic corrosion coating on the substrate contact face of pinboard 2 and aircraft basal body structure；
Step 2, by fastener through the matrix connecting hole of pinboard 2, and pinboard 2 is fixed to aircraft basal body structure
On so that fitted with aircraft basal body structure in described substrate contact face；
Step 3, fastener is sequentially passed through the covering connecting hole of covering 1 and pinboard 2, and covering 1 is fixed to switching
On plate 2 so that described covering 1 is fitted with the covering contact surface.
Further, such as Fig. 2 a and 2b, covering 1 uses titanium alloy TC 4 material, aircraft basal body structure material with pinboard 2
Expect to be 20CrMnTi alloy steel materials.
Advantages of the present invention：
By increasing the pinboard consistent with skin material between TC4 titanium alloy coverings and 20CrMnTi matrixes, prevent from covering
Protective coating of the skin on damaging substrate during frequently dismounting；Simultaneously as anticorrosive measure can be in covering and switching
Solved between plate, therefore the contact area between matrix and pinboard can be reduced, reduce the coated area of protective coating；Due to turning
Fishplate bar need not be dismantled frequently after being connected with matrix, therefore protective coating is survivable.
The design feature ensure that the part of normal dismounting is connected thereto base member and keeps same material, galvanic couple not occur rotten
Erosion, while reducing the contact area between foreign material, by combining coating technology, the generation that can effectively reduce galvanic corrosion is general
Rate.
Brief description of the drawings：
Fig. 1 a are the skin connecting structure sectional view of prior art；
Fig. 1 b are the skin connecting structure schematic diagram of prior art；
Fig. 2 a are preventing galvanic corrosion structure sectional view；
Fig. 2 b are preventing galvanic corrosion structural representation；
Fig. 3 is pinboard and aircraft matrix connection diagram；
Fig. 4 is covering and pinboard connection diagram；
Wherein：1- coverings, 2- pinboards, 3- aircraft basal body structures.
Specific embodiment：
The present invention is described in further detail below in conjunction with the accompanying drawings.
There is provided a kind of preventing galvanic corrosion method of aircraft skin joint face, aircraft skin 1 and pinboard 2 in the method
Titanium alloy material is, covering 1 is identical or different with the titanium alloy trade mark of pinboard 2；Aircraft basal body structure 3 is structural alloy steel
Material；The top and bottom of pinboard 2 are respectively covering contact surface and substrate contact face；
Covering connecting hole and matrix connecting hole are provided with pinboard 2, and covering connecting hole is spaced with matrix connecting hole；
Described method comprises the following steps：
Step one, the coating preventing galvanic corrosion coating on the substrate contact face of pinboard 2 and aircraft basal body structure；
Step 2, by fastener through the matrix connecting hole of pinboard 2, and pinboard 2 is fixed to aircraft basal body structure
On so that fitted with aircraft basal body structure 3 in described substrate contact face；
Step 3, fastener is sequentially passed through the covering connecting hole of covering 1 and pinboard 2, and covering 1 is fixed to switching
On plate 2 so that described covering 1 is fitted with the covering contact surface.
Further, such as Fig. 2 a and 2b, covering 1 uses titanium alloy TC 4 material, aircraft basal body structure material with pinboard 2
Expect to be 20CrMnTi alloy steel materials.
Claims (2)
1. a kind of preventing galvanic corrosion method of aircraft skin joint face, the aircraft skin (1) in the method is with pinboard (2)
Titanium alloy material, covering (1) is identical or different with the titanium alloy trade mark of pinboard (2)；Aircraft basal body structure (3) is alloy structure
Steel material；The top and bottom of pinboard (2) are respectively covering contact surface and substrate contact face；
Covering connecting hole and matrix connecting hole are provided with pinboard (2), and covering connecting hole is spaced with matrix connecting hole；
Described method comprises the following steps：
Step one, the coating preventing galvanic corrosion coating on the substrate contact face of pinboard (2) and aircraft basal body structure；
Step 2, by fastener through the matrix connecting hole of pinboard (2), and pinboard (2) is fixed to aircraft basal body structure
On so that fitted with aircraft basal body structure (3) in described substrate contact face；
Step 3, the covering connecting hole that fastener is sequentially passed through covering (1) and pinboard (2), and by covering (1) be fixed to turn
On fishplate bar (2) so that described covering (1) is fitted with the covering contact surface.
2. the preventing galvanic corrosion method of a kind of aircraft skin joint face according to claim 1, it is characterised in that：Covering
(1) titanium alloy TC 4 material is used with pinboard (2), aircraft basal body structure material is 20CrMnTi alloy steel materials.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201611059085.6A CN106741830A (en) | 2016-11-24 | 2016-11-24 | A kind of preventing galvanic corrosion method of aircraft skin joint face |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201611059085.6A CN106741830A (en) | 2016-11-24 | 2016-11-24 | A kind of preventing galvanic corrosion method of aircraft skin joint face |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN106741830A true CN106741830A (en) | 2017-05-31 |
Family
ID=58911503
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201611059085.6A Pending CN106741830A (en) | 2016-11-24 | 2016-11-24 | A kind of preventing galvanic corrosion method of aircraft skin joint face |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN106741830A (en) |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101631719A (en) * | 2007-01-23 | 2010-01-20 | 空中客车德国有限公司 | Connecting element and use of such a connecting element for fastening aircraft components in the case of a CFK-metal hybrid construction |
| US20100206989A1 (en) * | 2007-06-26 | 2010-08-19 | Airbus Operations Gmbh | Corrosion-resistant connection between a first component and second component |
| CN104276274A (en) * | 2013-07-10 | 2015-01-14 | 波音公司 | Apparatus and methods for joining composite structures of aircrafts |
| CN106435601A (en) * | 2016-11-22 | 2017-02-22 | 江西洪都航空工业集团有限责任公司 | Galvanic corrosion prevention method for airplane skin connection surface |
-
2016
- 2016-11-24 CN CN201611059085.6A patent/CN106741830A/en active Pending
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101631719A (en) * | 2007-01-23 | 2010-01-20 | 空中客车德国有限公司 | Connecting element and use of such a connecting element for fastening aircraft components in the case of a CFK-metal hybrid construction |
| US20100206989A1 (en) * | 2007-06-26 | 2010-08-19 | Airbus Operations Gmbh | Corrosion-resistant connection between a first component and second component |
| CN104276274A (en) * | 2013-07-10 | 2015-01-14 | 波音公司 | Apparatus and methods for joining composite structures of aircrafts |
| CN106435601A (en) * | 2016-11-22 | 2017-02-22 | 江西洪都航空工业集团有限责任公司 | Galvanic corrosion prevention method for airplane skin connection surface |
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Legal Events
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|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| WD01 | Invention patent application deemed withdrawn after publication |
Application publication date: 20170531 |
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| WD01 | Invention patent application deemed withdrawn after publication |