CN108817487A - A method of thin-wall titanium alloy plate is processed into aircraft skin - Google Patents
A method of thin-wall titanium alloy plate is processed into aircraft skin Download PDFInfo
- Publication number
- CN108817487A CN108817487A CN201810608719.1A CN201810608719A CN108817487A CN 108817487 A CN108817487 A CN 108817487A CN 201810608719 A CN201810608719 A CN 201810608719A CN 108817487 A CN108817487 A CN 108817487A
- Authority
- CN
- China
- Prior art keywords
- thin
- titanium alloy
- alloy plate
- wall titanium
- aircraft skin
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- 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.)
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Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
- B23C—MILLING
- B23C3/00—Milling particular work; Special milling operations; Machines therefor
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
- B23C—MILLING
- B23C2215/00—Details of workpieces
- B23C2215/04—Aircraft components
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
- B23C—MILLING
- B23C2222/00—Materials of tools or workpieces composed of metals, alloys or metal matrices
- B23C2222/88—Titanium
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Shaping Metal By Deep-Drawing, Or The Like (AREA)
Abstract
The present invention is thin-wall titanium alloy plate material molding technology, and in particular to a method of thin-wall titanium alloy plate is processed into aircraft skin, the modified thickness of aircraft skin after molding.Thin-wall titanium alloy plate for aircraft skin, size before processing is δ 1.2 × 2000 × 300, it is too thin, part machined surface is big, clamping face is difficult to flatten when processing, and part inherently has thickness error, and part is uneven, height difference can reach 0.4mm, be easily deformed be difficult to ensure thickness uniformly and in the margin of tolerance in process.The present invention provides a kind of method that thin-wall titanium alloy plate is processed into aircraft skin, is processed after installing thin-wall titanium alloy plate on reference surface by milling front, is then processed by milling reverse side, guarantees that parts fixation is stablized, processing sequence is reasonable.Rationally control cutting output, when clamping, clearly suppress the sequence of plate, can be realized the flatness of machined surface in 0.05mm in the actual processing process.
Description
Technical field
The present invention is thin-wall titanium alloy plate material molding technology, and in particular to a kind of that thin-wall titanium alloy plate is processed into aircraft
The method of covering, the modified thickness of aircraft skin after molding.
Background technique
For the thin-wall titanium alloy plate of aircraft skin, the size before processing is δ 1.2 × 2000 × 300, and too thin, part adds
Work face is big, and clamping face is difficult to flatten when processing, and part inherently has thickness error, and part is uneven, and height difference can
Reach 0.4mm, is easily deformed is difficult to ensure thickness uniformly and in the margin of tolerance in process.
Summary of the invention
The present invention provides a kind of method that thin-wall titanium alloy plate is processed into aircraft skin, guarantees that parts fixation is stablized, adds
Work sequence is reasonable.
A method of thin-wall titanium alloy plate is processed into aircraft skin, is included the following steps：
One, thin-wall titanium alloy plate is installed on reference surface
When clamping plate need to be successively suppressed toward surrounding from intermediate；
Two, front processing thin-wall titanium alloy plate
The front corresponds to aircraft skin inner surface, processes the depth in each region by way of numerical control milling to the surface
It sink, then processes location hole；
Three, reverse side processes thin-wall titanium alloy plate
Special tooling, the outer mold surface of the tooling matchs with the front of thin-wall titanium alloy plate, and when reverse side clamping need to be past from centre
Surrounding successively suppresses plate；The depth for processing each region by way of numerical control milling to reverse side is sunk, from intermediate region when processing
It is processed toward surrounding, carries out contour machining later, finally obtain the part of aircraft skin.
When being installed on reference surface, by detecting the flatness for determining thin-wall titanium alloy plate within 0.2mm.
In reverse side clamping, by detect determine flatness of the thin-wall titanium alloy plate at same depth 0.05mm with
It is interior.
Thin-wall titanium alloy plate is positioned by the positioning pin in tooling when reverse side clamping, there are precision holes in tooling, for adding
The origin in working hour.
Beneficial effect：In this way, rationally control cutting output, when clamping, clearly suppress plate in the actual processing process
Sequentially, it can be realized the flatness of machined surface in 0.05mm.
Specific embodiment
Specific implementation process of the invention is as follows：
One, thin-wall titanium alloy plate is installed on reference surface
Plate need to be successively suppressed toward surrounding from intermediate when clamping, while determine that the flatness of thin-wall titanium alloy plate exists by detecting
Within 0.2mm；
Two, front processing thin-wall titanium alloy plate
The front corresponds to aircraft skin inner surface, processes the depth in each region by way of numerical control milling to the surface
It sink, then processes location hole；
Three, reverse side processes thin-wall titanium alloy plate
Special tooling, the outer mold surface of the tooling is matched with the front of thin-wall titanium alloy plate, and passes through the positioning pin in tooling
Thin-wall titanium alloy plate being positioned, there are precision holes in tooling, origin when for processing.It need to successively be beaten from intermediate toward surrounding when clamping
Pressing plate, while determining flatness of the thin-wall titanium alloy plate at same depth within 0.05mm by detecting；
The depth that each region is processed by way of numerical control milling to the surface is sunk, from intermediate region toward surrounding when processing
Processing, it is ensured that the stress that part generates when processing is decomposed toward surrounding.Contour machining is carried out later, finally obtains the zero of aircraft skin
Part.
Claims (4)
1. a kind of method that thin-wall titanium alloy plate is processed into aircraft skin, which is characterized in that include the following steps：
One, thin-wall titanium alloy plate is installed on reference surface
When clamping plate need to be successively suppressed toward surrounding from intermediate；
Two, front processing thin-wall titanium alloy plate
The front corresponds to aircraft skin inner surface, is processed by way of numerical control milling under the depth in each region to the surface
It falls into, then processes location hole；
Three, reverse side processes thin-wall titanium alloy plate
Special tooling, the outer mold surface of the tooling matchs with the front of thin-wall titanium alloy plate, and when reverse side clamping need to be from intermediate past surrounding
Successively suppress plate；The depth for processing each region by way of numerical control milling to reverse side is sunk, from intermediate region toward four when processing
Zhou Jiagong carries out contour machining later, finally obtains the part of aircraft skin.
2. according to the method described in claim 1, it is characterized in that：When installing on reference surface, thin-walled is determined by detecting
The flatness of titanium alloy sheet is within 0.2mm.
3. according to the method described in claim 1, it is characterized in that：In reverse side clamping, thin-wall titanium alloy is determined by detecting
Flatness of the plate at same depth is within 0.05mm.
4. according to the method described in claim 1, it is characterized in that：By the positioning pin in tooling to thin-wall titanium when reverse side clamping
Alloy sheets position, and have precision holes in tooling, origin when for processing.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810608719.1A CN108817487A (en) | 2018-06-13 | 2018-06-13 | A method of thin-wall titanium alloy plate is processed into aircraft skin |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810608719.1A CN108817487A (en) | 2018-06-13 | 2018-06-13 | A method of thin-wall titanium alloy plate is processed into aircraft skin |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN108817487A true CN108817487A (en) | 2018-11-16 |
Family
ID=64141339
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201810608719.1A Pending CN108817487A (en) | 2018-06-13 | 2018-06-13 | A method of thin-wall titanium alloy plate is processed into aircraft skin |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN108817487A (en) |
Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB703239A (en) * | 1949-12-06 | 1954-02-03 | Fairey Aviat Co Ltd | Improvements in or relating to the manufacture of complex structures of sheet material |
| US20090146008A1 (en) * | 2007-03-28 | 2009-06-11 | Airbus Deutschland Gmbh | Door Frame Compartment of Cast Titanium and Structural Fuselage Part |
| CN103920915A (en) * | 2014-04-04 | 2014-07-16 | 中航沈飞民用飞机有限责任公司 | Thin skin milling device and method for milling by utilizing device |
| CN104476132A (en) * | 2014-11-26 | 2015-04-01 | 江西洪都航空工业集团有限责任公司 | Manufacturing process for aircraft skin |
| CN105033585A (en) * | 2015-08-03 | 2015-11-11 | 江西洪都航空工业集团有限责任公司 | Double-curved-surface sawtooth skin manufacturing method capable of controlling gap clearance precisely |
| CN105677997A (en) * | 2016-01-13 | 2016-06-15 | 上海数设科技有限公司 | Method and device for determining size of airplane skin unit chemically-milled area |
| CN105269049B (en) * | 2015-11-28 | 2017-07-14 | 沈阳飞机工业（集团）有限公司 | A kind of aircraft skin is without surplus digital control milling method |
-
2018
- 2018-06-13 CN CN201810608719.1A patent/CN108817487A/en active Pending
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB703239A (en) * | 1949-12-06 | 1954-02-03 | Fairey Aviat Co Ltd | Improvements in or relating to the manufacture of complex structures of sheet material |
| US20090146008A1 (en) * | 2007-03-28 | 2009-06-11 | Airbus Deutschland Gmbh | Door Frame Compartment of Cast Titanium and Structural Fuselage Part |
| CN103920915A (en) * | 2014-04-04 | 2014-07-16 | 中航沈飞民用飞机有限责任公司 | Thin skin milling device and method for milling by utilizing device |
| CN104476132A (en) * | 2014-11-26 | 2015-04-01 | 江西洪都航空工业集团有限责任公司 | Manufacturing process for aircraft skin |
| CN105033585A (en) * | 2015-08-03 | 2015-11-11 | 江西洪都航空工业集团有限责任公司 | Double-curved-surface sawtooth skin manufacturing method capable of controlling gap clearance precisely |
| CN105269049B (en) * | 2015-11-28 | 2017-07-14 | 沈阳飞机工业（集团）有限公司 | A kind of aircraft skin is without surplus digital control milling method |
| CN105677997A (en) * | 2016-01-13 | 2016-06-15 | 上海数设科技有限公司 | Method and device for determining size of airplane skin unit chemically-milled area |
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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 | ||
| RJ01 | Rejection of invention patent application after publication | ||
| RJ01 | Rejection of invention patent application after publication |
Application publication date: 20181116 |