CN105667832A - Method for increasing iron clad bonding strength of leading edge of blade - Google Patents
Method for increasing iron clad bonding strength of leading edge of blade Download PDFInfo
- Publication number
- CN105667832A CN105667832A CN201610161443.8A CN201610161443A CN105667832A CN 105667832 A CN105667832 A CN 105667832A CN 201610161443 A CN201610161443 A CN 201610161443A CN 105667832 A CN105667832 A CN 105667832A
- Authority
- CN
- China
- Prior art keywords
- leading edge
- blade
- iron clad
- iron
- clad
- 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
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Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B24—GRINDING; POLISHING
- B24C—ABRASIVE OR RELATED BLASTING WITH PARTICULATE MATERIAL
- B24C1/00—Methods for use of abrasive blasting for producing particular effects; Use of auxiliary equipment in connection with such methods
- B24C1/04—Methods for use of abrasive blasting for producing particular effects; Use of auxiliary equipment in connection with such methods for treating only selected parts of a surface, e.g. for carving stone or glass
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/32—Rotors
- B64C27/46—Blades
- B64C27/473—Constructional features
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/32—Rotors
- B64C27/46—Blades
- B64C27/473—Constructional features
- B64C2027/4733—Rotor blades substantially made from particular materials
- B64C2027/4736—Rotor blades substantially made from particular materials from composite materials
Abstract
The invention relates to a method for increasing the iron clad bonding strength of the leading edge of a blade, which belongs to the technical field of composite materials. According to the method, before iron clad is formed, blasting treatment is performed on the bonding surface of the iron clad in advance, so that the roughness of the bonding surface of the iron clad is increased, then the iron clad is formed, thus, the roughness of the surface of the iron clad can be increased, the iron clad of the leading edge is difficult to debond from the composite blade, and the deformation of the iron clad due to the blasting treatment can be avoided. By adopting the method, the bonding quality of the stainless steel iron clad and the composite material can be effectively increased, and the reliability and safety of an airplane are increased.
Description
Technical field
The invention belongs to technical field of composite materials, relate to a kind of method improving blade coating iron at the leading edge adhesive strength.
Background technology
Composite material blade of helicopter adopts coating iron at the leading edge protection structure; iron clad material is the metal material such as rustless steel, nickel; the material of blade is composite; adhesive technology between iron clad and composite material blade is; first molding iron clad; then, adopt chemical pickling technique that the iron clad after molding is carried out surface treatment, then glued joint with composite material blade. Through the composite material blade that this Technology is prepared, its iron clad easily and composite material blade generation unsticking phenomenon, causes the iron clad going straight up to composite material blade to come off, affects flight safety.
Summary of the invention
The purpose of the present invention is to propose to a kind of method improving blade coating iron at the leading edge adhesive strength of coating iron at the leading edge and composite material blade not easily unsticking. The technical solution of the present invention is, the first step: adopt forced dry blasting machine that rustless steel iron clad raw material is carried out blasting treatment, blast media is 120 order quartz sands, technological parameter is pressure 2.5bar, spray gun and the raw-material distance of rustless steel iron clad: 150mm-200mm, the raw-material splicing face of rustless steel iron clad is carried out sandblasting by spray gun line by line;
Second step: rustless steel iron clad raw material is shaped to the shape matched with blade leading edge shape;
3rd step: the blade coating iron at the leading edge that molding is completed carries out alkali oil removal treatment;
4th step: by designing requirement, is coated with bonding agent on the splicing face of blade coating iron at the leading edge, and blade iron clad is placed on the paved composite material blade leading edge completed;
5th step: the composite material blade being enclosed with blade coating iron at the leading edge is carried out molded curing.
The present invention has the advantage that and beneficial effect, the present invention adopted before iron clad molding, iron clad is gluedd joint the method that blasting treatment is done in face in advance, the roughness that iron clad glueds joint face is made to increase, then, carry out iron clad molding again, so namely can improve the ironing surface roughness of bag and make coating iron at the leading edge and composite material blade not easily unsticking, be avoided that again the deformation that iron clad is caused by sandblasting. Adopt the method can be effectively improved the bonding quality of rustless steel iron clad and composite, improve reliability and the safety of aircraft.
Detailed description of the invention
The first step: adopt forced dry blasting machine that rustless steel iron clad raw material is carried out blasting treatment, blast media is 120 order quartz sands, technological parameter is pressure 2.5bar, spray gun and the raw-material distance of rustless steel iron clad: 150mm-200mm, the raw-material splicing face of rustless steel iron clad is carried out sandblasting by spray gun line by line;
Second step: rustless steel iron clad raw material is shaped to the shape matched with blade leading edge shape;
3rd step: the blade coating iron at the leading edge that molding is completed carries out alkali oil removal treatment;
4th step: by designing requirement, is coated with bonding agent on the splicing face of blade coating iron at the leading edge, and blade coating iron at the leading edge is placed on blade coating iron at the leading edge leading edge;
5th step: the composite material blade being enclosed with blade coating iron at the leading edge is carried out molded curing.
Embodiment
Iron clad material 0Cr18Ni9, paddle material: carbon fiber, glass fiber compound material;
The first step: adopt forced dry blasting machine that rustless steel iron clad raw material 0Cr18Ni9 is entered blasting treatment, medium is 120 order quartz sand technological parameters is pressure 2.5bar, the distance of spray gun and sand-blast material: 150mm-200mm, the raw-material splicing face of rustless steel iron clad is carried out sandblasting by spray gun line by line;
Second step: rustless steel iron clad raw material is shaped to the shape matched with blade leading edge shape;
3rd step: the blade coating iron at the leading edge that molding is completed carries out alkali oil removal treatment;
4th step: by designing requirement, is coated with bonding agent on the splicing face of blade coating iron at the leading edge, and blade iron clad is placed on the paved composite material blade leading edge completed;
5th step: the composite material blade being enclosed with blade coating iron at the leading edge is carried out molded curing.
Claims (1)
1. the method improving blade coating iron at the leading edge adhesive strength, is characterized in that,
The first step: adopt forced dry blasting machine that rustless steel iron clad raw material is carried out blasting treatment, blast media is 120 order quartz sands, technological parameter is pressure 2.5bar, spray gun and the raw-material distance of rustless steel iron clad: 150mm-200mm, the raw-material splicing face of rustless steel iron clad is carried out sandblasting by spray gun line by line;
Second step: rustless steel iron clad raw material is shaped to the shape matched with blade leading edge shape;
3rd step: the blade coating iron at the leading edge that molding is completed carries out alkali oil removal treatment;
4th step: by designing requirement, is coated with bonding agent on the splicing face of blade coating iron at the leading edge, and blade iron clad is placed on the paved composite material blade leading edge completed;
5th step: the composite material blade being enclosed with blade coating iron at the leading edge is carried out molded curing.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610161443.8A CN105667832A (en) | 2016-03-21 | 2016-03-21 | Method for increasing iron clad bonding strength of leading edge of blade |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610161443.8A CN105667832A (en) | 2016-03-21 | 2016-03-21 | Method for increasing iron clad bonding strength of leading edge of blade |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN105667832A true CN105667832A (en) | 2016-06-15 |
Family
ID=56311088
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201610161443.8A Pending CN105667832A (en) | 2016-03-21 | 2016-03-21 | Method for increasing iron clad bonding strength of leading edge of blade |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN105667832A (en) |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108032979A (en) * | 2017-12-04 | 2018-05-15 | 惠阳航空螺旋桨有限责任公司 | A kind of leading edge safeguard structure of alloy matrix aluminum blade |
| CN108067831A (en) * | 2016-11-14 | 2018-05-25 | 江西昌河航空工业有限公司 | A kind of thin-wall stamping part moulding process with splicing face |
| CN112846674A (en) * | 2021-01-04 | 2021-05-28 | 中国航空制造技术研究院 | Treatment method for titanium alloy wrapping edges of helicopter blades |
| CN116197092A (en) * | 2022-12-09 | 2023-06-02 | 哈尔滨哈飞航空工业有限责任公司 | Surface treatment method for stainless steel sheet before cementing |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20070177330A1 (en) * | 2005-09-06 | 2007-08-02 | Ackerman Patrice K | Copper grid repair technique for lightning strike protection |
| CN103101253A (en) * | 2013-01-23 | 2013-05-15 | 陕西生益科技有限公司 | Copper surface processing technique for manufacturing thick copper-clad laminated board |
| CN103331702A (en) * | 2013-07-08 | 2013-10-02 | 河北华北柴油机有限责任公司 | Sand blasting apparatus for small diameter pipe fitting inner walls |
| CN104670519A (en) * | 2013-12-02 | 2015-06-03 | 昌河飞机工业（集团）有限责任公司 | Blade front edge cap repairing method |
| CN104691779A (en) * | 2015-01-13 | 2015-06-10 | 哈尔滨飞机工业集团有限责任公司 | Process method for replacement and repair of iron clad of main blade made of composite material |
| CN105398050A (en) * | 2015-11-30 | 2016-03-16 | 哈尔滨飞机工业集团有限责任公司 | Bonding method for helicopter blade front edge wrapping piece |
-
2016
- 2016-03-21 CN CN201610161443.8A patent/CN105667832A/en active Pending
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20070177330A1 (en) * | 2005-09-06 | 2007-08-02 | Ackerman Patrice K | Copper grid repair technique for lightning strike protection |
| CN103101253A (en) * | 2013-01-23 | 2013-05-15 | 陕西生益科技有限公司 | Copper surface processing technique for manufacturing thick copper-clad laminated board |
| CN103331702A (en) * | 2013-07-08 | 2013-10-02 | 河北华北柴油机有限责任公司 | Sand blasting apparatus for small diameter pipe fitting inner walls |
| CN104670519A (en) * | 2013-12-02 | 2015-06-03 | 昌河飞机工业（集团）有限责任公司 | Blade front edge cap repairing method |
| CN104691779A (en) * | 2015-01-13 | 2015-06-10 | 哈尔滨飞机工业集团有限责任公司 | Process method for replacement and repair of iron clad of main blade made of composite material |
| CN105398050A (en) * | 2015-11-30 | 2016-03-16 | 哈尔滨飞机工业集团有限责任公司 | Bonding method for helicopter blade front edge wrapping piece |
Non-Patent Citations (1)
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| 李丽波等: "《表面预处理实用手册》", 31 January 2014, 机械工业出版社 * |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108067831A (en) * | 2016-11-14 | 2018-05-25 | 江西昌河航空工业有限公司 | A kind of thin-wall stamping part moulding process with splicing face |
| CN108032979A (en) * | 2017-12-04 | 2018-05-15 | 惠阳航空螺旋桨有限责任公司 | A kind of leading edge safeguard structure of alloy matrix aluminum blade |
| CN112846674A (en) * | 2021-01-04 | 2021-05-28 | 中国航空制造技术研究院 | Treatment method for titanium alloy wrapping edges of helicopter blades |
| CN116197092A (en) * | 2022-12-09 | 2023-06-02 | 哈尔滨哈飞航空工业有限责任公司 | Surface treatment method for stainless steel sheet before cementing |
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| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| WD01 | Invention patent application deemed withdrawn after publication | ||
| WD01 | Invention patent application deemed withdrawn after publication |
Application publication date: 20160615 |