CN101811571A - Integrated forming method of closed composite material taper fairing - Google Patents
Integrated forming method of closed composite material taper fairing Download PDFInfo
- Publication number
- CN101811571A CN101811571A CN201010103051A CN201010103051A CN101811571A CN 101811571 A CN101811571 A CN 101811571A CN 201010103051 A CN201010103051 A CN 201010103051A CN 201010103051 A CN201010103051 A CN 201010103051A CN 101811571 A CN101811571 A CN 101811571A
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- China
- Prior art keywords
- composite material
- fairing
- shop
- forming method
- material taper
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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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Abstract
The invention belongs to composite material forming technologies and relates to an integrated forming method of a closed composite material taper fairing. The forming method comprises the steps of: die making, overall layering, formed frock replacing, integral vacuum bag sealing and solidifying and forming. The forming method not only meets the requirement of integral layering, but also reaches the quality requirement of the outer surface of the fairing and satisfies the development requirement of a certain type of helicopter.
Description
Technical field
The invention belongs to the composite material forming technology, relate to a kind of integral forming method of closed composite material taper fairing part.
Background technology
Certain type helicopter tail cone fairing is the closed cone structure of full composite material, and its Forming Quality need satisfy the requirement of outside face one-level.And, need whole shop to apply during the layer of shop to satisfy requirement of strength.If adopt the female mould forming of traditional upper and lower mould structure, because the inner chamber of cone tip is narrow and small, can't carries out the integral body shop and apply, can not satisfy the requirement of whole shop layer; And if this part of employing formpiston structure frock moulding is difficult to delivery after then solidifying, and can't satisfy the requirements for quality of outside face.
Summary of the invention
The objective of the invention is: a kind of integral forming method of closed composite material taper fairing is provided, spreads the requirement of layer to satisfy integral body, and guarantee the requirements for quality of fairing outside face.
Technical scheme of the present invention is: integrated forming method of closed composite material taper fairing is characterized in that the step of moulding is as follows:
1, mould-manufacturing; Make formpiston and former two sleeve forming frocks respectively;
2, the whole layer of spreading; Carrying out the shop of the whole shop of composite material taper fairing layer on formpiston applies;
3, change the moulding frock; Good composite material taper fairing shop layer is applied in the shop take off, put into the female mould forming frock from formpiston;
4, envelope system overall vacuum bag;
5, curing molding.
Advantage of the present invention is: both satisfied the requirement of whole shop layer, can guarantee the requirements for quality of fairing outside face again, satisfied the development needs of certain type helicopter.
Description of drawings
Fig. 1 is the design of part scheme drawing of certain type helicopter tail cone fairing.
The specific embodiment
Below the present invention is described in further details.Integrated forming method of closed composite material taper fairing is characterized in that, the step of moulding is as follows:
Principle of work of the present invention is: after adopting formpiston to carry out integral body shop layer, by changing the moulding frock, adopt the female mould forming frock to be cured moulding.Like this, the intensity of composite material taper fairing can be guaranteed, its outer surface quality can be improved again.
Embodiment
Certain type helicopter tail cone fairing that moulding is shown in Figure 1.
1, mould-manufacturing; Formpiston and former two sleeve forming frocks have been made respectively;
2, the whole layer of spreading; Carrying out earlier the shop of the whole shop of composite material taper fairing layer on formpiston applies;
3, change the moulding frock; Good composite material taper fairing shop layer is applied in the shop take off, put into the female mould forming frock from formpiston;
4, envelope system overall vacuum bag;
5, curing molding.
Claims (1)
1. integrated forming method of closed composite material taper fairing is characterized in that, the step of moulding is as follows:
1.1, mould-manufacturing; Make formpiston and former two sleeve forming frocks respectively;
1.2, whole shop layer; Carrying out the shop of the whole shop of composite material taper fairing layer on formpiston applies;
1.3, change the moulding frock; Good composite material taper fairing shop layer is applied in the shop take off, put into the female mould forming frock from formpiston;
1.4, envelope system overall vacuum bag;
1.5, curing molding.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201010103051A CN101811571A (en) | 2010-01-26 | 2010-01-26 | Integrated forming method of closed composite material taper fairing |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201010103051A CN101811571A (en) | 2010-01-26 | 2010-01-26 | Integrated forming method of closed composite material taper fairing |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN101811571A true CN101811571A (en) | 2010-08-25 |
Family
ID=42618978
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201010103051A Pending CN101811571A (en) | 2010-01-26 | 2010-01-26 | Integrated forming method of closed composite material taper fairing |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN101811571A (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102501350A (en) * | 2011-10-27 | 2012-06-20 | 大同机车新型材料制品有限责任公司 | Injection-compression molding method for glass fiber reinforced plastic fairing of locomotive |
| CN113335504A (en) * | 2021-08-09 | 2021-09-03 | 中国空气动力研究与发展中心空天技术研究所 | Rotor wing fairing of composite wing aircraft |
-
2010
- 2010-01-26 CN CN201010103051A patent/CN101811571A/en active Pending
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102501350A (en) * | 2011-10-27 | 2012-06-20 | 大同机车新型材料制品有限责任公司 | Injection-compression molding method for glass fiber reinforced plastic fairing of locomotive |
| CN113335504A (en) * | 2021-08-09 | 2021-09-03 | 中国空气动力研究与发展中心空天技术研究所 | Rotor wing fairing of composite wing aircraft |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| C02 | Deemed withdrawal of patent application after publication (patent law 2001) | ||
| WD01 | Invention patent application deemed withdrawn after publication |
Application publication date: 20100825 |