CN101642962A - Forming method for hull of gas vane made of composite materials - Google Patents
Forming method for hull of gas vane made of composite materials Download PDFInfo
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- CN101642962A CN101642962A CN200810041388A CN200810041388A CN101642962A CN 101642962 A CN101642962 A CN 101642962A CN 200810041388 A CN200810041388 A CN 200810041388A CN 200810041388 A CN200810041388 A CN 200810041388A CN 101642962 A CN101642962 A CN 101642962A
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Abstract
The invention relates to a forming method for a hull of a gas vane made of composite materials. The method is implemented by the steps of substrate surface processing, layer-binding, pre-forming, pressing and demoulding. The method has the advantages that: because the process of the substrate surface processing and pre-curing before pressing is adopted, the problems that the binding performance between the two interfaces of the substrate and the binding layer is poor and the substrate is seriously deformed when formed are solved.
Description
Technical field
The present invention relates to a kind of hull of gas vane made, relate in particular to this hull of gas vane made and adopt composite material forming method.
Background technology
Certain weapon hull of gas vane made is mainly formed by metallic aluminium alloy substrate and the composite molding of nonmetallic materials paste layer two parts.Compare conventional metal combustion gas rudder stock, hull of gas vane made of composite materials has lighter quality, higher anti-ablation, anti-washing away and airborne lotus.But because adhesive property is relatively poor between the matrix of hull of gas vane made of composite materials and paste layer two parts interface, matrix is out of shape seriously during moulding, so the moulding process difficulty of hull of gas vane made of composite materials is bigger.
Summary of the invention
The technical issues that need to address of the present invention have provided a kind of forming method for hull of gas vane made of composite materials, are intended to solve the above problems.
In order to solve the problems of the technologies described above, the present invention realizes by following steps:
Matrix surface is handled: in the matrix surface sandblast, be coated with a kind of organo-silicon coupling agent at matrix surface then, the molecular structural formula of this organo-silicon coupling agent is H
2N-CH
2-CH
2CH
2-Si (OC
2H
5)
3
Paste layer: the composite paste layer adopts high silicone resin composite materials; The resin of composite paste layer adopts solidification temperature to be lower than the middle temperature resin of aluminium alloy temper softening degree; Before the paste layer, vagcor cloth impregnated phenolic resin is made high silica preimpregnation glass cloth, then preimpregnation cloth is cut into a certain size and is laid on the metallic matrix;
Preformed: the goods that will spread behind the layer are put in precuring in the autoclave, and the mode that curing mode adopts ladder to suppress is specially and is warming up to 105 ± 15 ℃, suppresses 0.5～0.8Mpa, is warming up to 130 ± 15 ℃ again, is incubated 1.5～2.5 hours;
Compacting: the goods after the preformed are put into mould, in die cavity, add high silicone premix, on press, adopt staged to suppress curing, be specially and be warming up to 105 ± 15 ℃, suppress 15 ± 5MPa, be warming up to 120 ± 10 ℃, be incubated 0.5～1 hour, be warming up to 145 ± 15 ℃, be incubated 3～5 hours;
The demoulding: after finishing compacting, treat the goods release to be come out of the stove after press is cooled to room temperature.
Compared with prior art, the invention has the beneficial effects as follows: since adopted matrix surface handle and compacting before the process of first precuring, the serious problem of matrix distortion when having solved between matrix and paste layer two interfaces adhesive property difference and moulding.
Description of drawings
Fig. 1 is a flow chart of the present invention.
The specific embodiment
Below in conjunction with the accompanying drawing and the specific embodiment the present invention is described in further detail:
The present invention realizes by following steps:
Step 1: matrix surface is handled.In the matrix surface sandblast, increase the area of the bonding plane of matrix and paste layer.Be coated with a kind of organo-silicon coupling agent at matrix surface then, the molecular structural formula of this organo-silicon coupling agent is H
2N-CH
2-CH
2CH
2-Si (OC
2H
5)
3Because this coupling agent on chemical constitution, has the reactive functionality of different in kind on the end group of molecule, can combine with the paste layer composite is good, also can combine with alloy matrix aluminum is good.By the effect of coupling agent, make the material coupling of this two classes different in kind of metallic matrix and composite paste layer, just can obtain good adhesive property.
Step 2: paste layer.Because the combustion gas rudder stock when whole bullet emission, need bear certain overload pressure and high-temperature fuel gas ablation, effect such as wash away, so the composite paste layer adopts high silicone resin composite materials.Cause aluminium alloy temper softening problem for fear of follow-up paste layer curing, the resin of composite paste layer adopts solidification temperature to be lower than the middle temperature resin of aluminium alloy temper softening degree.Before the paste layer, vagcor cloth impregnated phenolic resin is made high silica preimpregnation glass cloth, then preimpregnation cloth is cut into a certain size and is laid on the metallic matrix.
Step 3: preformed.The problem of matrix distortion when solving the moulding of composite combustion gas rudder stock needs earlier to carry out preformed to the combustion gas rudder stock of paste layer.Goods behind the layer of shop are put in precuring in the autoclave, and the mode that curing mode adopts ladder to suppress is specially and is warming up to 105 ± 15 ℃, suppresses 0.5～0.8Mpa, is warming up to 130 ± 15 ℃ again, is incubated 1.5～2.5 hours.
Step 4: compacting.Goods after the preformed are put into particular manufacturing craft, in die cavity, add high silicone premix, on press, adopt staged to suppress curing, be specially and be warming up to 105 ± 15 ℃, suppress 15 ± 5MPa, be warming up to 120 ± 10 ℃, be incubated 0.5～1 hour, be warming up to 145 ± 15 ℃, be incubated 3～5 hours.
Step 5: the demoulding.After finishing compacting, treat the goods release to be come out of the stove after press is cooled to room temperature.
Be a concrete forming method of composite combustion gas rudder stock below:
The metal base surface sandblast is increased and nonmetallic contact area.Subsequently, evenly be coated with one deck H at matrix surface
2N-CH
2-CH
2CH
2-Si (OC
2H
5)
3Coupling agent guarantees that metallic matrix and nonmetallic materials can be compound.
High silica/barium phenolic aldehyde is made preimpregnation cloth, preimpregnation cloth is cut into the cloth of 1000mm * 100mm size, cloth is laid in metal base surface equably.
The goods of having spread layer are put into autoclave, be warming up to 105 ± 15 ℃ from room temperature, suppress 0.5～0.8Mpa simultaneously, keep-uping pressure is increased to 130 ± 15 ℃ with temperature, and this temperature insulation 1.5～2.5 hours, cools to room temperature at last with the furnace, takes out goods.
Preformed goods are put in particular manufacturing craft, make prepreg with high silica/barium phenolic aldehyde and put into die cavity, cure under pressure on hot press, curing mode is that room temperature rises to 105 ± 15 ℃, suppress 15 ± 5MPa, be warming up to 120 ± 10 ℃, be incubated 0.5～1 hour, be warming up to 145 ± 15 ℃, be incubated 3～5 hours.
After being cooled to room temperature with press, the moulding that goods have promptly been finished hull of gas vane made of composite materials is taken out in the demoulding.
Claims (1)
1. forming method for hull of gas vane made of composite materials, realize by following steps:
Matrix surface is handled: in the matrix surface sandblast, be coated with a kind of organo-silicon coupling agent at matrix surface then, the molecular structural formula of this organo-silicon coupling agent is H
2N-CH
2-CH
2CH
2-Si (OC
2H
5)
3
Paste layer: the composite paste layer adopts high silicone resin composite materials; The resin of composite paste layer adopts solidification temperature to be lower than the middle temperature resin of aluminium alloy temper softening degree; Before the paste layer, vagcor cloth impregnated phenolic resin is made high silica preimpregnation glass cloth, then preimpregnation cloth is cut into a certain size and is laid on the metallic matrix;
Preformed: the goods that will spread behind the layer are put in precuring in the autoclave, and the mode that curing mode adopts ladder to suppress is specially and is warming up to 105 ± 15 ℃, suppresses 0.5～0.8Mpa, is warming up to 130 ± 15 ℃ again, is incubated 1.5～2.5 hours;
Compacting: the goods after the preformed are put into mould, in die cavity, add high silicone premix, on press, adopt staged to suppress curing, be specially and be warming up to 105 ± 15 ℃, suppress 15 ± 5MPa, be warming up to 120 ± 10 ℃, be incubated 0.5～1 hour, be warming up to 145 ± 15 ℃, be incubated 3～5 hours;
The demoulding: after finishing compacting, treat the goods release to be come out of the stove after press is cooled to room temperature.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN200810041388A CN101642962A (en) | 2008-08-05 | 2008-08-05 | Forming method for hull of gas vane made of composite materials |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN200810041388A CN101642962A (en) | 2008-08-05 | 2008-08-05 | Forming method for hull of gas vane made of composite materials |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN101642962A true CN101642962A (en) | 2010-02-10 |
Family
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| CN200810041388A Pending CN101642962A (en) | 2008-08-05 | 2008-08-05 | Forming method for hull of gas vane made of composite materials |
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Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105069857A (en) * | 2015-07-20 | 2015-11-18 | 西安航空制动科技有限公司 | Flight data recorder casing and preparation method thereof |
| CN105225294A (en) * | 2015-09-15 | 2016-01-06 | 西安航空制动科技有限公司 | Formula flight data recorders housing and preparation method thereof is put in throwing |
| CN105899765A (en) * | 2014-01-09 | 2016-08-24 | 斯奈克玛 | Fire protection of a fan casing made of composite |
| CN110001092A (en) * | 2019-05-16 | 2019-07-12 | 航天特种材料及工艺技术研究所 | A kind of phenolic resin preimpregnation material and metalwork integral formation method |
| CN110216902A (en) * | 2019-06-19 | 2019-09-10 | 湖北菲利华石英玻璃股份有限公司 | A kind of metal rudder core adds the dead size RTM forming method of polymer matrix composites |
| CN113844068A (en) * | 2021-09-18 | 2021-12-28 | 西安昊友航天复合材料有限公司 | Preparation method of high-silica-phenolic resin composite heat-proof plate |
-
2008
- 2008-08-05 CN CN200810041388A patent/CN101642962A/en active Pending
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105899765A (en) * | 2014-01-09 | 2016-08-24 | 斯奈克玛 | Fire protection of a fan casing made of composite |
| CN105069857A (en) * | 2015-07-20 | 2015-11-18 | 西安航空制动科技有限公司 | Flight data recorder casing and preparation method thereof |
| CN105225294A (en) * | 2015-09-15 | 2016-01-06 | 西安航空制动科技有限公司 | Formula flight data recorders housing and preparation method thereof is put in throwing |
| CN110001092A (en) * | 2019-05-16 | 2019-07-12 | 航天特种材料及工艺技术研究所 | A kind of phenolic resin preimpregnation material and metalwork integral formation method |
| CN110216902A (en) * | 2019-06-19 | 2019-09-10 | 湖北菲利华石英玻璃股份有限公司 | A kind of metal rudder core adds the dead size RTM forming method of polymer matrix composites |
| CN113844068A (en) * | 2021-09-18 | 2021-12-28 | 西安昊友航天复合材料有限公司 | Preparation method of high-silica-phenolic resin composite heat-proof plate |
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Open date: 20100210 |