CN103085973A - Carbon fiber rotary wing - Google Patents
Carbon fiber rotary wing Download PDFInfo
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- CN103085973A CN103085973A CN2012105725817A CN201210572581A CN103085973A CN 103085973 A CN103085973 A CN 103085973A CN 2012105725817 A CN2012105725817 A CN 2012105725817A CN 201210572581 A CN201210572581 A CN 201210572581A CN 103085973 A CN103085973 A CN 103085973A
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- rotary wing
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- helicopter
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Abstract
The invention relates to a rotary wing of carbon fiber of a rotary wing helicopter. At present, the manufacture material for the rotary wing helicopter is generally a metal material, the processing requirements are higher, and the processing difficulty is large; the weight of the whole rotary wing is large, the defects such as metal fatigue and non-resisting corrosion are easy to generate, the service life of the rotary wing is influenced, and the safety feature of a plane is influenced. The rotary wing of the helicopter provided by the invention has the characteristics of small density, corrosion resistance, good hardness, high fatigue strength, good rigidity, temperature and cold resistance, and acid and alkali resistance.
Description
Technical field:
The present invention relates to a kind of carbon fiber rotor of going straight up to cyclogyro.
Background technology:
Be used at present going straight up to the metallic material that is generally that rotorcraft rotor is made material, it is had relatively high expectations to Fabricating machinery and processing technology, and difficulty of processing is large, and the weight of whole rotor is large.And steel are long-time use after, easily produce the defectives such as metal fatigue, withstanding corrosion, thermal expansion coefficient be not large, thereby have influence on the service life of rotor, affect the aircraft safety performance.
Summary of the invention:
Purpose of the present invention provides a kind of rotor of heligyro of carbon fiber reinforce plastic, and its weight is light and handy, thermal expansion coefficient is little, good rigidity, high-fatigue strength, heatproof cold, acid and alkali-resistance.
The present invention adopts 3-12K carbon cloth, epoxy resin, T31 curing agent (or 593 curing agent), dibutyl ester, the calculating of compound process raw MAT'L, carbon cloth cutting, artificial outfit, colloid preparation, coating, oven dry, press mold, vacuumizes, solidifies and make.
The technological process of carbon fiber rotor of the present invention is as follows:
1) dead work: cut out in advance the required two-way carbon cloth of each several part according to designed carbon fiber moulded dimension, 3-12K (colloid proportioning corresponding to other K value changes) is got in the unification of two-way carbon cloth standard, institute's cutting carbon cloth is demarcated stand-by with label sequence number, cleaning mould inboard makes it totally level and smooth.
2) add T31 curing agent (or 593 curing agent), dibutyl ester mixing and stirring in epoxy resin, form liquid epoxy resin colloid;
3) consumption of each component of aforementioned epoxy resins glue is: the 20-30%, the dibutyl ester that take epoxy resin as 100%, T31 curing agent are epoxy resin are the 5-10% of epoxy resin.
4) indoor lower than the temperature conditions of 5 ℃ under, the two-way carbon cloth that tiling one deck 12K cuts out in advance on mould, then be coated with one deck step 2) preparation epoxide-resin glue, be right after at the synthetic carbon cloth of surface coverage one deck of epoxy glue layer, then again in surface-coated one deck step 2 of synthetic carbon cloth) epoxide-resin glue of preparation, be right after at the synthetic carbon cloth of this layer epoxy resin layer surface coverage, reciprocal with this, until required thickness.
5) carbon fibre preform that MULTILAYER COMPOSITE is good, with fastener fix and be evacuated after put it into (the large-scale even heat treatment of employing external electric) in baking oven, be heated to 50-70 ℃, be incubated stopped heating after 60-80 minute, take out model after naturally cooling 6-8 hour.
6) open mould, take out in type carbon fiber reinforce plastic goods, after the assay was approved, it is carried out trimming, polishing, can make finished product.
Interests effect of the present invention is by the lifting airscrew that above scheme is made, following advantage to be arranged:
1. hardness is good, and Shao Shi D hardness meter measured value is 95HD;
2. the tension coefficient is high, is 3.5 times of common iron;
3. high elastic modulus, the tensile modulus of elasticity of carbon fiber composite material is higher than steel (but the tensile modulus of elasticity of aramid fiber and glass fiber compound material is only a half-sum 1/4th of steel);
4. high-fatigue strength, the strength at repeated alternation of carbon fiber composite material is higher than high tensile steel wire.Metallic material is under the effect of reverse stress, and fatigue limit is only the 30%-40% of quiet lotus intensity.Due to fiber and the compound Crack Extension that relaxes of matrix, and have fiber internal force reallocation possibility, the fatigue strength limit of composite material is higher, is the 60%-70% of quiet lotus intensity, and the significant sign of distortion is arranged before destruction;
5. density is little, and density is 1.5;
6. cold-resistant-70 ℃, 50 ℃ of heatproofs;
7. acid-alkali-corrosive-resisting;
8. bounce-back property is preferably arranged;
9. thermal expansion coefficient is little, than the little 4-5 of metallic material doubly;
10. good rigidity, for the 2-3 of metallic material doubly.
The specific embodiment:
1) cut out the two-way carbon cloth of 3-12K.
2) take the method for conventional molding to make the upper die and lower die of required size, the mould inboard is cleaned out smoothly.
3) add 593 curing agent, dibutyl ester mixing and stirring in epoxy resin, form liquid epoxy resin colloid;
4) consumption of each component of epoxide-resin glue is: take epoxy resin as 100%, 593 curing agent be epoxy resin 5%, dibutyl ester is 5% of epoxy resin.
5) at counterdie inside face coating one antireflective film layer agent acetone, then be coated with one deck step 4) preparation epoxide-resin glue, be right after at the synthetic carbon cloth of surface coverage one deck of epoxy glue layer, then again in surface-coated one deck step 3 of synthetic carbon cloth) epoxide-resin glue of preparation, be right after at the synthetic carbon cloth of this layer epoxy resin layer surface coverage, reciprocal with this, coating speed is quick, reach required thickness within the time of calculating, upper film and counterdie are closed film, fix and be evacuated with tight round part and be heated to 150 ℃ at indoor electric heater afterwards, be incubated stopped heating after 60 minutes, the cooling nature takes out model after cooling 5 hours.
Open mould, take out in type carbon fiber composite article, after the assay was approved, it is carried out trimming, polishing, can make finished product.
Description of drawings:
1. accompanying drawing 1 is the whole structure figure of rotor product;
2. accompanying drawing 2 is the cross-section analysis figure of rotor.
Claims (10)
1. carbon fiber rotor is characterized in that composite material makes.
2. as claimed in claim 1, it is characterized in that hardness is good, Shao Shi D hardness meter measured value is 95HD.
3. as claimed in claim 1, it is characterized in that the tension coefficient is good, be 3.5 times of common iron.
4. as claimed in claim 1, it is characterized in that good rigidity, for the 2-3 of metallic material doubly.
5. as claimed in claim 1, it is characterized in that thermal expansion coefficient is little, than the little 4-5 of metallic material doubly.
6. as claimed in claim 1, it is characterized in that high-fatigue strength is the 60%-70% of quiet lotus intensity, and the significant sign of distortion is arranged before destruction.
7. as claimed in claim 1, it is characterized in that density is little, density is 1.5.
8. as claimed in claim 1, it is characterized in that resisting cold-70 ℃, 50 ℃ of heatproofs.
9. as claimed in claim 1, it is characterized in that bounce-back is arranged.
10. as claimed in claim 1, it is characterized in that acid-alkali-corrosive-resisting.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2012105725817A CN103085973A (en) | 2012-12-26 | 2012-12-26 | Carbon fiber rotary wing |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2012105725817A CN103085973A (en) | 2012-12-26 | 2012-12-26 | Carbon fiber rotary wing |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN103085973A true CN103085973A (en) | 2013-05-08 |
Family
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN2012105725817A Pending CN103085973A (en) | 2012-12-26 | 2012-12-26 | Carbon fiber rotary wing |
Country Status (1)
| Country | Link |
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| CN (1) | CN103085973A (en) |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101706833A (en) * | 2009-11-25 | 2010-05-12 | 哈尔滨工业大学 | Design method for marine propeller made of carbon fiber composite material |
| CN101706832A (en) * | 2009-11-25 | 2010-05-12 | 哈尔滨工业大学 | Optimization design method of fibre enhanced composite material marine propeller blade |
| CN101704302A (en) * | 2009-11-17 | 2010-05-12 | 哈尔滨工业大学 | Integrally forming mould of composite propeller and manufacture method thereof |
| US20100213320A1 (en) * | 2009-02-20 | 2010-08-26 | Stephen Daynes | Device which is subject to fluid flow |
| CN102795338A (en) * | 2012-07-27 | 2012-11-28 | 北京卫星制造厂 | Micro unmanned aerial vehicle carbon fiber rotor wing and preparation method thereof |
-
2012
- 2012-12-26 CN CN2012105725817A patent/CN103085973A/en active Pending
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20100213320A1 (en) * | 2009-02-20 | 2010-08-26 | Stephen Daynes | Device which is subject to fluid flow |
| CN101704302A (en) * | 2009-11-17 | 2010-05-12 | 哈尔滨工业大学 | Integrally forming mould of composite propeller and manufacture method thereof |
| CN101706833A (en) * | 2009-11-25 | 2010-05-12 | 哈尔滨工业大学 | Design method for marine propeller made of carbon fiber composite material |
| CN101706832A (en) * | 2009-11-25 | 2010-05-12 | 哈尔滨工业大学 | Optimization design method of fibre enhanced composite material marine propeller blade |
| CN102795338A (en) * | 2012-07-27 | 2012-11-28 | 北京卫星制造厂 | Micro unmanned aerial vehicle carbon fiber rotor wing and preparation method thereof |
Non-Patent Citations (5)
| Title |
|---|
| 上海化工学院: "《玻璃钢工艺学》", 31 December 1979, 中国建筑工业出版社 * |
| 建筑考试培训研究中心: "《建筑工程技术与计量》", 31 May 2011 * |
| 张阿樱等: "碳纤维/环氧树脂层压板疲劳性能研究进展", 《玻璃钢/复合材料》 * |
| 施琪: "碳纤维复合材料抗拉性能测试结果的影响因素分析", 《兰州交通大学学报》 * |
| 郁文娟等: "《塑料产品工业设计基础》", 31 January 2007, 化学工业出版社 * |
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| C02 | Deemed withdrawal of patent application after publication (patent law 2001) | ||
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Application publication date: 20130508 |