CN104877303A - Anti-erosion and anti-ablation material suitable for oxygen-rich environment - Google Patents
Anti-erosion and anti-ablation material suitable for oxygen-rich environment Download PDFInfo
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- CN104877303A CN104877303A CN201410070400.XA CN201410070400A CN104877303A CN 104877303 A CN104877303 A CN 104877303A CN 201410070400 A CN201410070400 A CN 201410070400A CN 104877303 A CN104877303 A CN 104877303A
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Abstract
The invention relates to an anti-erosion and anti-ablation material suitable for an oxygen-rich environment, wherein the material comprises 30-50 parts of a high temperature resistance phenol formaldehyde resin, 2-5 parts of carbon fibers, 1-5 parts of aramid fibers, 0-30 parts of silicon carbide, and 0-25 parts of a high temperature resistance oxide filler. The anti-erosion and anti-ablation material of the present invention has characteristics of excellent erosion resistance, excellent ablation resistance, high strength, and good anti-oxidation performance, and can meet requirements of the gas suction type rocket engine with the work time exceeding 400 s.
Description
Technical field
The present invention relates to the matrix material of the resistance to ablation of a kind of antiscour for oxygen-enriched environment, as airbreathing motor housing and engine jet pipe etc., belong to rocket engine thermal protection field.
Background technology
Antiscour ablation resistant material is generally used in rocket engine, comprises jet pipe and the metal shell of engine.Rocket engine to produce in the course of the work several thousand degree high-temperature fuel gas and with a large amount of metallicss as magnesium, aluminium, boron etc.; combustion gas and particle will produce violent ablation and wash away to metallic walls, burn the ablation resistant material needing to adhere at engine inner wall one deck antiscour protect it for preventing engine metal housing.At present, conventional rocket engine metal shell thermal insulation material is for forming through paster sulfuration in engine for base material adds the fiber of resistance to ablation such as aramid fiber or carbon fiber etc. with EPDM rubber.EPDM rubber heat-insulating material will speed up its oxygenolysis under oxygen-enriched environment, cannot bear washing away and ablation of a large amount of metallics, finds through test, and EPDM material cannot meet rocket engine under oxygen-enriched environment and to work long hours requirement.DC93-104 trade mark material is used for THERMAL PROTECTION OF SCRAMJET, this material main ingredient is organopolysiloxane elastomerics, fills silicon-dioxide, long carbon fiber, silicon carbide and solidifying agent etc., this strength of materials is 0.29MPa, testing oxyacetylene ablation rate by ASTM E285 is 0.0625mm/s, and burn through time is 97s.Above-mentioned bi-material can not meet excessive oxygen to its strong oxygenolysis, can not meet the requirement to its violent scour and ablation of particle under the engine long working hour.
Summary of the invention
The object of the invention is to solve the above-mentioned deficiency of prior art, a kind of antiscour ablation resistant material being applicable to oxygen-enriched environment can resisted combustion gas ablation and metallics for a long time and wash away is provided.
The antiscour ablation resistant material being applicable to oxygen-enriched environment of the present invention comprises following component and mass fraction: (apart from outside explanation, the ratio adopted in the present invention is weight ratio)
Modified phenolic resins: 30 ~ 50 parts;
Carbon fiber: 2 ~ 5 parts;
Aramid fiber: 1 ~ 5 part;
Silicon carbide: 0 ~ 30 part;
High temperature resistant filler: 0 ~ 25 part.
Modified phenolic resins is modified, high temperature resistant resol.
Described carbon fiber is >=5mm chopped carbon fiber.
Described silicon carbide is technical grade green silicon carbide powder.
Described aramid fiber is pulp or fibre shape.
Described high temperature resistant filler is inorganic high-temperature resistant metal oxide.
Described high temperature resistant filler is one or more in magnesium oxide, aluminum oxide, silicon-dioxide, zirconium white, calcium oxide, ferric oxide, chromium sesquioxide.
Preparation technology of the present invention comprises: add in mixing machine after modified phenolic resins, carbon fiber, aramid fiber, silicon carbide, refractory oxide being weighed in proportion, start mixing machine, above-mentioned material is rotated by stirring rake in mixing machine hopper mix fully, churning time controls in 30 ~ 50 min, the material mixed is taken out and is placed in clean place, solvent in resol is fully volatilized, makes prepreg.Prepreg is pressed into work in-process, puts into mould, vulcanizing press solidifies 50 ~ 180min at about 150 ~ 180 DEG C, namely plastic.
The invention solves current material in high-temperature oxygen-enriched combustion gas environment and cannot ensure the problem of rocket motor case structural integrity, beneficial effect compared with prior art:
(1) composite material strength of the present invention is high, and antioxidant property is good, have excellent antiscour and anti-yaw damper performance, can meet the air-breathing rocket engine job requirement of working hour more than 400s.
(2) matrix material of the present invention adopts modified phenolic resins, has good thermotolerance, flame retardant resistance, ablation resistance and adhesive property.
(3) matrix material of the present invention adopts chopped carbon fiber and the aramid fiber of resistance to ablation, has both improve the anti-yaw damper performance of material, and has in turn enhanced the intensity of matrix material.
(4) matrix material of the present invention adopts silicon carbide and refractory oxide to combinationally use, and improves resistance to elevated temperatures and the antioxidant property of matrix material.
Embodiment
The following describes embodiments of the invention, but the present invention is not limited only to following embodiment.
Table 1 ~ table 6 is specific embodiments, and the number in embodiment is mass fraction.
Embodiment 1
Table 1
| Title | Mass fraction |
| Modified phenolic resins | 30 |
| Silicon carbide | 20 |
| Magnesium oxide | 15 |
| Aramid fiber | 2 |
| Chopped carbon fiber | 3 |
Embodiment 2
Table 2
| Title | Mass fraction |
| Modified phenolic resins | 40 |
| Silicon carbide | 10 |
| Aluminum oxide | 0 |
| Aramid fiber | 5 |
| Chopped carbon fiber | 5 |
Embodiment 3
Table 3
| Title | Mass fraction |
| Modified phenolic resins | 50 |
| Silicon carbide | 10 |
| Aluminum oxide | 10 |
| Aramid fiber | 4.5 |
| Chopped carbon fiber | 3 |
Embodiment 4
Table 4
| Title | Mass fraction |
| Modified phenolic resins | 50 |
| Silicon carbide | 10 |
| Silicon-dioxide | 10 |
| Aramid fiber | 4.5 |
| Chopped carbon fiber | 3 |
Embodiment 5
Table 5
| Title | Mass fraction |
| Modified phenolic resins | 35 |
| Silicon carbide | 15 |
| Chromium sesquioxide | 10 |
| Aramid fiber | 4.5 |
| Chopped carbon fiber | 2.5 |
Embodiment 6
Table 6
| Title | Mass fraction |
| Modified phenolic resins | 45 |
| Silicon carbide | 0 |
| Ferric oxide | 15 |
| Aramid fiber | 4 |
| Chopped carbon fiber | 2.5 |
Embodiment 1 ~ 6 material property
| Project name | Unit | Measured value |
| Density | g/cm 3 | 1.50～1.85 |
| Ablation rate | mm/s | 0.03～0.05 |
| Tensile strength | MPa | 20～35 |
| Thermal conductivity | W/m.k | 0.4～0.5 |
In specification sheets, unaccomplished matter belongs to technology as well known to those skilled in the art.
Claims (7)
1. be applicable to an antiscour ablation resistant material for oxygen-enriched environment, it is characterized in that comprising following component and mass fraction:
Modified phenolic resins: 30 ~ 50 parts;
Carbon fiber: 2 ~ 5 parts;
Aramid fiber: 1 ~ 5 part;
Silicon carbide: 0 ~ 30 part;
High temperature resistant filler: 0 ~ 25 part.
2. a kind of antiscour ablation resistant material being applicable to oxygen-enriched environment according to claim 1, is characterized in that carbon fiber is >=5mm chopped carbon fiber.
3. a kind of antiscour ablation resistant material being applicable to oxygen-enriched environment according to claim 1, is characterized in that silicon carbide is technical grade green silicon carbide powder.
4. a kind of antiscour ablation resistant material being applicable to oxygen-enriched environment according to claim 1, is characterized in that aramid fiber is pulp or fibre shape.
5. a kind of antiscour ablation resistant material being applicable to oxygen-enriched environment according to claim 1, is characterized in that described high temperature resistant filler is inorganic high-temperature resistant metal oxide.
6. a kind of antiscour ablation resistant material being applicable to oxygen-enriched environment according to claim 1, is characterized in that described high temperature resistant filler is one or more in magnesium oxide, aluminum oxide, silicon-dioxide, zirconium white, calcium oxide, ferric oxide, chromium sesquioxide.
7. the preparation technology being applicable to the antiscour ablation resistant material of oxygen-enriched environment according to claim 1, it is characterized in that: add in mixing machine after modified phenolic resins, carbon fiber, aramid fiber, silicon carbide, refractory oxide are weighed in proportion, start mixing machine, above-mentioned material is rotated by stirring rake in mixing machine hopper mix fully, churning time controls in 30 ~ 50 min, the material mixed is taken out and is placed in clean place, solvent in resol is fully volatilized, makes prepreg; Prepreg is pressed into work in-process, puts into mould, vulcanizing press solidifies 50 ~ 180min at about 150 ~ 180 DEG C, namely plastic.
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| Application Number | Priority Date | Filing Date | Title |
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| CN201410070400.XA CN104877303B (en) | 2014-02-28 | 2014-02-28 | A kind of antiscour ablation resistant material suitable for oxygen-enriched environment |
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| CN201410070400.XA CN104877303B (en) | 2014-02-28 | 2014-02-28 | A kind of antiscour ablation resistant material suitable for oxygen-enriched environment |
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| CN104877303A true CN104877303A (en) | 2015-09-02 |
| CN104877303B CN104877303B (en) | 2018-01-05 |
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Cited By (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105261437A (en) * | 2015-09-15 | 2016-01-20 | 苏州凯欧曼新材料科技有限公司 | Preparation method of heat-resistant composite magnetic material |
| CN106609037A (en) * | 2015-11-05 | 2017-05-03 | 湖北航天化学技术研究所 | Solvent-free silicon-based ablation-resistant material |
| CN107189309A (en) * | 2017-06-01 | 2017-09-22 | 苏州蔻美新材料有限公司 | A kind of preparation method of magnesium oxide modified poly- aryl ethane resin high temperature resistant composite |
| CN107353583A (en) * | 2017-06-01 | 2017-11-17 | 苏州蔻美新材料有限公司 | A kind of preparation method of magnesium oxide modified boron bakelite resin high temperature resistant composite |
| CN108178897A (en) * | 2017-12-18 | 2018-06-19 | 北京卫星制造厂 | A kind of superhigh intensity thermal insulation material and preparation method thereof |
| CN108821788A (en) * | 2018-07-24 | 2018-11-16 | 合肥岑遥新材料科技有限公司 | A kind of corrosion resistant ceramic matric composite and preparation method thereof |
| CN109354822A (en) * | 2018-11-14 | 2019-02-19 | 长春工业大学 | A kind of preparation method of calcination carbon oxide fiber enhancing phenolic resin friction composite material |
| CN109868057A (en) * | 2017-12-01 | 2019-06-11 | 辽宁法库陶瓷工程技术研究中心 | A kind of fiber reinforcement antiscour ablation surface and the preparation method and application thereof |
| CN109868056A (en) * | 2017-12-01 | 2019-06-11 | 辽宁法库陶瓷工程技术研究中心 | A kind of melting antiscour ablation surface and preparation method thereof |
| CN109868028B (en) * | 2017-12-01 | 2021-12-24 | 辽宁省轻工科学研究院有限公司 | Anti-erosion ablation coating and preparation method thereof |
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Cited By (13)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105261437A (en) * | 2015-09-15 | 2016-01-20 | 苏州凯欧曼新材料科技有限公司 | Preparation method of heat-resistant composite magnetic material |
| CN106609037A (en) * | 2015-11-05 | 2017-05-03 | 湖北航天化学技术研究所 | Solvent-free silicon-based ablation-resistant material |
| CN107189309A (en) * | 2017-06-01 | 2017-09-22 | 苏州蔻美新材料有限公司 | A kind of preparation method of magnesium oxide modified poly- aryl ethane resin high temperature resistant composite |
| CN107353583A (en) * | 2017-06-01 | 2017-11-17 | 苏州蔻美新材料有限公司 | A kind of preparation method of magnesium oxide modified boron bakelite resin high temperature resistant composite |
| CN109868056A (en) * | 2017-12-01 | 2019-06-11 | 辽宁法库陶瓷工程技术研究中心 | A kind of melting antiscour ablation surface and preparation method thereof |
| CN109868056B (en) * | 2017-12-01 | 2021-12-31 | 辽宁省轻工科学研究院有限公司 | Melting erosion-resistant ablation coating and preparation method thereof |
| CN109868028B (en) * | 2017-12-01 | 2021-12-24 | 辽宁省轻工科学研究院有限公司 | Anti-erosion ablation coating and preparation method thereof |
| CN109868057A (en) * | 2017-12-01 | 2019-06-11 | 辽宁法库陶瓷工程技术研究中心 | A kind of fiber reinforcement antiscour ablation surface and the preparation method and application thereof |
| CN108178897B (en) * | 2017-12-18 | 2020-07-14 | 北京卫星制造厂 | Ultrahigh-strength heat-insulating material and preparation method thereof |
| CN108178897A (en) * | 2017-12-18 | 2018-06-19 | 北京卫星制造厂 | A kind of superhigh intensity thermal insulation material and preparation method thereof |
| CN108821788A (en) * | 2018-07-24 | 2018-11-16 | 合肥岑遥新材料科技有限公司 | A kind of corrosion resistant ceramic matric composite and preparation method thereof |
| CN109354822A (en) * | 2018-11-14 | 2019-02-19 | 长春工业大学 | A kind of preparation method of calcination carbon oxide fiber enhancing phenolic resin friction composite material |
| CN109354822B (en) * | 2018-11-14 | 2021-02-12 | 长春工业大学 | Preparation method of firing oxidized carbon fiber reinforced phenolic resin friction composite material |
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| CN104877303B (en) | 2018-01-05 |
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Inventor after: Chen Chunjuan Inventor after: Zhang Honglei Inventor after: Li Yang Inventor after: Wang Jiang Inventor after: Peng Zhenggui Inventor after: Zhao Zhixiang Inventor after: Zhan Kong Inventor after: Song Dan Inventor before: Chen Chunjuan Inventor before: Zhang Honglei Inventor before: Wang Jiang Inventor before: Peng Zhenggui Inventor before: Zhao Zhixiang Inventor before: Zhan Kong Inventor before: Song Dan |