CN113022039A - High-temperature-resistant composite material missile wing and preparation method thereof - Google Patents
High-temperature-resistant composite material missile wing and preparation method thereof Download PDFInfo
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- CN113022039A CN113022039A CN202110329419.1A CN202110329419A CN113022039A CN 113022039 A CN113022039 A CN 113022039A CN 202110329419 A CN202110329419 A CN 202110329419A CN 113022039 A CN113022039 A CN 113022039A
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B32—LAYERED PRODUCTS
- B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
- B32B5/00—Layered products characterised by the non- homogeneity or physical structure, i.e. comprising a fibrous, filamentary, particulate or foam layer; Layered products characterised by having a layer differing constitutionally or physically in different parts
- B32B5/02—Layered products characterised by the non- homogeneity or physical structure, i.e. comprising a fibrous, filamentary, particulate or foam layer; Layered products characterised by having a layer differing constitutionally or physically in different parts characterised by structural features of a fibrous or filamentary layer
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B32—LAYERED PRODUCTS
- B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
- B32B33/00—Layered products characterised by particular properties or particular surface features, e.g. particular surface coatings; Layered products designed for particular purposes not covered by another single class
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B32—LAYERED PRODUCTS
- B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
- B32B5/00—Layered products characterised by the non- homogeneity or physical structure, i.e. comprising a fibrous, filamentary, particulate or foam layer; Layered products characterised by having a layer differing constitutionally or physically in different parts
- B32B5/22—Layered products characterised by the non- homogeneity or physical structure, i.e. comprising a fibrous, filamentary, particulate or foam layer; Layered products characterised by having a layer differing constitutionally or physically in different parts characterised by the presence of two or more layers which are next to each other and are fibrous, filamentary, formed of particles or foamed
- B32B5/24—Layered products characterised by the non- homogeneity or physical structure, i.e. comprising a fibrous, filamentary, particulate or foam layer; Layered products characterised by having a layer differing constitutionally or physically in different parts characterised by the presence of two or more layers which are next to each other and are fibrous, filamentary, formed of particles or foamed one layer being a fibrous or filamentary layer
- B32B5/26—Layered products characterised by the non- homogeneity or physical structure, i.e. comprising a fibrous, filamentary, particulate or foam layer; Layered products characterised by having a layer differing constitutionally or physically in different parts characterised by the presence of two or more layers which are next to each other and are fibrous, filamentary, formed of particles or foamed one layer being a fibrous or filamentary layer another layer next to it also being fibrous or filamentary
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B32—LAYERED PRODUCTS
- B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
- B32B2260/00—Layered product comprising an impregnated, embedded, or bonded layer wherein the layer comprises an impregnation, embedding, or binder material
- B32B2260/02—Composition of the impregnated, bonded or embedded layer
- B32B2260/021—Fibrous or filamentary layer
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B32—LAYERED PRODUCTS
- B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
- B32B2260/00—Layered product comprising an impregnated, embedded, or bonded layer wherein the layer comprises an impregnation, embedding, or binder material
- B32B2260/04—Impregnation, embedding, or binder material
- B32B2260/046—Synthetic resin
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B32—LAYERED PRODUCTS
- B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
- B32B2262/00—Composition or structural features of fibres which form a fibrous or filamentary layer or are present as additives
- B32B2262/10—Inorganic fibres
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B32—LAYERED PRODUCTS
- B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
- B32B2262/00—Composition or structural features of fibres which form a fibrous or filamentary layer or are present as additives
- B32B2262/10—Inorganic fibres
- B32B2262/101—Glass fibres
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B32—LAYERED PRODUCTS
- B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
- B32B2262/00—Composition or structural features of fibres which form a fibrous or filamentary layer or are present as additives
- B32B2262/10—Inorganic fibres
- B32B2262/106—Carbon fibres, e.g. graphite fibres
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B32—LAYERED PRODUCTS
- B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
- B32B2307/00—Properties of the layers or laminate
- B32B2307/30—Properties of the layers or laminate having particular thermal properties
- B32B2307/306—Resistant to heat
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/40—Weight reduction
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Abstract
The invention relates to a high-temperature resistant composite material missile wing and a preparation method thereof, which mainly comprises a structural layer, a heat insulation layer and an anti-ablation layer, wherein the heat insulation layer is arranged on the surfaces except a front edge, a wing tip and a rear edge; the presence of an anti-ablation layer only at the leading edge, wing tip and trailing edge; the preparation method comprises the following steps: the method comprises the steps of preparing phthalonitrile resin, carbon fiber fabric, glass fiber fabric, high silica fabric and the like into prepreg by using a wet prepreg machine, preparing phthalonitrile resin and high silica chopped fiber into premix by using a stirring kettle, manually paving and pasting a thermal insulation layer on the lower surface into a female die, paving and pasting a structural layer, paving and pasting a thermal insulation layer on the upper surface, manually paving an anti-ablation layer, putting the male die on a press, heating and pressurizing to integrally cure and mold the composite material. The invention has the positive effects that: (1) high temperature resistance; (2) the strength is high; (3) the weight is light; (4) integrally forming; (5) the cost is low.
Description
Technical Field
The invention relates to the technical field of composite materials, in particular to a high-temperature-resistant composite material missile wing for a high-speed missile and a preparation method thereof.
Background
The missile wing bears aerodynamic load and provides lift force in the missile flying process, the aerodynamic heating effect is more and more severe along with the increase of the missile speed, and when the missile flying speed reaches 2 Mach, the front edge stagnation point temperature reaches 100 ℃, 350 ℃ when 3 Mach and more than 1000 ℃ when 5 Mach. At present, the missile wing mainly has structural forms of alloy steel, titanium alloy, aluminum alloy, steel skeleton, composite material skin and the like, the alloy steel structure is heavy, the titanium alloy is high in price and difficult to form, a non-metal material is required to be added on the surface of the missile wing to insulate heat when the temperature is over 500 ℃, the mechanical property of the aluminum alloy is sharply reduced when the temperature is over 300 ℃, and the steel skeleton and composite material skin structure is difficult to assemble. In recent years, many researches on high-temperature resistant composite material missile wings exist, but some composite materials are found to have better mechanical properties but not have ablation resistance, for example, a polyimide resin-based composite material has Tg close to 500 ℃, but is not ablation resistant and expensive, and some composite materials have ablation resistance but have insufficient mechanical properties, for example, a phenolic resin-based composite material also has the problem that the two materials are combined, the surface of the composite material is made of ablation-resistant phenolic resin, and the inside of the composite material is made of polyimide resin with good high-temperature mechanical properties, but the interface between the two materials is adhered. Therefore, a high-temperature resistant composite material missile wing is urgently needed, can meet the bearing requirement at high temperature, and is simple to form, light in weight and low in cost.
Disclosure of Invention
The invention aims to overcome the defects of the prior art and provides a high-temperature-resistant composite material missile wing and a preparation method thereof.
The purpose of the invention is realized by the following technical scheme:
a high-temperature resistant composite material missile wing mainly comprises a structural layer, a heat insulation layer and an anti-ablation layer, wherein the heat insulation layer is arranged on the surfaces except a front edge, a wing tip and a rear edge; only the leading edge, the wing tip and the trailing edge are present with an anti-ablation layer.
The structural layer is carbon fiber fabric or glass fiber fabric/phthalonitrile resin prepreg.
The heat insulation layer is high silica fiber fabric or glass fiber fabric/phthalonitrile resin prepreg.
The ablation resistant layer is high silica chopped fiber/phthalonitrile resin premix.
The resin used for the structural layer, the heat insulation layer and the ablation resistant layer of the missile wing are the same, and are all phthalonitrile and other resin systems containing CN triple bonds, the resin has good high-temperature mechanical properties, the Tg is more than or equal to 350 ℃, the ablation resistant performance is excellent, the linear ablation rate is 0.083mm/s (about 0.1mm/s of phenolic resin), the carbon residue rate during ablation at 900 ℃ is more than or equal to 70%, the heat insulation performance is also good, and the heat conductivity is 0.4W/m.K.
Hollow fillers such as glass beads and phenolic microspheres are added into the prepreg of the heat insulation layer, so that the heat conductivity of the heat insulation layer is less than or equal to 0.5W/m.K, and the thickness of the heat insulation layer is more than or equal to 0.5 mm.
The thickness of the ablation-resistant layer is more than or equal to 10 mm.
A preparation method of a high-temperature-resistant composite material missile wing comprises the steps of preparing a prepreg from phthalonitrile resin, a carbon fiber fabric, a glass fiber fabric, a high silica fabric and the like by using a wet prepreg machine, preparing a premix from phthalonitrile resin and high silica chopped fibers by using a stirring kettle, manually paving a heat insulation layer on the lower surface in a female die, paving a structural layer, paving a heat insulation layer on the upper surface, manually paving an anti-ablation layer, closing the male die, placing the male die on a press, heating and pressurizing to integrally cure and mold the composite material missile wing.
The forming die consists of a female die, a male die, a top die block and a limiting block.
The front edge, the wing tip and the rear edge are directly molded to the specified size by compression, at least 10mm of allowance needs to be reserved in the wing root area, and the specified size is machined after molding.
Compared with the prior art, the invention has the following positive effects:
(1) high temperature resistance;
(2) the strength is high;
(3) the weight is light;
(4) integrally forming;
(5) the cost is low.
Drawings
FIG. 1 is a block diagram of the present invention;
FIG. 2 is an enlarged cross-sectional view of the present invention;
FIG. 3 is a schematic view of a forming die used in the present invention;
the labels in the figures are: 1. a structural layer; 2. a thermal insulation layer; 3 an ablation resistant layer; 4. a female die; 5, a top module; 6. a limiting block; 7. a male mold.
Detailed Description
The following provides a specific embodiment of the high temperature resistant composite missile wing and the preparation method thereof.
Example 1
The embodiment provides a high-temperature-resistant composite missile wing, as shown in fig. 1 and 2, the missile wing is composed of a structural layer 1, a heat insulation layer 2 and an anti-ablation layer 3. The structural layer 1 is a carbon fiber fabric (or a glass fiber fabric)/phthalonitrile resin prepreg, the heat insulation layer 2 is a high silica fiber fabric (or a glass fiber fabric)/phthalonitrile resin prepreg, and the anti-ablation layer 3 is a high silica chopped fiber/phthalonitrile resin premix.
And determining the material, the number of layers and the angle of the structural layer 1 by using Patran and Nastran strength calculation software according to the requirements of the shape, the load, the strength and the rigidity of the missile wing.
The temperature field and the ablation amount were simulated using Ansys software, and the thickness of the thermal insulation layer 2 and the ablation resistant layer 3 was determined by a blow test.
And drawing a missile wing digital model and a layering diagram by using CATIA three-dimensional software.
And drawing a digital-analog model of the missile wing forming die by using CATIA three-dimensional software, wherein the forming die consists of a female die 4, a male die 7, a top die block 5 and a limiting block 6.
The preparation method of the high-temperature-resistant composite material missile wing in the embodiment mainly comprises the following steps:
(1) the prepreg is prepared from phthalonitrile resin, carbon fiber fabric, glass fiber fabric, high silica fabric and the like by using a wet prepreg machine.
(2) And (3) preparing the phthalonitrile resin and the high-silica chopped fibers into a premix by using a stirring kettle.
(3) In the female die 4, the thermal insulation layer 2 on the lower surface of the missile wing is manually paved.
(4) And paving and pasting the structural layer 1.
(5) And a heat insulation layer 2 is paved and attached to the upper surface of the missile wing.
(6) The ablation-resistant layer 3 was spread manually.
(7) After the male mold 7 is closed, the mold is placed on a press, and is cured and molded by heating and pressurizing.
(8) After the mold is opened, the ejection module 5 is used for ejecting the missile wing.
(9) The wing root area was machined to specified dimensions using a numerically controlled milling machine.
The foregoing is only a preferred embodiment of the present invention, and it should be noted that, for those skilled in the art, several modifications and decorations can be made without departing from the concept of the present invention, and these modifications and decorations should also be regarded as being within the protection scope of the present invention.
Claims (10)
1. A high-temperature resistant composite material missile wing is characterized by mainly comprising a structural layer, a heat insulation layer and an anti-ablation layer, wherein the heat insulation layer is arranged on the surfaces except a front edge, a wing tip and a rear edge; only the leading edge, the wing tip and the trailing edge are present with an anti-ablation layer.
2. The high temperature resistant composite missile wing of claim 1, wherein the structural layer is carbon fiber fabric or glass fiber fabric/phthalonitrile resin prepreg.
3. The high temperature resistant composite missile wing of claim 1, wherein the thermal insulation layer is a high silica fiber fabric or a glass fiber fabric/phthalonitrile resin prepreg.
4. The high temperature resistant composite missile wing of claim 1, wherein the ablation resistant layer is a high silica chopped fiber/phthalonitrile resin premix.
5. The high-temperature-resistant composite material missile wing as claimed in claim 1, wherein the structural layer, the thermal insulation layer and the ablation-resistant layer of the missile wing are made of the same resin, and are all a phthalonitrile resin system containing CN triple bonds, the resin has good high-temperature mechanical properties, Tg is not less than 350 ℃, the ablation-resistant properties are excellent, the linear ablation rate is 0.083mm/s, the residual carbon rate during ablation at 900 ℃ is not less than 70%, the thermal insulation properties are also good, and the thermal conductivity is 0.4W/m.K.
6. The high-temperature-resistant composite material missile wing as claimed in claim 1, wherein the prepreg of the thermal insulation layer is added with hollow fillers such as glass beads and phenolic microspheres, so that the thermal conductivity of the thermal insulation layer is less than or equal to 0.5W/m.K, and the thickness of the thermal insulation layer is more than or equal to 0.5 mm.
7. The high temperature resistant composite missile wing of claim 1, wherein the thickness of the ablation resistant layer is more than or equal to 10 mm.
8. A preparation method of a high-temperature-resistant composite material missile wing is characterized by comprising the steps of preparing a prepreg from phthalonitrile resin, a carbon fiber fabric, a glass fiber fabric, a high silica fabric and the like by using a wet prepreg machine, preparing a premix from phthalonitrile resin and high silica chopped fibers by using a stirring kettle, manually paving a heat insulation layer on the lower surface in a female die, paving a structural layer, paving a heat insulation layer on the upper surface, manually paving an anti-ablation layer, closing a male die, placing the male die on a press, heating and pressurizing to integrally cure and mold the male die.
9. The method for preparing the high-temperature-resistant composite material missile wing according to claim 8, wherein the forming die consists of a female die, a male die, a top die block and a limiting block.
10. The method of claim 8, wherein the leading edge, the wing tip and the trailing edge are directly molded to a predetermined size, a margin of at least 10mm is reserved in the wing root area, and the molded wing is mechanically added to the predetermined size.
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| Application Number | Priority Date | Filing Date | Title |
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| CN202110329419.1A CN113022039B (en) | 2021-03-28 | 2021-03-28 | High-temperature-resistant composite material missile wing and preparation method thereof |
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| CN202110329419.1A CN113022039B (en) | 2021-03-28 | 2021-03-28 | High-temperature-resistant composite material missile wing and preparation method thereof |
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| CN113022039B CN113022039B (en) | 2022-08-12 |
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Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113246339A (en) * | 2021-07-15 | 2021-08-13 | 北京航天天美科技有限公司 | Laminated carbon fiber reinforced prepreg material and method for forming coated missile wing by using same |
| CN113787735A (en) * | 2021-11-15 | 2021-12-14 | 北京玻钢院复合材料有限公司 | Composite material grid product and preparation method thereof |
| CN113997591A (en) * | 2021-11-16 | 2022-02-01 | 航天特种材料及工艺技术研究所 | Three-dimensional reticular structure resin-based heat-proof layer and preparation method and application thereof |
| CN114085524A (en) * | 2021-11-18 | 2022-02-25 | 航天特种材料及工艺技术研究所 | Structural bearing-ablation integrated phthalonitrile resin prepreg, composite material and preparation method thereof |
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| CN107791636A (en) * | 2017-10-25 | 2018-03-13 | 哈尔滨工业大学 | A kind of multi-layered anti-yaw damper composite and preparation method thereof |
| CN108454135A (en) * | 2018-01-31 | 2018-08-28 | 航天材料及工艺研究所 | A kind of o-phthalonitrile resin prepreg, composite material and preparation method |
| CN111707145A (en) * | 2020-06-10 | 2020-09-25 | 宁波曙翔新材料股份有限公司 | Loading, ablation and heat-proof integrated composite material missile wing and rudder for hypersonic missile and preparation method thereof |
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2021
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| CN107791636A (en) * | 2017-10-25 | 2018-03-13 | 哈尔滨工业大学 | A kind of multi-layered anti-yaw damper composite and preparation method thereof |
| CN108454135A (en) * | 2018-01-31 | 2018-08-28 | 航天材料及工艺研究所 | A kind of o-phthalonitrile resin prepreg, composite material and preparation method |
| CN111707145A (en) * | 2020-06-10 | 2020-09-25 | 宁波曙翔新材料股份有限公司 | Loading, ablation and heat-proof integrated composite material missile wing and rudder for hypersonic missile and preparation method thereof |
Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113246339A (en) * | 2021-07-15 | 2021-08-13 | 北京航天天美科技有限公司 | Laminated carbon fiber reinforced prepreg material and method for forming coated missile wing by using same |
| CN113246339B (en) * | 2021-07-15 | 2021-09-21 | 北京航天天美科技有限公司 | Carbon fiber reinforced prepreg material and method for forming coated missile wing by using same |
| CN113787735A (en) * | 2021-11-15 | 2021-12-14 | 北京玻钢院复合材料有限公司 | Composite material grid product and preparation method thereof |
| CN113997591A (en) * | 2021-11-16 | 2022-02-01 | 航天特种材料及工艺技术研究所 | Three-dimensional reticular structure resin-based heat-proof layer and preparation method and application thereof |
| CN113997591B (en) * | 2021-11-16 | 2023-04-25 | 航天特种材料及工艺技术研究所 | Three-dimensional reticular structure resin-based heat-resistant layer and preparation method and application thereof |
| CN114085524A (en) * | 2021-11-18 | 2022-02-25 | 航天特种材料及工艺技术研究所 | Structural bearing-ablation integrated phthalonitrile resin prepreg, composite material and preparation method thereof |
| CN114085524B (en) * | 2021-11-18 | 2023-09-29 | 航天特种材料及工艺技术研究所 | Structural bearing-ablation integrated phthalonitrile resin prepreg, composite material and preparation method thereof |
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Address after: 312000 Building 2, Haitu jiuyiqiu, Binhai Industrial Zone, Keqiao District, Shaoxing City, Zhejiang Province Patentee after: Shaoxing Baojing composite material Co.,Ltd. Patentee after: Shaoxing Baojing Composite Technology Research and Development Co.,Ltd. Address before: 312030 Building 2, jiuyiqiu, Haitu, Binhai Industrial Zone, Shaoxing City, Zhejiang Province Patentee before: Shaoxing Baojing composite material Co.,Ltd. Patentee before: JINGGONG (SHAOXING) COMPOSITE TECHNOLOGY R & D CO.,LTD. |