CN114311868A - Composite material heat shield - Google Patents
Composite material heat shield Download PDFInfo
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- CN114311868A CN114311868A CN202111591965.9A CN202111591965A CN114311868A CN 114311868 A CN114311868 A CN 114311868A CN 202111591965 A CN202111591965 A CN 202111591965A CN 114311868 A CN114311868 A CN 114311868A
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Abstract
The invention belongs to the field of aerospace heat insulation materials, and discloses a composite material heat shield which comprises a heat insulation layer and a heat insulation disc, wherein the heat insulation layer is made of a composite material; arranging a heat insulation layer in the maximum heat flow direction of the heat insulation disc; wherein, the insulating layer is SiO2 aerogel/fibre sandwich structure, and the heat insulating dish is the multilayer composite construction that adopts the one-shot integrated moulding of coinjection RTM technology. The invention realizes a heat insulation component with low density, high specific strength, high toughness and excellent heat insulation performance. The invention is suitable for the hot end heat insulation component of the spacecraft, has the characteristics of low density, high specific surface area, high porosity, low heat conductivity and the like, overcomes the defects of difficult process processing, low reliability and the like of the injection temperature and the curing system of two different resins, solves the difficulty of integrated design of the heat insulation component, meets the structural strength of the component, and effectively reduces the heat conductivity coefficient and the weight.
Description
Technical Field
The invention belongs to the field of aerospace heat insulation materials, and relates to a composite material heat insulation disc.
Background
With the development of aerospace technology, space technology has become a highly competitive high-precision technology in all countries, and all countries have more and more attentions for the development of aircrafts, and the heat protection and heat insulation problem is one of the most critical factors for determining the safety of aircrafts to complete various tasks. Because the aircraft is in maneuvering flight in the atmosphere for a long time at a high Mach number, the pneumatic heating is serious and durable, and the pneumatic thermal environment is low in enthalpy, low in heat flux density and long-time heating, the thermal protection material is required to have good ablation resistance and good heat insulation performance, and meanwhile, the thermal protection material needs to have high mechanical property and low density.
The heat-insulating material is adopted as the heat-insulating layer in the higher temperature area and the lower temperature area of the space shuttle, and through development for many years, the heat-insulating material system and the structure are greatly improved, and the heat-insulating material system and the structure which are high temperature resistant, light in weight and good in reliability and can be repeatedly used play a very important role in improving the performance of the space shuttle, so that the research of the heat-proof heat-insulating material with high temperature resistance and better performance is a key point and a hot point of international controversial research in order to meet the high performance requirements of a new generation of aircraft such as ultrahigh speed, maneuvering flight, repeated use and the like.
Disclosure of Invention
In order to solve the problems, the invention provides the composite material heat shield which is light in weight, high-temperature resistant, ablation resistant and high in mechanical property.
The technical scheme of the invention is as follows:
a composite heat shield comprises a heat insulating layer and a heat insulating disc; arranging a heat insulation layer in the maximum heat flow direction of the heat insulation disc; wherein, the insulating layer is SiO2 aerogel/fibre sandwich structure, and the heat insulating dish is the multilayer composite construction that adopts the one-shot integrated moulding of coinjection RTM technology.
Furthermore, the heat insulation layer is of a multilayer structure made of composite materials, and a SiO2 aerogel/fiber sandwich structure is adopted.
Further, the heat insulation layer comprises a bearing layer, a reinforcing layer and a heat-proof layer; wherein the bearing layer is arranged on the upper surface of the reinforcing layer, and the heat-proof layer is arranged on the lower surface of the reinforcing layer and is contacted with the heat-insulating disc; the bearing layer, the reinforcing layer and the heat-proof layer adopt aluminosilicate high-temperature resistant inorganic glue as an adhesive, the liquid phase of the aluminosilicate high-temperature resistant inorganic glue is aluminosilicate solution, and the solid phase and the solidified bonding closed die are pressed and formed.
Furthermore, the bearing layer is made of carbon/epoxy composite material with high specific strength and high specific modulus, so that the weight of the structure can be reduced on the premise of meeting the main bearing requirement.
Furthermore, the reinforcing layer is of an aluminum honeycomb core structure, and SiO2 aerogel is filled in the reinforcing layer. The enhancement layer is aluminium honeycomb core layer, and the advantage is that structural strength is higher when light in weight to because the service temperature is higher, consequently choose aluminium as the preparation material for use.
Further, the heat-proof layer is an aluminum silicate fiber three-dimensional space woven laminate or a carbon/phenolic composite material. The composite material is one of resin-based ablation-resistant materials with the most excellent comprehensive performance, and aims to furthest exert the ablation heat-proof function on the basis of certain bearing performance.
Furthermore, the heat insulation disc is of a multilayer composite structure and comprises a bearing framework, a sandwich plate and a heat-proof plate, the bearing framework is filled with the sandwich plate, and the heat-proof plate is bonded to the outer layer at last.
Furthermore, the bearing framework is made of carbon/epoxy composite material, the sandwich plate is made of aluminum silicate sandwich structure composite material, and the heat-proof plate is made of carbon/phenolic aldehyde composite material.
Further, a bearing framework and a heat-proof plate which are used as a bearing are subjected to coinjection by adopting a coinjection RTM (resin transfer molding) process, high-temperature adhesives are adhered to the inner wall surface and the outer wall surface of the sandwich plate, and then curing is carried out, so that the bearing/heat-proof integrated heat-insulation plate is integrally prepared at one time.
The invention has the advantages that:
1. with the development of space technology, the thermal insulation material taking the composite material as the main body has the advantages of light weight, high temperature resistance, high reliability and greatly improved mechanical property, thereby meeting the requirements of the ultra-high-speed and high-maneuverability aircraft in the sweat pore aerospace field. Therefore, the composite material is highly concerned by the world aerospace strong nation, and is popularized and applied to space vehicles, rockets, missiles and aviation turbofan engines step by step.
2. The invention overcomes the defects of complex structural design and heavy weight of the aerospace vehicle heat insulation component, and solves the problems of low precision, difficult processing, serious corrosion and abrasion and low reliability of the SiO2 aerogel/fiber composite material.
Drawings
FIG. 1 is a schematic diagram of the general structure of the present invention;
FIG. 2 is a schematic A-A diagram of FIG. 1;
FIG. 3 is a schematic view of the composite heat shield of the present invention;
FIG. 4 is a schematic view of the honeycomb insulation structure of the present invention;
the heat insulation plate comprises 1-a heat insulation layer, 2-a heat insulation plate, 1-a bearing layer, 1-2-a reinforcing layer, 1-3-a heat protection layer, 2-1-a bearing framework, 2-3-a sandwich plate and 2-3-a heat protection plate.
Detailed Description
This section is an example of the present invention and is provided to explain and illustrate the technical solutions of the present invention.
The composite material heat shield is characterized by comprising a heat insulation layer 1 and a heat insulation disc 2; a heat insulation layer 1 is arranged in the maximum direction of heat flow of the heat insulation disc 2; wherein, the heat insulating layer 1 is a SiO2 aerogel/fiber sandwich structure, and the heat insulating plate 2 is a multi-layer composite structure integrally formed at one time by adopting a coinjection RTM process.
The heat insulation layer 1 is a multilayer structure made of composite materials and is of a SiO2 aerogel/fiber sandwich structure.
The heat insulation layer 1 comprises a bearing layer 1-1, a reinforcing layer 1-2 and a heat protection layer 1-3; wherein, the bearing layer 1-1 is arranged on the upper surface of the reinforced layer 1-2, and the heat-proof layer 1-3 is arranged on the lower surface of the reinforced layer 1-2 and is contacted with the heat insulation disc 2; the bearing layer 1-1, the reinforcing layer 1-2 and the heat-proof layer 1-3 adopt aluminosilicate high-temperature resistant inorganic glue as an adhesive, the liquid phase of the aluminosilicate high-temperature resistant inorganic glue is aluminosilicate solution, and the solid phase and the solidified bonding closed die are pressed and molded.
The material of the bearing layer 1-1 is carbon/epoxy composite material with high specific strength and high specific modulus, so that the weight of the structure can be reduced on the premise of meeting the main bearing requirement.
The reinforcing layer 1-2 is an aluminum honeycomb core structure, and SiO2 aerogel is filled in the reinforcing layer. The enhancement layer is aluminium honeycomb core layer, and the advantage is that structural strength is higher when light in weight to because the service temperature is higher, consequently choose aluminium as the preparation material for use.
The heat-proof layers 1-3 are aluminum silicate fiber three-dimensional space braided laminates or carbon/phenolic aldehyde composite materials. The composite material is one of resin-based ablation-resistant materials with the most excellent comprehensive performance, and aims to furthest exert the ablation heat-proof function on the basis of certain bearing performance.
The heat insulation disc 2 is of a multilayer composite structure and comprises a bearing framework 2-1, a sandwich plate 2-2 and a heat-proof plate 2-3, wherein the bearing framework 2-1 is filled with the sandwich plate 2-2, and finally the heat-proof plate 2-3 is bonded on the outer layer.
The bearing framework 2-1 is a carbon/epoxy composite material, the sandwich plate 2-2 is an aluminum silicate sandwich structure composite material, and the heat-proof plate 2-3 is a carbon/phenolic aldehyde composite material.
The bearing framework 2-1 and the heat-proof plate 2-3 which are used as the bearing are injected together by adopting a joint injection RTM process, the high-temperature adhesive is stuck on the inner wall surface and the outer wall surface of the sandwich plate 2-2, and then the curing is carried out, so that the bearing/heat-proof integrated heat-proof plate 2 is integrally prepared at one time.
For a better understanding of the present invention, reference is made to the following detailed description taken in conjunction with the accompanying drawings.
Please refer to fig. 1 and 2, which are schematic diagrams of the composite heat shield structure and the honeycomb heat insulation structure according to the present invention.
The composite heat shield is formed as follows:
the composite material heat shield adopts an integrated design technology to carry out a layered structure design on the heat insulation disc and the heat insulation layer. The heat insulation layer and the heat insulation plate are formed by solidifying and bonding DB5012 aluminosilicate high-temperature resistant inorganic glue.
The heat insulation layer is designed into an aluminum silicate fiber sandwich structure, the heat insulation plate is a SiO2 aerogel/aluminum silicate fiber three-dimensional space braided laminate, and SiO2 aerogel is a filling material; the reinforcing layer is an aluminum honeycomb core structure. The heat insulating board and the reinforcing layer are made of DB5012 aluminosilicate high-temperature resistant inorganic glue, the liquid phase is aluminosilicate solution, and the heat insulating board and the reinforcing layer are formed by solid phase and solidification bonding. The heat insulation plate is of a multi-layer composite structure, the bearing layer is made of a carbon/E-44/GA 32 epoxy resin composite material, the heat insulation layer is made of an aluminum silicate sandwich structure composite material, and the heat protection layer is made of a carbon/benzoxazine resin phenolic aldehyde composite material; adopting a co-injection RTM process to integrally form, wherein the optimal injection window temperature is 85 ℃, and the optimal co-curing system is 4h +140 ℃/2h +160 ℃.
The heat insulation layer 1 is a SiO2 aerogel/fiber sandwich structure
The heat insulation plate 2 is of a multilayer composite structure and is integrally formed in one step by adopting a coinjection RTM (resin transfer molding) process.
The heat insulation layer 1 is formed by bonding and curing a silicate inorganic adhesive and the heat insulation disc 2.
The composite material heat shield disclosed by the invention is of a multilayer composite material structure, realizes the aims of weight reduction, high temperature resistance and heat insulation by utilizing an integrated design technology and adopting a co-injection RTM (resin transfer molding) process, and has excellent mechanical properties and strength. The invention is suitable for the hot end heat insulation component of the spacecraft, has the characteristics of low density, high specific surface area, high porosity, low heat conductivity and the like, overcomes the defects of difficult process processing, low reliability and the like of the injection temperature and the curing system of two different resins, solves the difficulty of integrated design of the heat insulation component, meets the structural strength of the component, and effectively reduces the heat conductivity coefficient and the weight.
Claims (9)
1. The composite material heat shield is characterized by comprising a heat insulation layer (1) and a heat insulation disc (2); a heat insulation layer (1) is arranged in the maximum direction of heat flow of the heat insulation disc (2); wherein, the heat insulation layer (1) is a SiO2 aerogel/fiber sandwich structure, and the heat insulation plate (2) is a multi-layer composite structure integrally formed at one time by adopting a co-injection RTM process.
2. A composite heat shield according to claim 1, characterized in that the insulating layer (1) is a multilayer structure of composite material, which is a SiO2 aerogel/fibre sandwich structure.
3. A composite heat shield according to claim 2, characterised in that the insulating layer (1) comprises a carrier layer (1-1), a reinforcing layer (1-2) and a heat protection layer (1-3); wherein the bearing layer (1-1) is arranged on the upper surface of the reinforcing layer (1-2), and the heat-proof layer (1-3) is arranged on the lower surface of the reinforcing layer (1-2) and is contacted with the heat-insulating disc (2); the bearing layer (1-1), the reinforcing layer (1-2) and the heat-proof layer (1-3) adopt aluminosilicate high-temperature resistant inorganic glue as an adhesive, the liquid phase of the aluminosilicate high-temperature resistant inorganic glue is aluminosilicate solution, and the solid phase and the solidified adhesive are pressed and molded in a closed mold.
4. The composite material heat shield as claimed in claim 3, wherein the material of the bearing layer (1-1) is carbon/epoxy composite material with high specific strength and high specific modulus, so that the weight of the structure can be reduced on the premise of meeting the main load-carrying requirement.
5. A composite heat shield according to claim 3, characterized in that the reinforcement layer (1-2) is of an aluminum honeycomb core structure, and the reinforcement layer is filled with SiO2 aerogel. The enhancement layer is aluminium honeycomb core layer, and the advantage is that structural strength is higher when light in weight to because the service temperature is higher, consequently choose aluminium as the preparation material for use.
6. A composite heat shield according to claim 3, characterized in that the heat protection layer (1-3) is a three-dimensional woven laminate of aluminium silicate fibres or a carbon/phenolic composite. The composite material is one of resin-based ablation-resistant materials with the most excellent comprehensive performance, and aims to furthest exert the ablation heat-proof function on the basis of certain bearing performance.
7. The composite material heat shield according to claim 1, wherein the heat shield disc (2) is a multi-layer composite structure and comprises a bearing framework (2-1), a sandwich plate (2-2) and a heat shield plate (2-3), the bearing framework (2-1) is filled with the sandwich plate (2-2), and finally the heat shield plate (2-3) is bonded to the outer layer.
8. The composite heat shield according to claim 7, wherein the force-bearing skeleton (2-1) is a carbon/epoxy composite, the sandwich plate (2-2) is an aluminum silicate sandwich structure composite, and the heat-proof plate (2-3) is a carbon/phenolic composite.
9. The composite material heat shield according to claim 8, characterized in that the bearing framework (2-1) and the heat-proof plate (2-3) are injected together by a co-injection RTM process, and are adhered to the inner and outer wall surfaces of the sandwich plate (2-2) by a high-temperature adhesive, and then are cured to integrally prepare the bearing/heat-proof integrated heat-proof plate (2) at one time.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111591965.9A CN114311868A (en) | 2021-12-23 | 2021-12-23 | Composite material heat shield |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111591965.9A CN114311868A (en) | 2021-12-23 | 2021-12-23 | Composite material heat shield |
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| CN114311868A true CN114311868A (en) | 2022-04-12 |
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| CN202111591965.9A Pending CN114311868A (en) | 2021-12-23 | 2021-12-23 | Composite material heat shield |
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Citations (5)
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| CN101417516A (en) * | 2008-02-29 | 2009-04-29 | 中国人民解放军国防科学技术大学 | Bearing/insulating/ablating all-in-one sandwich structure composite material and preparation method thereof |
| CN109969432A (en) * | 2019-04-04 | 2019-07-05 | 北京卫星制造厂有限公司 | A kind of detachable thermal protection struc ture and its preparation method and application |
| CN209196416U (en) * | 2018-12-12 | 2019-08-02 | 陕西科诺材料科技有限公司 | A kind of multi-functional Combined thermal insulative panel |
| CN110103532A (en) * | 2019-05-07 | 2019-08-09 | 苏州宏久航空防热材料科技有限公司 | A kind of heat-insulating sound-insulating carrying multifunctional all composite construction |
| CN110181879A (en) * | 2019-06-27 | 2019-08-30 | 中素新科技有限公司 | Graphene aerogel fiber composite honeycomb aluminum plate and preparation method thereof |
-
2021
- 2021-12-23 CN CN202111591965.9A patent/CN114311868A/en active Pending
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101417516A (en) * | 2008-02-29 | 2009-04-29 | 中国人民解放军国防科学技术大学 | Bearing/insulating/ablating all-in-one sandwich structure composite material and preparation method thereof |
| CN209196416U (en) * | 2018-12-12 | 2019-08-02 | 陕西科诺材料科技有限公司 | A kind of multi-functional Combined thermal insulative panel |
| CN109969432A (en) * | 2019-04-04 | 2019-07-05 | 北京卫星制造厂有限公司 | A kind of detachable thermal protection struc ture and its preparation method and application |
| CN110103532A (en) * | 2019-05-07 | 2019-08-09 | 苏州宏久航空防热材料科技有限公司 | A kind of heat-insulating sound-insulating carrying multifunctional all composite construction |
| CN110181879A (en) * | 2019-06-27 | 2019-08-30 | 中素新科技有限公司 | Graphene aerogel fiber composite honeycomb aluminum plate and preparation method thereof |
Non-Patent Citations (1)
| Title |
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| 陈照峰: "《无机非金属材料学 第2版》", pages: 250 * |
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