CN210851565U - Novel hot guard plate - Google Patents
Novel hot guard plate Download PDFInfo
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- CN210851565U CN210851565U CN201921512331.8U CN201921512331U CN210851565U CN 210851565 U CN210851565 U CN 210851565U CN 201921512331 U CN201921512331 U CN 201921512331U CN 210851565 U CN210851565 U CN 210851565U
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Abstract
The utility model belongs to the technical field of hot protection system, a novel hot guard plate is disclosed. The heat insulation plate sequentially comprises a cover plate, a heat insulation layer and an inner panel from outside to inside, a bolt penetrates through the cover plate towards the inner panel, and the tail end of the bolt extends out of the inner wall of the inner panel and is fixed by a nut; an aerogel heat insulation cover is arranged on the inner wall of the inner panel at the periphery of the positions where the bolts and the nuts are located; the cover plate is a carbon fiber reinforced ceramic matrix composite cover plate; the heat insulation layer is an aerogel felt layer; the inner panel is a resin-based composite material inner panel; the bolt is a carbon fiber reinforced ceramic matrix composite bolt, and the nut is a carbon fiber reinforced ceramic matrix composite nut. The utility model discloses hot guard plate performance is excellent, can satisfy aircraft surface temperature and use at the within range below 900 ℃.
Description
Technical Field
The utility model belongs to the technical field of hot protection system, concretely relates to novel hot guard plate.
Background
The Thermal Protection System (TPS) is a structure for protecting a spacecraft from burnout and overheating in a pneumatic heating environment, has an unappreciable effect in a novel power System and aircrafts such as a load-on aircraft, a space probe aircraft, a near space aircraft, a reusable vehicle and the like, and the performance and reliability of the TPS are one of the determinants of the advancement and reliability of the related power System and aircrafts. To date, there are two types of thermal protection systems: ablation heat protection system and reusable heat protection system. The ablation heat prevention adopts the mechanism that the gasification product of the heat prevention material pyrolyzed at high temperature is utilized to radiate heat to the boundary mass injection effect; the device has the greatest advantages of safety, reliability, strong capability of adapting to external heating change and bearing high heat flow; the disadvantage is that it is disposable and can be deformed by ablation. The reusable thermal protection system does not have phase change and mass loss in the take-off and loading processes, and can play a bearing role, protect equipment and fuel in the aircraft body from being impacted by micrometeors and space debris, and safely complete flight tasks in severe weather such as thunderstorm and the like.
With the continuous improvement of the flight speed of the hypersonic aircraft, the service environment is more and more severe, and the thermal protection problem of the aircraft becomes a bottleneck limiting the development of the aircraft. Early thermal protection systems were mainly Flexible thermal protection systems, abbreviated as afei (advanced Flexible External insulation), and the materials thereof should mainly satisfy the requirements of light weight, flexibility, folding property, and high temperature resistance. Followed by a rigid ceramic heat resistant tile system consisting of a ceramic tile, a Nomex flexible Strain Isolation Pad (SIP), and room temperature cured silicone (RTV). The ceramic heat-proof tile is mainly applied to a higher temperature region with the lower surface temperature of 600-1260 ℃ of the fuselage and the wing. At present, a popular metal thermal protection system is provided, metal TPS can bear high temperature of 982-1093 ℃, an internal heat-proof material prevents hot air flow from entering a skin structure to form a TPS structure whole, the outer layer structure of the thermal protection system is made of high-temperature-resistant alloy, and the thermal protection system has certain strength and rigidity, can effectively play a heat insulation role and can bear certain external load impact.
From the development of materials for thermal protection systems, the materials are being transformed from flexible to rigid, which means that reusable thermal protection systems are transitioning from single to multiple use. The metal thermal protection system is the most commonly used thermal protection structure at present, but besides the poor overheating ability of the metal cover plate, the premature transition of the surface layer from laminar flow to turbulent flow due to thermal expansion deformation arching, the complex design and manufacturing process, the difficulty in inspection and quality monitoring, the adhesion stability problem of the non-catalytic coating, and in addition, the high thermal expansion coefficient of the metal, when it is subjected to large temperature gradient, the thermal stress fatigue failure may occur. Therefore, the research on the high-efficiency thermal protection system is always an urgent problem to be solved in the industry.
SUMMERY OF THE UTILITY MODEL
The utility model aims at providing a novel hot guard plate.
In order to achieve the purpose, the utility model adopts the following technical scheme:
a novel heat protection plate comprises a cover plate, a heat insulation layer and an inner panel in sequence from outside to inside, wherein bolts penetrate through the cover plate towards the inner panel, and the tail ends of the bolts extend out of the inner wall of the inner panel and are fixed by nuts; an aerogel heat insulation cover is arranged on the inner wall of the inner panel at the periphery of the positions where the bolts and the nuts are located;
the cover plate is a carbon fiber reinforced ceramic matrix composite cover plate, namely Cfa/SiC cover plate; the heat insulation layer is an aerogel felt layer; the inner panel is a resin-based composite material inner panel; the bolt is a carbon fiber reinforced ceramic matrix composite bolt, namely Cfa/SiC bolt, wherein the nut is a carbon fiber reinforced ceramic matrix composite nut, namely Cfa/SiC nut.
Preferably, the aerogel heat shield and the inner panel are bonded by high-temperature glue with the heat-resistant temperature not lower than 1000 ℃.
Further, the high-temperature glue is inorganic high-temperature glue.
Preferably, a spring washer is disposed between the inner panel and the nut.
Preferably, the outer surface of the cover plate is provided with a SiC coating.
Preferably, the carbon fiber reinforced ceramic matrix composite cover plate is a woven structure carbon fiber reinforced ceramic matrix composite cover plate, the carbon fiber reinforced ceramic matrix composite bolt is a woven structure carbon fiber reinforced ceramic matrix composite bolt, and the carbon fiber reinforced ceramic matrix composite nut is a woven structure carbon fiber reinforced ceramic matrix composite nut.
Preferably, the aerogel blanket is a polyurethane aerogel blanket, a polyimide aerogel blanket, or a silica aerogel blanket.
Preferably, the aerogel separates heat exchanger and separates heat exchanger for polyurethane aerogel, polyimide aerogel or separate heat exchanger for silica aerogel.
Preferably, the resin matrix composite inner panel is a fiber reinforced resin matrix composite inner panel.
Further, the fiber reinforced resin matrix composite inner panel is a glass fiber reinforced epoxy resin matrix composite inner panel, a carbon fiber reinforced epoxy resin matrix composite inner panel, an alumina fiber reinforced epoxy resin matrix composite inner panel, a silica fiber reinforced epoxy resin matrix composite inner panel, an aluminum borate fiber reinforced epoxy resin matrix composite inner panel, a glass fiber reinforced polyimide resin matrix composite inner panel, a carbon fiber reinforced polyimide resin matrix composite inner panel, an alumina fiber reinforced polyimide resin matrix composite inner panel, a silica fiber reinforced polyimide resin matrix composite inner panel, an aluminum borate fiber reinforced polyimide resin matrix composite inner panel, a glass fiber reinforced phenolic resin matrix composite inner panel, a carbon fiber reinforced phenolic resin matrix composite inner panel, a glass fiber reinforced epoxy resin matrix composite inner panel, a glass fiber, An alumina fiber reinforced phenolic resin matrix composite inner panel, a silica fiber reinforced phenolic resin matrix composite inner panel or an aluminum borate fiber reinforced phenolic resin matrix composite inner panel.
The utility model discloses in material that relates to, for example (weave structure) carbon fiber reinforcement ceramic matrix composite, high temperature glue, polyurethane aerogel, polyimide aerogel, silica aerogel, glass fiber reinforcement epoxy resin matrix composite, carbon fiber reinforcement epoxy resin matrix composite, alumina fiber reinforcement epoxy resin matrix composite, silica fiber reinforcement epoxy resin matrix composite, aluminium borate fiber reinforcement epoxy resin matrix composite, glass fiber reinforcement polyimide resin matrix composite, carbon fiber reinforcement polyimide resin matrix composite, alumina fiber reinforcement polyimide resin matrix composite, silica fiber reinforcement polyimide resin matrix composite, aluminium borate fiber reinforcement polyimide resin matrix composite, glass fiber reinforcement phenolic resin matrix composite, carbon fiber reinforcement phenolic resin matrix composite, polyurethane aerogel, The alumina fiber reinforced phenolic resin matrix composite material, the silica fiber reinforced phenolic resin matrix composite material and the aluminum borate fiber reinforced phenolic resin matrix composite material are all known products and can be obtained by market purchase or prepared according to the existing preparation method.
The utility model discloses hot guard plate when specifically using, needs a plurality of hot guard plates to splice into the shape with aircraft shape looks adaptation, can use C between the concatenation seamfSiC bolt and CfAnd connecting and fixing the/SiC nut.
Has the advantages that: the utility model adopts Cfthe/SiC plate is used as a cover plate and has high oxidation resistance and interlaminar shear strength; the aerogel felt is used as a heat insulation layer, and the unique characteristics of the aerogel are utilized to ensure that the aerogel has excellent heat insulation performance, so that the temperature control temperature required in the cabin section is effectively ensured; the inner panel is made of resin-based composite materials, has good interface performance and can be used within a safe temperature range for a long time, so that the obtained thermal protection plate has excellent performance, can meet the requirement that the surface temperature of an aircraft is used within a range below 900 ℃, and ensures that the internal temperature is within a required range; the utility model discloses the research to thermal protection system for the aircraft has important impetus.
Drawings
FIG. 1: the structure of the utility model is shown schematically;
the heat insulation structure comprises a cover plate 1, a heat insulation layer 2, an inner panel 3, a bolt 4, a nut 5, a spring gasket 6 and an aerogel heat insulation cover 7.
Detailed Description
The technical solution of the present invention will be described in detail and clearly with reference to the following embodiments, but the scope of the present invention is not limited thereto.
Example 1
As shown in fig. 1, the novel heat protection plate sequentially comprises a cover plate 1, a heat insulation layer 2 and an inner panel 3 from outside to inside, wherein a SiC coating (not shown) is arranged on the outer surface of the cover plate 1, a bolt 4 penetrates through the cover plate 1 towards the inner panel 3, the tail end of the bolt 4 extends out of the inner wall of the inner panel 3 and is fixed by a nut 5, and a spring gasket 6 is arranged between the inner panel 3 and the nut 5; an aerogel heat insulation cover 7 is arranged on the inner wall of the inner panel 3 at the periphery of the positions of the bolts 4 and the nuts 5, and the aerogel heat insulation cover 7 is bonded with the inner panel 3 by inorganic high-temperature glue with the heat resistance temperature not lower than 1000 ℃;
the cover plate 1 is a woven structure carbon fiber reinforced ceramic matrix composite cover plate; the heat insulation layer 2 is a silicon dioxide aerogel felt layer; the inner panel 3 is a glass fiber reinforced epoxy resin matrix composite inner panel; the bolt 4 is a woven structure carbon fiber reinforced ceramic matrix composite bolt, and the nut 5 is a woven structure carbon fiber reinforced ceramic matrix composite nut; the aerogel separates heat exchanger 7 for silica aerogel separates heat exchanger.
Claims (10)
1. A novel heat protection plate is characterized in that: the heat insulation plate sequentially comprises a cover plate, a heat insulation layer and an inner panel from outside to inside, a bolt penetrates through the cover plate towards the inner panel, and the tail end of the bolt extends out of the inner wall of the inner panel and is fixed by a nut; an aerogel heat insulation cover is arranged on the inner wall of the inner panel at the periphery of the positions where the bolts and the nuts are located;
the cover plate is a carbon fiber reinforced ceramic matrix composite cover plate; the heat insulation layer is an aerogel felt layer; the inner panel is a resin-based composite material inner panel; the bolt is a carbon fiber reinforced ceramic matrix composite bolt, and the nut is a carbon fiber reinforced ceramic matrix composite nut.
2. A novel heat shield according to claim 1, wherein: the aerogel heat insulation cover and the inner panel are bonded by high-temperature glue with the heat-resistant temperature not lower than 1000 ℃.
3. A novel heat shield according to claim 2, wherein: the high-temperature glue is inorganic high-temperature glue.
4. A novel heat shield according to claim 1, wherein: a spring washer is arranged between the inner panel and the nut.
5. A novel heat shield according to claim 1, wherein: and the outer surface of the cover plate is provided with a SiC coating.
6. A novel heat shield according to claim 1, wherein: the carbon fiber reinforced ceramic matrix composite cover plate is a woven structure carbon fiber reinforced ceramic matrix composite cover plate, the carbon fiber reinforced ceramic matrix composite bolt is a woven structure carbon fiber reinforced ceramic matrix composite bolt, and the carbon fiber reinforced ceramic matrix composite nut is a woven structure carbon fiber reinforced ceramic matrix composite nut.
7. A novel heat shield according to claim 1, wherein: the aerogel felt layer is a polyurethane aerogel felt layer, a polyimide aerogel felt layer or a silicon dioxide aerogel felt layer.
8. A novel heat shield according to claim 1, wherein: the aerogel separates heat exchanger and separates heat exchanger for polyurethane aerogel, polyimide aerogel or separate heat exchanger for silica aerogel.
9. A novel heat shield according to claim 1, wherein: the resin matrix composite inner panel is a fiber reinforced resin matrix composite inner panel.
10. A novel heat shield according to claim 8, wherein: the fiber reinforced resin matrix composite inner panel is a glass fiber reinforced epoxy resin matrix composite inner panel, a carbon fiber reinforced epoxy resin matrix composite inner panel, an alumina fiber reinforced epoxy resin matrix composite inner panel, a silica fiber reinforced epoxy resin matrix composite inner panel, an aluminum borate fiber reinforced epoxy resin matrix composite inner panel, a glass fiber reinforced polyimide resin matrix composite inner panel, a carbon fiber reinforced polyimide resin matrix composite inner panel, an alumina fiber reinforced polyimide resin matrix composite inner panel, a silica fiber reinforced polyimide resin matrix composite inner panel, an aluminum borate fiber reinforced polyimide resin matrix composite inner panel, a glass fiber reinforced phenolic resin matrix composite inner panel, a carbon fiber reinforced phenolic resin matrix composite inner panel, a composite outer panel, a composite inner, An alumina fiber reinforced phenolic resin matrix composite inner panel, a silica fiber reinforced phenolic resin matrix composite inner panel or an aluminum borate fiber reinforced phenolic resin matrix composite inner panel.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201921512331.8U CN210851565U (en) | 2019-09-11 | 2019-09-11 | Novel hot guard plate |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201921512331.8U CN210851565U (en) | 2019-09-11 | 2019-09-11 | Novel hot guard plate |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN210851565U true CN210851565U (en) | 2020-06-26 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201921512331.8U Active CN210851565U (en) | 2019-09-11 | 2019-09-11 | Novel hot guard plate |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN210851565U (en) |
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2019
- 2019-09-11 CN CN201921512331.8U patent/CN210851565U/en active Active
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