阅读说明：本技术 一种热防护板 (Heat protection plate ) 是由 姚栋嘉 吴恒 刘喜宗 张东生 邓伟 吕多军 张相国 王征 于 2019-09-11 设计创作，主要内容包括：本发明属于热防护系统技术领域,公开一种热防护板。由外至内依次包括盖板、隔热层、内面板,自盖板向内面板方向贯穿设置有螺栓,螺栓的末端延伸出内面板内壁并用螺母固定；内面板内壁上在螺栓和螺母所处位置的外周设有气凝胶隔热罩；所述盖板为碳纤维增强陶瓷基复合材料盖板；所述隔热层为气凝胶毡层；所述内面板为树脂基复合材料内面板；所述螺栓为碳纤维增强陶瓷基复合材料螺栓,所述螺母为碳纤维增强陶瓷基复合材料螺母。本发明热防护板性能优异,能够满足飞行器表面温度在900℃以下的范围内使用。(The invention belongs to the technical field of thermal protection systems, and discloses a thermal protection plate. 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 thermal protection plate disclosed by the invention is excellent in performance and can meet the requirement that the surface temperature of an aircraft is used within the range of below 900 ℃.)

1. A heat shield plate, 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. The heat shield of claim 1, wherein: a spring washer is arranged between the inner panel and the nut.

3. The heat shield of claim 1, wherein: the carbon fiber reinforced ceramic matrix composite cover plate is a woven carbon fiber reinforced ceramic matrix composite cover plate; the carbon fiber reinforced ceramic matrix composite bolt is a woven carbon fiber reinforced ceramic matrix composite bolt; the carbon fiber reinforced ceramic matrix composite nut is a woven carbon fiber reinforced ceramic matrix composite nut; the resin-based composite material inner panel is a fiber reinforced resin-based composite material inner panel; the aerogel felt layer is a polyurethane aerogel felt layer, a polyimide aerogel felt layer or a silicon dioxide aerogel felt layer; the aerogel separates heat exchanger and separates heat exchanger for polyurethane aerogel, polyimide aerogel or separate heat exchanger for silica aerogel.

4. The heat shield of claim 1, wherein: a first aerogel heat insulation pad is sleeved on the bolt between the inner panel and the nut; the bolt positioned in the inner panel is sleeved with an aerogel heat insulation ring.

5. The heat shield of claim 4, wherein: the first aerogel heat insulation pad is a polyurethane aerogel heat insulation pad, a polyimide aerogel heat insulation pad or a silicon dioxide aerogel heat insulation pad; the aerogel heat insulation ring is a polyurethane aerogel heat insulation ring, a polyimide aerogel heat insulation ring or a silicon dioxide aerogel heat insulation ring.

6. The heat shield of claim 4, wherein: the bolt that is located insulating layer inside is equipped with second aerogel heat insulating mattress, ceramic ring from its one end that is close to the inner panel to the other end cover in proper order.

7. The heat shield of claim 6, wherein: the second aerogel heat insulation pad is a polyurethane aerogel heat insulation pad, a polyimide aerogel heat insulation pad or a silicon dioxide aerogel heat insulation pad; the ceramic ring is a zirconium oxide ring, a zirconium carbide ring, a zirconium diboride ring, a hafnium carbide ring or a hafnium diboride ring.

8. The heat shield of claim 4 ~ 7, wherein a spring washer is disposed between the first aerogel insulation blanket and the nut.

9. The heat shield of claim 1 ~ 7, wherein the aerogel heat shield is bonded to the inner panel by a high temperature glue having a heat resistance of not less than 1000 ℃.

10. The heat shield of claim 1 ~ 7, wherein the outer surface of said cover plate is provided with a SiC coating.

Technical Field

The invention belongs to the technical field of thermal protection systems, and particularly relates to a thermal protection 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.

The early thermal protection system is mainly a Flexible thermal protection system, namely AFEI (advanced Flexible External insulation) and the material of the early thermal protection system mainly meets the requirements of light weight, flexibility, folding and high temperature resistance, then a rigid ceramic thermal tile system is formed by ceramic tiles, Nomex Flexible Strain Isolation Pads (SIP) and room temperature curing silica gel (RTV), the ceramic thermal tile is mainly applied to a higher temperature region with the temperature of 600 ~ 1260 ℃ on the lower surface of a fuselage, at present, a metal thermal protection system is relatively accepted, metal TPS can bear the high temperature of 982 ~ 1093 ℃, the internal thermal protection material can prevent hot air flow from entering a skin structure to form a TPS structure whole, the outer layer structure of the thermal protection system is high temperature resistant alloy, and the thermal protection system has certain strength and rigidity, can effectively play a thermal 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.

Disclosure of Invention

The invention aims to provide a heat protection plate.

In order to achieve the above purpose, the invention provides three technical solutions, which are specifically as follows:

the scheme is as follows: a heat protection plate comprises a cover plate, a heat insulation layer and an inner panel in sequence from outside to inside, wherein 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.

Further, a spring washer is arranged between the inner panel and the nut.

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 carbon fiber reinforced ceramic matrix composite bolt; the carbon fiber reinforced ceramic matrix composite nut is a woven carbon fiber reinforced ceramic matrix composite nut; the resin-based composite material inner panel is a fiber reinforced resin-based composite material inner panel; the aerogel felt layer is a polyurethane aerogel felt layer, a polyimide aerogel felt layer or a silicon dioxide aerogel felt layer; the aerogel separates heat exchanger and separates heat exchanger for polyurethane aerogel, polyimide aerogel or separate heat exchanger for silica aerogel.

Preferably, 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 inner panel, 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.

Scheme II: on the basis of the scheme I, the following structures are further added: a first aerogel heat insulation pad is sleeved on the bolt between the inner panel and the nut; the bolt positioned in the inner panel is sleeved with an aerogel heat insulation ring.

Preferably, the first aerogel heat insulation pad is a polyurethane aerogel heat insulation pad, a polyimide aerogel heat insulation pad or a silicon dioxide aerogel heat insulation pad; the aerogel heat insulation ring is a polyurethane aerogel heat insulation ring, a polyimide aerogel heat insulation ring or a silicon dioxide aerogel heat insulation ring.

Scheme III: on the basis of the scheme II, the following structures are further added: the bolt that is located insulating layer inside is equipped with second aerogel heat insulating mattress, ceramic ring from its one end that is close to the inner panel to the other end cover in proper order.

Preferably, the second aerogel heat insulation pad is a polyurethane aerogel heat insulation pad, a polyimide aerogel heat insulation pad or a silicon dioxide aerogel heat insulation pad; the ceramic ring is a zirconium oxide ring, a zirconium carbide ring, a zirconium diboride ring, a hafnium carbide ring or a hafnium diboride ring.

In the second and third schemes, a spring gasket is preferably arranged between the first aerogel heat insulation pad and the nut.

In the schemes I, II and III, the aerogel heat insulation cover is preferably bonded with the inner panel by high-temperature glue with the heat-resistant temperature not lower than 1000 ℃. The high-temperature glue is preferably an inorganic high-temperature glue.

In the schemes of the first, second and third, the outer surface of the cover plate is preferably provided with a SiC coating.

The materials involved in the present invention include (woven structure) carbon fiber-reinforced ceramic matrix composites, high-temperature glue, polyurethane aerogel, polyimide aerogel, silica aerogel, glass fiber-reinforced epoxy resin matrix composites, carbon fiber-reinforced epoxy resin matrix composites, alumina fiber-reinforced epoxy resin matrix composites, silica fiber-reinforced epoxy resin matrix composites, aluminum borate fiber-reinforced epoxy resin matrix composites, glass fiber-reinforced polyimide resin matrix composites, carbon fiber-reinforced polyimide resin matrix composites, alumina fiber-reinforced polyimide resin matrix composites, silica fiber-reinforced polyimide resin matrix composites, aluminum borate fiber-reinforced polyimide resin matrix composites, glass fiber-reinforced phenolic resin matrix composites, carbon fiber-reinforced phenolic resin matrix composites, polyurethane aerogel, polyimide aerogel, silica aerogel, glass fiber-reinforced epoxy resin matrix composites, glass fiber-reinforced phenolic, The alumina fiber reinforced phenolic resin matrix composite material, the silica fiber reinforced phenolic resin matrix composite material, the aluminum borate fiber reinforced phenolic resin matrix composite material, the zirconia, the zirconium carbide, the zirconium diboride, the hafnium carbide and the hafnium diboride are all known products and can be obtained by market purchase or prepared according to the existing preparation method.

When the heat protection plate is used specifically, a plurality of heat protection plates are required to be spliced into a shape matched with the shape of an aircraft, and C can be used between splicing seams_fSiC bolt and C_fAnd connecting and fixing the/SiC nut.

Has the advantages that: in the invention, C is used_fthe/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 in a safe temperature range for a long time; according to the invention, the aerogel heat insulation ring is arranged between the bolt and the inner panel, the first aerogel heat insulation pad is arranged between the nut and the inner panel to prevent the inner panel from being overheated, and meanwhile, the aerogel heat insulation cover is adopted to integrally wrap the bolt and the nut to further prevent heat from being transferred into the cabin through the bolt; according to the invention, the ceramic ring is arranged between the cover plate and the inner panel, so that the cover plate and the inner panel can be prevented from being deformed due to the flexibility of the heat insulation layerThe second aerogel heat insulation pad is added between the ceramic ring and the inner panel to avoid the thermal damage of the ceramic ring to the inner panel, so that the structural integrity of the ceramic ring is ensured while the good heat insulation performance is ensured; the heat protection plate obtained by the invention has excellent performance, can meet the requirement that the surface temperature of an aircraft is used in a range below 900 ℃, and ensures that the internal temperature is in a required range; the invention has important promotion effect on the research of the thermal protection system for the aircraft.

Drawings

FIG. 1: the structure of the first embodiment of the invention is shown schematically;

FIG. 2: a schematic structural diagram of a second embodiment of the present invention;

FIG. 3: the third embodiment of the invention is a structural schematic diagram;

1-cover plate, 2-heat insulation layer, 3-inner panel, 4-bolt, 5-nut, 6-spring gasket, 7-aerogel heat insulation cover, 81-first aerogel heat insulation pad, 82-second aerogel heat insulation pad, 9-aerogel heat insulation ring and 10-ceramic ring.

Detailed Description

The technical solutions of the present invention will be further described in detail and clearly in the following with reference to specific examples, but the scope of the present invention is not limited thereto.