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The invention relates to the technical field of spacecraft thermal protection material preparation, and provides a surface strengthening and toughening gradient thermal protection structure and a preparation method thereof.The thermal protection structure comprises an outer layer mainly composed of a fiber-reinforced glass-based composite material thermal protection panel; ceramic fiber rigid thermal insulation tiles adopted by the thermal protection panel are marked as first rigid thermal insulation tiles; the middle layer is mainly composed of a second rigid heat insulation tile; the inner layer is mainly composed of a rigid heat insulation tile/silicon dioxide aerogel composite material; the outer layer is used for reducing the surface temperature of the thermal protection structure from T1 to T2; the middle layer is used for reducing the T2 to T3; the inner layer does not shrink at the T3 temperature. The structure design and the heat transfer design are adopted, the double functions of gradient cooling and overall structure stability maintaining can be considered, and the mechanical obdurability, the high temperature resistance and the heat insulation performance of the thermal protection structure can all meet the requirements of hypersonic aircrafts.
本发明涉及航天器热防护材料制备技术领域,提供一种表面强韧化梯度热防护结构及其制备方法,该热防护结构包括:主要由纤维增强玻璃基复合材料热防护面板构成的外层;热防护面板采用的陶瓷纤维刚性隔热瓦记为第一刚性隔热瓦;以及,主要由第二刚性隔热瓦构成的中间层;以及,主要由刚性隔热瓦/二氧化硅气凝胶复合材料构成的内层;所述外层用于使所述热防护结构的表面温度从T1降低至T2;所述中间层用于使所述T2降低至T3;所述内层在所述T3温度下不收缩。本发明采用结构设计以及传热设计,能兼顾梯度降温和维持整体结构稳定的双重作用,使热防护结构的力学强韧性、耐高温性和隔热性均能满足高超音速飞行器的要求。
The invention relates to the technical field of spacecraft thermal protection material preparation, and provides a surface strengthening and toughening gradient thermal protection structure and a preparation method thereof.The thermal protection structure comprises an outer layer mainly composed of a fiber-reinforced glass-based composite material thermal protection panel; ceramic fiber rigid thermal insulation tiles adopted by the thermal protection panel are marked as first rigid thermal insulation tiles; the middle layer is mainly composed of a second rigid heat insulation tile; the inner layer is mainly composed of a rigid heat insulation tile/silicon dioxide aerogel composite material; the outer layer is used for reducing the surface temperature of the thermal protection structure from T1 to T2; the middle layer is used for reducing the T2 to T3; the inner layer does not shrink at the T3 temperature. The structure design and the heat transfer design are adopted, the double functions of gradient cooling and overall structure stability maintaining can be considered, and the mechanical obdurability, the high temperature resistance and the heat insulation performance of the thermal protection structure can all meet the requirements of hypersonic aircrafts.
本发明涉及航天器热防护材料制备技术领域,提供一种表面强韧化梯度热防护结构及其制备方法,该热防护结构包括:主要由纤维增强玻璃基复合材料热防护面板构成的外层;热防护面板采用的陶瓷纤维刚性隔热瓦记为第一刚性隔热瓦;以及,主要由第二刚性隔热瓦构成的中间层;以及,主要由刚性隔热瓦/二氧化硅气凝胶复合材料构成的内层;所述外层用于使所述热防护结构的表面温度从T1降低至T2;所述中间层用于使所述T2降低至T3;所述内层在所述T3温度下不收缩。本发明采用结构设计以及传热设计,能兼顾梯度降温和维持整体结构稳定的双重作用,使热防护结构的力学强韧性、耐高温性和隔热性均能满足高超音速飞行器的要求。
Surface strengthening and toughening gradient thermal protection structure and preparation method and application thereof
一种表面强韧化梯度热防护结构及其制备方法和应用
2024-10-29
Patent
Electronic Resource
Chinese
IPC:
C04B
Kalk
,
LIME
/
B32B
LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
,
Schichtkörper, d.h. aus Ebenen oder gewölbten Schichten, z.B. mit zell- oder wabenförmiger Form, aufgebaute Erzeugnisse
/
B64C
AEROPLANES
,
Flugzeuge
/
B64G
Raumfahrt
,
COSMONAUTICS
/
C03C
Chemische Zusammensetzungen für Gläser, Glasuren oder Emails
,
CHEMICAL COMPOSITION OF GLASSES, GLAZES, OR VITREOUS ENAMELS
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