Design and analysis of integrated thermal protection system based on lightweight C/SiC pyramidal lattice core sandwich panel

Design and analysis of integrated thermal protection system based on lightweight C/SiC pyramidal lattice core sandwich panel
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基于轻质C/SiC金字塔晶格芯夹芯板的集成热防护系统设计与分析

DOI:
10.1016/j.matdes.2016.09.021
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发表时间:
2016-12
期刊:
影响因子:
8.4
通讯作者:
Fang Daining
Fang Daining
中科院分区:
材料科学1区
文献类型:
--
作者:
Wei Kai;Cheng Xiangmeng;Mo Fuhao;Wen Weibin;Fang Daining

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热保护系统(TPS)对于高超声速飞行器的成功研制起着关键作用。在这里,提出了一种基于轻质 C/SiC 金字塔芯晶格夹芯板的新型结构和热集成热保护系统(ITPS)。该ITPS综合了低面密度和耐高温高达1600°C的优点。 C/SiC 夹芯板的传热特性和压缩响应是预先确定的。结果表明,在孔中填充氧化铝纤维可显着降低有效导热率,从 2.45–4.83 W/m °C 降至不超过 0.7 W/m °C。确定气动压力载荷下的失效模型的临界相对密度。同时,专门建立了典型气动热通量和压力载荷下ITPS的分析程序。在满足温度和机械约束的情况下,获得最小面密度。与现有的金属波纹芯ITPS相比,本文提出的ITPS将温度限制显着提高到1600°C,并将面密度降低了35%,在高超音速飞行器中的潜在应用非常有前景。
Thermal protection system (TPS) plays the key role to successful development of hypersonic vehicles. Here, a novel structurally and thermally integrated thermal protection system (ITPS) based on the lightweight C/SiC pyramidal core lattice sandwich panel is proposed. This ITPS integrates advantages of low areal density and high temperature resistance up to 1600 °C. Heat transfer characteristics and compressive responses of the C/SiC sandwich panel are established in advance. The results demonstrate that filling alumina fibers in the pore significantly reduce the effective thermal conductivity from 2.45–4.83 W/m °C to no more than 0.7 W/m °C. The critical relative density is determinated for the failure models under aerodynamic pressure load. Meanwhile, an analysis procedure of the ITPS is exclusively established under typical aerodynamic heat flux and pressure load. With fulfillment of both temperature and mechanical constraints, minimum areal density is obtained. Compared with current metal corrugated core ITPS, the ITPS proposed here significantly raises the temperature limitation up to 1600 °C and reduces the areal density up to 35%, and is very promising for potential application in hypersonic vehicles.
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