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热防护系统中所采用的多层复合热防护材料的层间界面结合和小块材料之间的连接对航天器的可靠性有很大影响,目前二者都存在一定的缺陷。依据功能梯度材料和C/C复合材料的理论,将高导热率碳泡沫和低导热率碳微球设计成密度和热导率功能梯度热防护碳泡沫材料,使其具备组分之间无层间界面和小块材料间易于连接等特点。
The multi-layer composite thermal protection materials used in the thermal protection system have a great influence on the reliability of the spacecraft due to the combination of the interface between the layers and the connection of the small pieces of materials. At present, both of them have certain defects. According to the theory of FGM and C / C composites, high thermal conductivity carbon foam and low thermal conductivity carbon microspheres were designed into density and thermal conductivity functionally graded thermal protection carbon foam materials with no layer Between the interface and small pieces of material easy to connect and so on.