航天器热防护材料研究现状与发展趋势

Research Status and Application Advance of Heat Resistant Materials for Space Vehicles

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 reliability of space vehicles is much affected by the interface bonding of multi-layer heat resistant materials and the joining of smaller materials in the thermal protection system. However, there are defects in both aspects. Based on the theories concerning functional gradient materials and C/C composites, a way is designed to prepare a functional gradient carbon foam with density and heat conductivity for thermal protection from the carbon foam with high heat conductivity and the carbon microsphere with low heat conductivity. The advantages of the newly designed material lie in that there are no interfaces between layers of materials and smaller pieces of materials are easy to join.