Aero-engine heat shield material

The invention relates to an aero-engine heat shield material. The heat shield material is prepared by adding a salt substance into a ceramic matrix composite material, wherein the ceramic matrix composite material is a SiC/SiC ceramic matrix composite material, the salt substance is an inorganic salt, and the inorganic salt is preferably a zinc borosilicate. According to the aero-engine heat shield material provided by the invention, the zinc borosilicate is added into the ceramic matrix composite material, so that thermal conductivity of the heat shield material can be reduced, and effectiveheat insulation of the high-temperature end of a heat shield can be realized; the zinc borosilicate has a self-healing effect, that is, the zinc borosilicate realizes an effect of forming flow-state glass to seal cracks at high temperature; and a heat shield prepared from the heat shield material can better meet requirements of an engine, especially a high-performance aero-engine. 本发明涉及种航空发动机隔热屏材料，隔热屏材料是在陶瓷基复合材料中加入盐类物质制备而