The invention relates to a high-temperature thermal barrier coating material. The high-temperature thermal barrier coating material is rare earth niobate and a solid solution thereof. The chemical constitution of the rare earth niobate is Ln3NbO7, and Ln comprises the rare earth elements of La, Pr, Nd, Sm, Eu, Gd, Tb, Dy, Ho, Er, Tm, Yb, Lu, Y and Sc. The chemical constitution of the solid solution is Ln3(Nb1-xTax)O7 (x is larger than or equal to 0 and smaller than 1). Ln is a combination of one or more than one of the rare earth elements. The high-temperature thermal barrier coating material is characterized in that the heat conductivity of the material is low, when the temperature is 1000 DEG C, the intrinsic thermal conductivity of a compact block body is 1.1-1.4 W/m.k, compared with a commercial yttria-stabilized zirconia (YSZ) material (the thermal conductivity is about 2.5 W/m.k) with the weight percentage being 7%-8%, the thermal conductivity of the material is reduced by a large margin, and the material keeps phase stability and excellent oxygen-resistance capacity from the indoor temperature to the temperature of 1600 DEG C. The material can be applied to protection of high-temperature metal hot end parts of gas turbines or aero-engines.