目的 开展以正钛酸锌（Zn2TiO4）为填料的无机热控涂层研究，丰富和发展具有低太阳吸收比（αS）、高红外发射率（εH）的空间稳定热控涂层体系。方法 首先以草酸、四氯化钛和氯化锌等为原料，通过共沉淀、高温固相烧结和酸性提纯结合的方法制备了Zn2TiO4粉体，并使用XRD和SEM对粉体的晶体结构和微观形貌进行了表征。然后以Zn2TiO4为填料，硅酸钾（K2SiO3）为粘接剂，配制了热控涂料。采用划格法和热循环试验对涂料的结合力和热环境适应性分别进行了研究。结果 酸性提纯处理后，实现了高纯度Zn2TiO4填料的制备，粒径为0.5~3 μm。Zn2TiO4/K2SiO3无机热控涂层的太阳吸收比为0.13±0.02，红外发射率为0.90±0.02，划格法的结合力等级为1级，经100次?196~200 ℃热循环试验后，涂层无脱落现象。结论 使用高纯度Zn2TiO4填料制得的无机热控涂层具有优异的热控性能，可以满足航天器高效、长寿命的热控设计需求，在航天器外表面具有良好的应用前景。

The work aims to enrich and develop space-stable thermal control coatings of low solar absorptance (αS) and high infrared emittance (εH), and to study inorganic thermal control coatings filled with zinc orthotitanate (Zn2TiO4). With oxalic acid, titanium tetrachloride and zinc chloride as raw materials, Zn2TiO4 powder was synthesized in the combined method of coprecipitation, calcination and acid washing. Crystal structure and microstructure of the Zn2TiO4 powder were characterized by XRD and SEM, respectively. Then inorganic thermal control coatings were obtained with Zn2TiO4 as filler and potassium silicate (K2SiO3) as adhesive. Cross cut test and thermal cycle test were adopted to study adhesion and thermo-environment adaptability of the coatings. High purity Zn2TiO4 filler was prepared through acid washing, its particle size ranged from 0.5 μm to 3 μm. The αS and εH of the Zn2TiO4/K2SiO3 inorganic thermal control coatings was 0.13±0.02 and 0.90±0.02, respectively. Adhesion of the coatings as tested in the cross cut test was grade 1. The coatings was free from spalling after 100 thermal cycles at ?196~200 ℃. Zn2TiO4/K2SiO3 inorganic thermal control coatings made from high purity Zn2TiO4 filler exhibits excellent thermal control performance, which is of good application prospects in external surface of spacecrafts as it can meet thermal control design requirements of spacecrafts which feature in high efficiency and long service life.