Implementation of lightweight and long-lasting thermal-control coatings (TCCs) is vital for regulating the surface temperature and energy consumption of spacecraft. Herein, Zn₂SiO₄ and hexagonal boron nitride (hBN) based inorganic TCCs are developed with potassium silicate binder. The α_s/ε_H (solar absorptance/ hemispherical emittance) ratio of the Zn₂SiO₄, ZnO and hBN coatings are 0.096, 0.190 and 0.107, respectively. Compared to the classical ZnO based Z-93 coating, both Zn₂SiO₄/K₂SiO₃ and hBN/K₂SiO₃ coatings show superior initial thermophysical properties. After vacuum-proton irradiation, the α_s of Zn₂SiO₄, Z-93 and hBN coatings increased from 0.091, 0.167 and 0.098 to 0.193, 0.253 and 0.241, respectively. Apparently, the as-developed Zn₂SiO₄ coating exhibits exceptional heat-dissipation and radiation-resistance features in relation to the hBN and Z-93 TCCs.

轻质且持久的热控涂层（TCC）的实施对于调节航天器的表面温度和能耗至关重要。在此，用硅酸钾粘合剂开发了Zn ₂ SiO _{4和六方氮化硼(hBN)基无机TCC。}Zn ₂ SiO ₄ 、ZnO和hBN涂层的α _s /ε _H （太阳吸收率/半球发射率）比分别为0.096、0.190和0.107。与经典的ZnO基Z-93涂层相比，Zn ₂ SiO ₄ /K ₂ SiO ₃和hBN/K ₂ SiO ₃涂层表现出优异的初始热物理性能。真空质子辐照后，Zn ₂ SiO _{4 、Z-93和hBN涂层的αs}分别从0.091、0.167和0.098增加到0.193、0.253和0.241。显然，所开发的Zn ₂ SiO ₄涂层相对于hBN 和Z-93 TCC 表现出优异的散热和抗辐射特性。