Re-entry space vehicle necessities sharp leading edges for better aerodynamic performance and, hence, require advanced thermal protection materials with improved safety for crew members. Material possessing high thermal conductivity and oxidation resistance are desirable at nose cap and wings leading edge of spacecraft. Consequently, the thermal shock resistance improves due to reduced thermal gradient and stresses. ZrB₂ has drawn strong impetus for futuristic space vehicles as thermal protection materials under extreme thermal environments. This study reviews the effect of the incorporation of non-carbonaceous and carbon additives on the thermal conductivity of ZrB₂ ceramics and based composites. Several factors such as the purity of starting powder, initial particle size, amount of sintering aids, processing route, porosity, the grain size of ZrB₂ matrix, distribution of secondary phases in the matrix and sinter density of the final composite, controls the overall thermal conductivity of ZrB₂ based composites.

再入太空飞行器必须具有锋利的前缘，才能获得更好的空气动力学性能，因此，需要先进的热防护材料，以提高机组人员的安全性。具有高导热性和抗氧化性的材料在航天器的机头和机翼前缘是理想的。因此，由于减小的热梯度和应力而提高了抗热震性。ZrB ₂推动了未来派航天器作为极端高温环境下的隔热材料。这项研究审查了掺入非碳和碳添加剂对ZrB ₂导热系数的影响陶瓷和复合材料。诸如粉末的纯度，初始粒度，烧结助剂的量，加工路线，孔隙率，ZrB ₂基体的晶粒尺寸，基体中第二相的分布以及最终复合材料的烧结密度等几个因素控制着整体ZrB ₂基复合材料的热导率。