论文部分内容阅读
针对当前超燃冲压发动机热防护技术面临的困境,为了突破更高飞行马赫数下的热障限制,提出了一种采用冷却剂与被动材料共同承担热载荷的主被动复合热防护技术。分析了主被动复合热防护技术的设计内涵及总体设计原则,讨论了被动层承担的热载荷和被动复合材料的导热系数、厚度之间的关系,并以C/SiC作为被动复合材料,对比分析了主被动复合热防护方案的优势。研究表明,当C/SiC厚度为4mm时,大致可将马赫数为6.5,当量比0.5工况下的热流密度降低42%。
Aimed at the current predicament of thermal protection technology of scramjet, in order to break through the thermal barrier under the higher flight Mach number, a passive and passive composite thermal protection technology using coolants and passive materials to share thermal load is proposed. The design connotation and overall design principles of the passive and passive composite thermal protection technology are analyzed. The relationship between the thermal load and passive thermal conductivity and thickness of the passive composite material is discussed. C / SiC as the passive composite material is compared with the comparative analysis The main passive composite thermal protection program advantages. The results show that when the thickness of C / SiC is 4mm, the Mach number can be roughly 6.5 and the equivalent heat flux can be reduced by 42% when the equivalent ratio is 0.5.