考虑防热层以及烧蚀的高超声速飞行器动特性计算模型研究

Study on Dynamic Model of Hypersonic Aircraft Considering TPS with Ablation Effects

针对全大气层滑翔的高超声速飞行器动特性预示需求,本文提出了考虑防热层以及烧蚀的高超声速飞行器截面刚度计算模型。首先,提出了三层组合的高超声速飞行器截面刚度计算模型,分别为最内层承力金属壳体、中间防热层原始层和最外防热层烧蚀层。其次,根据刚度线性叠加原理,给出了各层以及总的截面刚度参数的计算方法。最后,针对实际使用,给出了高超声速飞行器结构动特性具体的计算分析程序和步骤。

To indicate the dynamic characteristics of hypersonic aircraft gliding in the whole atmosphere,a calculation model of section stiffness considering thermal protection system(TPS)and ablation effects is proposed.Firstly,the section stiffness model with three-layer combination is put forward,which include the inside main backbone,the in-between original layer of TPS,and the outmost ablative layer of TPS.Secondly,based on the linear superposition principle,the calculation methods of each layer and total section stiffness parameters are given.At last,the analysis strategy of the hypersonic aircraft’s dynamic characteristics is given for actual use.