摘要
Presents the general physical mathematical model established for ablation of carbon carbon composite, a double moving boundary method used to determine the surface temperature, ablation rate and thickness of thermal protection material and real time simulation of ablation at stagnation point of some missile between 65～20km during reentry.
Presents the general physical mathematical model established for ablation of carbon carbon composite, a double moving boundary method used to determine the surface temperature, ablation rate and thickness of thermal protection material and real time simulation of ablation at stagnation point of some missile between 65～20km during reentry.
基金
SponsoredbyNationalDefense 973ResearchItem
