气动热作用下的充气式减速器性能研究

Study on the Performance of Inflatable Decelerator with Aerodynamic Heating

为了解高超声速再入时气动热载荷对充气式减速器柔性结构的影响,文章基于松散耦合方法开展了极端热载荷工况下的耦合数值研究。文章首先建立了流固耦合和热固耦合两种模型,分别对比研究了气动力和气动热两种气动载荷对蒙皮结构的影响。结果表明,气动热对结构的影响远大于气动力,在高超声速再入时应重点考虑。之后研究了气动热载荷下充气式减速器防热层各功能层温度分布,结果表明,绝热层隔热效果最为显著,绝热层导热系数增大一倍,内部最高温度升高21.7%,热变形最大值升高10.7%。上述成果为充气式减速器的设计提供了一定的理论依据。

A coupling numerical calculation is carried out under the limit conditions of the loose coupling method, in order to understand the influence of aerodynamic heating on a flexible structure of an inflatable decelerator in hypersonic re-entry process. The fluid-structure interaction model and the thermo-structure interaction model of the re-entry process are established. The effects of aerodynamic loads and aerothermal loads on outer layer of the structure are compared. The results show that the effect of pneumatic heating on outer layer of the structure deformation is much greater than pneumatic heating. In hypersonic re-entry, the effects of aerodynamic heating on the refilling process must be considered. Then, the temperature distribution of the functional layer of the aerated reheater under aerodynamic thermal load was studied. It is found that the insulation effect of the insulation layer is the most significant, indicating that the maximum internal temperature of the insulation layer will increase by 21.7%, the maximum thermal deformation will increase by 10.7%, and the thermal insulation layer has the best thermal insulation effect. The insulation layer is the most important. The thermal conductivity has doubled. These results have certain reference value for the design of the inflatable re-entry decelerator.