超声速稳定伞气动热数值仿真研究

Research on Aerodynamic Heating Numerical Simulation of Supersonic Stabilizing Parachute

超声速稳定伞能有效避免飞船返回舱姿态不确定性引起的主降落伞系统开伞故障,在多用途飞船缩比返回舱的再入过程中得到了应用。相比于亚声速开伞过程,稳定伞超声速开伞时会遇到强烈的气动加热问题。文章采用流固耦合方法模拟稳定伞超声速时充气的动态过程,利用气动热数值仿真方法对稳定伞在超声速段的气动加热情况开展研究,确定典型弹道下的伞船系统的流场环境以及稳定伞面热流、温度分布。该数值研究方法可为中国返回式航天器再入返回过程中的超声速稳定伞设计提供参考。

In order to avoid the failure of the main parachute caused by the uncertainty of space capsule＇s attitude, the supsonic stabilizing parachute is applied efficiently during the reentry phase. Comparing with the inflation during the subsonic process, the aerodynamic heating should be paid more attention on the inflation during the supersonic process. The inflation process of a supersonic stabilizing parachute was studied by using the fluid-structure coupling method. The aerodynamic heating of the stabilizing parachute is researched through the numerical simulation method and heat flux and temperature field are calculated on a typical reentry trajectory. The inflation process and the aerodynamic heating simulation of the stabilizing parachute in this paper can provide reference for design of the stabilizing parachute during the space capsule＇s reentry phase.