面向降落伞高空开伞的充气式钝锥阻力体气动构型仿真研究

Simulation of variant inflatable aerodynamic configurations for parachute deployment test at high attitude

针对钝锥阻力体航天器降落伞高空开伞试验采用低成本小直径火箭外形包络受限问题,提出在箭体上安装柔性充气环和充气裙锥两种变构型方案,用于模拟降落伞开伞过程真实流场环境。采用三维雷诺时均N-S(Reynolds Averaged Navier-Stokes,RANS)方程方法分别对某钝锥构型返回舱、某小型火箭以及火箭尾部加装充气环和充气锥裙4种构型进行流场数值模拟,并对比各种构型的尾流流场特征。计算结果表明,箭体上加装充气环和充气裙锥都可从一定程度上改善尾流特性;相比之下,采用充气裙锥方案更接近返回舱真实尾流流场。

In order to simulate the real flow field in the parachute deployment process,two kinds of configuration schemes,that is,with the instalment of an inflatable ring and with the instalment of an inflatable skirt cone,are proposed in view of the limitation of the rocket shape.The aerodynamic simulations are conducted by the 3D Reynolds averaged Navier-Stokes equation method for a blunted-cone capsule,a small rocket,an inflatable ring rocket,and an inflatable skirt cone rocket and a comparison is made among the wake flow fields.The results indicate that both of the variant configurations could improve the characteristics of the wake flow.In contrast,the wake of the inflatable skirt cone rocket is more similar to that of the capsule’s.