随着火星探测着陆研究的发展,对其主要的减速方式——盘–缝–带伞应用的研究也日趋火热.而在火星探测中,对伞衣充气过程的分析又是最为复杂的难题之一.文章介绍了常用于降落伞流场求解的数值模拟方法,并对它们的利弊做了简要的描述.文章使用守恒元/解元方法对盘–缝–带伞在超声速条件下,从收束状态开始的充气过程进行了数值模拟.首先对前置体进行单独仿真,之后在不同的马赫数下通过对降落伞系统的整体仿真完成对降落伞开伞过程的模拟.仿真数据与实验数据进行对比,获得了较为一致的结果,验证了方法的可行性.另外,文章对两种工作状态下的充气过程进行了对比,分析了盘–缝–带伞在两者中充气过程的异同,以及前置体阻力贡献随着马赫数的变化.最后通过开伞云图对充气过程中的开伞失败现象进行了分析.研究结果可为火星探测提供参考.%With the development of Mars exploration and landing, the research on the decelerator, the disk-gap-band parachute, is becoming more and more popular, and the analysis of the inflation process is one of the most complicated problems. In this paper, the numerical simulation methods used to solve the flow field of parachute are introduced, and their advantages and disadvantages are briefly described. This paper use conservation element and solution element (CE/SE) method to simulate the inflation process of the parachute from folding state in supersonic speed. Firstly, the probe is simulated separately, then the inflating process of the whole system is simulated under different Mach numbers. The simulation result are compared with the experimental data, and the comparison results are consistent, which verified the feasibility of the method. In this paper, the inflating process under two working conditions is compared, and the similarities and differences are analyzed. The resistance contribution of the probe changing along with the Mach number is also analyzed. Finally, the phenomenon of failure in the inflation process was analyzed by the contours of the parachute. The research result can provide reference for Mars exploration.
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