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为了研究返回舱再入黑障区等离子鞘套的特性,利用FASTRAN软件对返回舱再入黑障段进行数值模拟计算,获得了返回舱周围流场和气体电离等参数的分布特性。结果表明:返回舱再入段由于进行高超声速飞行,气体的压缩形成强的弓体激波,激波层内气体压强增大,温度升高,气体发生电离,产生NO+离子和电子等带电体,形成了包覆在返回舱周围的等离子鞘套。通过分析不同返回舱的计算数据,得出返回舱激波层后气体温度的变化与初始速度相关,压强的变化与初始速度和初始压强相关;激波层后气体离解的程度与振动温度相关,N2较O2发生离解的振动温度高;影响等离子鞘套的主要参数是平动温度和电子数密度,其大小和分布在不同返回舱的相同归一化距离下基本一致。
In order to study the characteristics of the plasma sheath in the return capsule into the black area, the distribution of return flow and gas ionization parameters were obtained by FASTRAN software. The results show that due to the hypersonic flight, the compression of the gas forms a strong bow shock, the gas pressure in the shock wave layer increases, the temperature rises and the gas ionizes, resulting in charged ions such as NO + ions and electrons , Forming a plasma sheath wrapped around the return capsule. By analyzing the calculation data of different return capsule, the change of gas temperature is related to the initial velocity after the shockwave layer of return capsule. The change of pressure is related to initial velocity and initial pressure. The degree of gas dissociation after shock wave layer is related to vibration temperature, The temperature of dissociation of N2 is higher than that of O2. The main parameters affecting the plasma sheath are the translational temperature and the electron density, and its size and distribution are basically the same under the same normalized distance of different return capsules.