论文部分内容阅读
空间碎片与航天器的撞击速度通常大于10km/s,这种速度条件下撞击过程的物理特点是高温、高压和高应变率,同时伴随着熔化、汽化及等离子体等相变问题发生。利用AUTODYN/SPH的二次开发功能,在程序中嵌入Sesame状态方程数据库和铝材料的相图,数值模拟出撞击速度为5.0和5.6km/s时的防护屏穿孔直径分别为9.02mm和9.34mm,计算结果与实验结果符合较好,说明物理建模及参数的选取合理,同时也验证了数值模拟方法的正确性及有效性。通过计算给出碎片云的热力学量压力和温度分布,结合铝的相图,对超高速撞击产生碎片云的相分布进行了初步计算,给出了碎片云中固、液、气相的分布范围。
The impact velocity of space debris and spacecraft is usually greater than 10km / s. The physical characteristics of the impact process at this velocity are high temperature, high pressure and high strain rate, accompanied by the phase transition problems of melting, vaporization and plasma. Using the secondary development function of AUTODYN / SPH, the Sesame equation of state database and the phase diagram of aluminum material are embedded in the program, and the perforation diameters of the protective screen when the impact velocity is 5.0 and 5.6 km / s are numerically simulated respectively as 9.02 mm and 9.34 mm The calculated results are in good agreement with the experimental results, which shows that the physical modeling and parameters selection are reasonable. The correctness and validity of the numerical simulation method are also verified. By calculating the thermodynamic pressure and temperature distribution of debris cloud and phase diagram of aluminum, the phase distribution of debris cloud generated by hypervelocity impact is preliminarily calculated, and the distribution range of solid, liquid and gas phases in debris cloud is given.