球形弹丸超高速斜撞击薄板的碎片云和侵彻特征仿真分析

低地球轨道航天器易受到微流星体及空间碎片的超高速撞击。相较于正撞击，斜撞击现象更加普遍、更具研究价值。文章采用Autodyn-3D数值模拟软件，利用光滑粒子流体动力学（smooth particle hydrodynamics, SPH）方法，模拟Al2017-T4球形弹丸超高速斜撞击Al2A12薄板的过程，开展弹丸撞击速度为3～6 km/s、撞击角度为0°～60°时的撞击特征仿真分析。结果表明:撞击角度对碎片云形貌与几何尺寸，以及穿孔大小和形状特征有显著影响；当撞击角度为30°～45°时会发生滑弹反溅现象，造成弹丸侵彻能力下降。研究结果可为超高速撞击防护结构的设计和改进提供支持。

Simulation analysis of the characteristics of debris cloud and perforation caused by oblique hypervelocity impact of spherical projectile on a thin plate

The spacecraft in the low Earth orbit is vulnerable to the hypervelocity impact by micrometeoroids and space debris. Compared with the vertical impact, the oblique impact is more commonly found and worth more research effort for the hypervelocity impacts. In this paper, a numerical calculation is made with the Autodyn-3D software and the smooth particle hydrodynamics (SPH) algorithm to simulate the process of the Al2017-T4 spherical projectile impacting obliquely the Al2A12 plate at an ultra-high speed of 3 km/s to 6 km/s with an impact angle of 0° to 60°. It is shown that the impact angle has a significant effect on the morphology of the debris cloud, as well as on the size and the shape of the perforation hole. With an impact angle between 30° and 45°, the backsplash of the sliding projectile will occur, reducing the penetration ability of the projectile. The above results may provide some guidance for the design and the improvement of the protective structures against the inflight hyper-velocity impact.