Abstract: In order to simulate and study the hypervelocity impact of space debris on spacecrafts through hypervelocity impact on aluminum dual-sheet structure, a two-stage light gas gun is used to launch 2017-T4 aluminum alloy spherical projectiles. The projectile diameters range from 2.00 mm to 6.35 mm and impact velocities range from 1.50 km/s to 6.98 km/s. The impact angle is 0°for all the tests. Crater distribution modes on the rear wall of aluminum dual-sheet structure by hypervelocity impact of AL-spheres in different impact velocity ranges are obtained. Crater distribution characteristics on the rear wall are analyzed. The forecast equations for crater distribution on the rear wall of aluminum dual-sheet structure by hypervelocity normal impact are derived. The results show that crater distribution on the rear wall is a circle area under hypervelocity normal impact. As projectile diameter, impact velocity and shielding space increases, crater distribution area increases. The critical fragmentation velocity of impact projectile is an important factor affecting the crater distribution modes on the rear wall.

Key words: Craters distribution, Dual-sheet structure, Explosion mechanics, Hypervelocity impact, Space debris