Mechanical damage of the composite structure in spacecraft solar array panels under hypervelocity impact

The hypervelocity impact (HVI) of space debris on composite structures in spacecraft solar array panels (CS-SSAP) can potentially degrade the performance of spacecraft missions. Understanding the damage mechanisms of CS-SSAP is crucial for protection design. In this study, a semi-refined numerical model of CS-SSAP is developed to investigate their mechanical damage under hypervelocity impact (HVI) using the finite element–smoothed particle hydrodynamics (FE–SPH) coupling method. The dynamic evolution of the CS-SSAP structure is analyzed, and the damage sizes and fragmentation behavior are quantitatively evaluated under varying coverglass thicknesses. The results show that the damage radii of the front panel, rear panel and honeycomb core of the CS-SSAP increase with increasing coverglass thickness. Based on both numerical and theoretical analyses, the strategies of reducing the impedance difference between the projectile and the front panel, and decreasing the front-panel thickness are proposed to mitigate the damage of CS-SSAPs under HVI. This study provides theoretical insights and technical guidance for the protection design of spacecraft solar array panels.