The rapid expansion of space activities has intensified the risk of hypervelocity impacts (HVI) in low Earth orbit (LEO), where collisions with debris or micrometeoroids at velocities exceeding 7 km/s threaten spacecraft integrity. This thesis presents a comprehensive numerical investigation into (HVI) phenomena, specifically examining the dynamic response of thin aluminum plates subjected to spherical projectile impacts by employing a hybrid finite element–smoothed particle hydrodynamics (FE-SPH) approach. The study closely adheres to the methodologies outlined in the literature, applying state of the art numerical techniques and validates debris cloud formation, wave propagation, fracture evolution, and crater formation against experimental work. The coupling of the two methods combines the stability of finite elements and the flexibility of SPH particles to capture fragmentation and large deformations, ensuring energy conservation while mitigating tensile instabilities. Four experimental cases were examined, in the velocity regime of (2.54-6.71 km/s), with a constant projectile diameter and varying plate thicknesses. The analyses demonstrated strong agreement with experimental X-ray imagery and empirical measurements in three of four cases, particularly in predicting debris cloud expansion, crater formation and dynamic fracture patterns with an average error of 4.38% across all measurements. Despite the overall consistency, a few isolated discrepancies were noted, mainly attributed to uncertainties inherent in the debris cloud tracking algorithm’s geometric search methodology as well as mesh resolution due to hardware constraints. A crater aggregation model was developed to predict the spatial distribution and ballistic interactions of individual fragments, integrating kernel-weighted spatial association of their physical characteristics and ballistic limit criteria. Validated through a numerical experiment, the model demonstrated a 4.23% relative error in predicting the final crater diameter. The hybrid FE-SPH approach proved superior to standalone methods, balancing computational efficiency with physical accuracy. It successfully captured essential metrics, such as debris cloud morphology and residual fragment information, while avoiding energy loss and instability issues inherent in pure finite element or SPH models. However, heat transfer effects and phase transitions were omitted due to computational constraints, and all simulations assumed normal impacts despite the prevalence of oblique collisions in real-world scenarios. Future work should integrate thermal-structural analyses, advanced equations of state for phase transitions, and oblique impact studies to refine predictive capabilities. Continued innovation in computational techniques, coupled with experimental validation, will be essential to safeguarding orbital infrastructure in an increasingly congested space environment.