AA 2024 alloy exhibits high specific strength, tensile properties, high surface finish and fatigue resistance over a wide range of temperatures. During actual service condition of aircraft structures, the structural components may experience stress in the form of tension, compression, bending and hydrostatic due to air medium. The tensile and fracture toughness of AA2024 is well reported in the literature. However, the dynamic behavior, particularly, ballistic impact behaviourof AA 2024 is scarce. Therefore, the present work is focused on analysis of ballistic impact resistance of AA2024alloyfor different target thicknesses using Finite Element Analysis.LS DYNA software is used to investigate the deformation characteristics of AA 2024 alloy under varying strain, strain rate and temperature. Tensile properties of AA2024 alloys reported in the literature are used to estimate the material and damage parameters in Johnson Cook plasticity model. The residual velocities obtained for the different nose shapes of projectile are validated through the available analytical models and were found to be in good agreement with each other. The preliminary study made on impact simulation deals with the failure in the target (AA2024 alloy) adopting complete element erosion of the target elements. However, due to the loss of energy, mass and momentum due to complete removal of elements; node splitting technique has been implemented during simulation to include those losses and thus, accounting for the fragments. The results obtained from node splitting technique were in agreement with the experimental and analytical studies reported in the literature. Furthermore, the high strain rate studies on AA 2024 and its processing conditions such as ‘Temper- T6 ‘and ‘annealed’ specimen were performed using Split Hopkinson Pressure Bar (SHPB) technique. A strain rate range of 5000/ s to 10000/s was imparted on AA 2024 alloy using SHPB. Additionally, LS DYNA software was used for simulating the high strain rate behavior of AA2024 and validated with the SHPB results for a thorough understanding of the impact phenomenon. It was observed that among the stress- strain curves obtained for the different processing conditions, the higher stresses were observed for the ‘Temper T6’ condition than the ‘As-Received’ condition. The calculated stresses using LS DYNA software exhibited a slight deviation from the experimental results by1.49%.