This thesis defines and implements a workflow for the finite element analysis of the landing of a 10 kg 6U CubeSat platform on the surface of an asteroid such as Apophis, with scientific objectives. The explicit solver Dytran was employed, well-suited for simulating highly nonlinear, short-duration dynamic events. An introductory review of the main asteroid types and past space missions provided the reference data. Based on this, a simplified CAD model of the lander was developed, discretized into finite elements, and processed in Patran to assign boundary conditions and material properties. The analysis was initially performed on a nominal scenario, representative of the most probable mission conditions, and subsequently extended through a sensitivity analysis.