In this thesis a study on the development and validation of a guidance algorithm is presented for an orbital vehicle during atmospheric reentry. This phase is a critical operation that that requires precise control to meet final conditions and achieve targeted landing accuracy. The main objective is to guarantee to reach the final states, minimizing deviations from a designated landing site. This objective is essential for improving both the safety and reliability of reentry missions, where a controlled descent can significantly influence mission outcomes. The project begins with a comprehensive literature review, analyzing a range of guidance algorithms that have been applied in past missions involving atmospheric reentry.