  In recent years, due to the constant increase of the density of satellites in
the space environment, several studies have been focused on the development of
active and passive strategies to remove and mitigate space debris. This work
investigates the feasibility of developing a reliable and fast approach to
analyze the re-entry of a satellite. The numerical model interfaces the
long-term orbit propagation obtained through semi-analytical methods with the
atmospheric destructive re-entry phase exploiting the concept of overshoot
boundary, highlighting the effect that an early break-off of the solar panels
can have on the re-entry prediction. The re-entry of ESA's INTEGRAL mission is
chosen as a test case to demonstrate the efficiency of the model in producing a
complete simulation of the re-entry. The simulation of the destructive re-entry
phase is produced using an object-oriented approach, paying attention to the
demisability process of the most critical components of the space system.
