The Atmospheric re-entry concerns the dynamic and the kinematic of a body coming from the space, descending from a planet orbit, as satellites and entry space vehicles, or from eccentric hyperbolic orbits, as meteoroids. The dynamic considered is a 3-Dof model represented with a Simulink algorithm. This model is valid up to a Mach number equal to the Triggered Mach.The work in this thesis is integrating re-entry Guidance, Navigation and Control algorithms for re-entry in a single simulation tool, including also the vehicle dynamics, for the design and testing of entry guidance and control solutions and for the generation of the steep and shallow trajectory.