Synthesis of reference guidance strategy based on re-entry corridor

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. For the work I used two tolls: Matlab and Simulink. The procedure is validated comparing the results with IXV data. The output of the model is a trajectory that satisfies the load, heat and range constrains .The work was developed at the company Thales Alenia Space in Torino in Strada Antica di Collegno.