Trajectory control algorithms for the de-orbiting and Re-entry of the MISTRAL satellite.

This paper presents the trajectory control strategies for the de-orbiting and re-entry phases of a micro satellite equipped with a deployable and controlled aero-brake. They are framed in the design of the Italian space mission MISTRAL (MIcro-SaTellite with Air-Launchable Re-entry capabilities) developed under the supervision of the DAC-Campanian Aerospace District. The proposed control approach makes use of two different control strategies for the de-orbiting and re-entry phases, respectively. The former is based on a linear quadratic optimal control, whereas the latter is based on a model predictive control approach. Numerical simulation results demonstrate the effectiveness of the proposed approach which guarantees a good compromise between stability and performance during the mission phases of interest. • A control strategy for the de-orbiting and re-entry phase of a micro-satellite using a deployable aero-brake is proposed. • An LQR-based approach with state feedback is used for the de-orbiting phase. • An MPC approach with a terminal cost on the prediction time horizon is used for the re-entry phase. • Performance is assessed numerically by modelling both the entire GNC system and the satellite dynamics. • The achieved tracking error is compatible with the required landing accuracy of 250 km. [ABSTRACT FROM AUTHOR]