Trajectory Planning and Tracking for a Re-Entry Capsule with a Deployable Aero-Brake

In the last decade, increasing use of NanoSats and CubeSats has made re-entry capsule an emerging research field needing updates in configuration technology. particular, door to advancements terms efficiency re-usability been opened by introduction inflatable and/or deployable aerodynamic brakes on-board electronics for active control. Such technologies allow smaller sizes at launch, controlled re-entries, safe recovery. This paper deals with design a guidance control algorithm aero-brake. A trajectory optimization model is used both mission planning phase reference path during update case major deviations from prescribed orbit, thanks simplifications aimed reducing computational burden. Successively, tracking controller, based on Nonlinear Model Predictive Control (NMPC), able modulate opening aero-brake order follow planned towards target. robustness analysis was carried out, via numerical simulations, verify reliability proposed controller presence uncertainties, orbital perturbations, measurement noise.