Currently, the amount of space debris is increasing rapidly due to the tremendous amount of satellite launches. Having an autonomous re-entry system aboard satellites at their end-of life, creates possibilities in the frame of lowering space debris, as well as for sample return from space. This paper aims at describing two possible deployment systems for the Thermal Protection System. Also, the integration of an onboard Fibre Bragg Grating-based shape monitoring system, coupled to an adaptive control system is described. Additionally, several re-entry trajectory steering systems are investigated, combined with an inflatable concept analysis. The combination of a deployable Thermal Protection System, an onboard closed feedback loop for shape monitoring, and the ability to adapt the shape of the Thermal Protection System, creates the possibility to design an autonomous dynamically steered re-entry system.@en