An analysis of attitude controller concepts, including four attitude flight controllers, for the re-entry of the HORUS-2b. The four concerning attitude flight controller concepts are the benchmark Linear Quadratic Regulator (LQR), Model predictive Controller, Incremental Non-linear Dynamic Inversion (INDI) and Sliding Mode Controller. Each attitude flight controller was employed in a full Guidance, Navigation and Control system and subsequently applied to a winged re-entry vehicle, the HORUS-2b. It was found that the INDI-controller is the most suitable attitude controller technique for real world entry GNC-systems. The INDI controller showed excellent performance with respect to disturbance rejection, amplification, robustness and implementation effort. Besides the INDI controller, the benchmark LQR-controller achieves excellent performance. In the current GNC-simulation set-up the LQR-controller is the best able to perform a re-entry, having zero control failures and an equal robustness to the INDI controller. Disadvantages of the LQR-controller are the large amplification of an oscillating signal and the implementation effort.