Control System Design of the Lander Demonstrator EAGLE

This paper presents the control system design for a prototype demonstrator of a small moon lander. The deflection of the main thruster is used to obtain the lateral displacement control while the actual value of the thrust is controlled to get hovering. To guarantee the decoupling of maneuver planes and increase the stability margin, a roll control system is included which uses a cold gas system as auxiliary thruster (on-off actuators). The algorithms are discussed and the computation of gains is presented. Simulation results also are shown.