New implicit neighboring optimal guidance and attitude control for three-dimensional lunar ascent
Recently, several Countries have shown an increasing interest toward robotic or human missions to the Moon. Ascent path and orbit injection represent a crucial issue for a lunar module, because the dynamical conditions at injection affect the subsequent phases of spaceflight. This research proposes the original combination of two techniques applied to lunar ascent modules, i.e. (i) the variable-time-domain neighboring optimal guidance (VTD-NOG), and (ii) a constrained proportional-derivative (CPD) attitude control algorithm.