Ricerc@Sapienza

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.

In this paper, an improved approach for the solution of the regulator problem for linear discrete-time dynamical systems with non-Gaussian disturbances and quadratic cost functional is proposed. It is known that a sub-optimal recursive
control can be derived from the classical LQG solution by substituting the linear filtering part with a quadratic, or in general polynomial, filter. However, we show that when the system