Closed Loop Guidance During Close Range Rendezvous in a Three Body Problem

Abstract The paper presents a novel application of the State Dependent Riccati Equation (SDRE) guidance approach with state constraints for chaser spacecraft in close proximity passive target. dynamics are described by full 6 degree freedom rigid-body relative motion. final trajectory is defined passively safe approaching cone, which acts as path constraint and follows attitude motion A Near Rectilinear Halo Orbit Earth-Moon system selected rendezvous scenario to fully validate proposed solution, even though parameters related weighting functions kept general possible, thus applicable other similar missions.