This research focuses on a particular case of distributed space systems technology: spacecraft rendezvous missions. More specifically, the case of a two-phase satellite rendezvous maneuver is examined for rigid bodies instead of point-masses. Traditional Clohessy-Wiltshire models for relative motion become invalid when the spacecraft shapes are considered. The studied mission is considered non-cooperative, in the sense that the target spacecraft does not maneuver to facilitate rendezvous with the chaser spacecraft.
The first part of this research considers a new guidance law for rendezvous based on the well-known Proportional Navigation guidance law, modified for the studied mission type. The required commanded accelerations are presented in the line-of-sight reference frame (transverse and longitudinal components). Equations for the relative motion between the target and the chaser are derived. The second part of this research discusses the estimation of the line-of-sight rate and its higher-order derivatives in the case of imperfect information due to measurement errors. Different filters are implemented, and a performance evaluation is presented.
