Angles-only initial relative orbit determination for space rendezvous using hybrid dynamics and virtual distribution method

This research develops a closed-form solution to the angles-only initial relative orbit determination problem for space rendezvous where a method of hybrid dynamics for virtual spacecraft formations produces range observability. Emphasis is placed on developing the solution in the context of Clohessy-Wiltshire orbital relative motion equations, obtaining spacecraft formation geometries that produce position/velocity observability, and deriving the closed-form error covariance equations for the initial relative orbit state solution. A two-body Monte Carlo simulation system is used to verify the feasibility and evaluate the performance of the closed-form relative state estimation algorithms. The sensitivity of the solution accuracy to the formation geometry, observation numbers is presented and discussed.