Uncertainty Quantification for Short Rendezvous Missions Using a Nonlinear Covariance Propagation Method

A study focuses on answering the two questions encountered in the short rendezvous-phasing mission. To accurately forward propagate the dynamic model uncertainties, initial state uncertainties, and orbital control uncertainties, the spacecraft's dynamic equations are first extended to include the atmospheric density and the J2 perturbation coefficient. State transition tensors A second-order nonlinear covariance propagation method that can handle uncertainties on initial states, model parameters and orbital controls are developed on the (STTs).