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Orbital maneuver accuracy analysis problem is studied by using linear covariance analysis techniques in this paper. Firstly, the main existing errors are analyzed and a closed-loop control system for orbit maneuver is established. Then, the models and equations for linear covariance orbit maneuver problem under both open-loop and closed-loop controls are developed respectively. And correction algorithm is presented based on orbit motion equation linearization. At last, the terminal state accuracies of high eccentric orbit maneuver under both open-loop and closed-loop controls is analyzed. And the validity of the results derived from linear covariance techniques is proved by using Monte Carlo simulations. [ABSTRACT FROM AUTHOR]