Abstract
The true trajectory of spacecraft disperses from the nominal due to kinds of errors and perturbations, including environment, actuator and sensor uncertainties. This paper studies the error analysis problem of closed-loop control for spacecraft orbital transfer via Monte Carlo method. At first, errors that affect the true state are introduced and a navigation-target-correction loop system for Monte Carlo simulation is built. A dynamical model for orbital transfer is established, based on which both the extended Kalman filter (EKF) algorithm and correction maneuver control algorithm are developed. Precision analysis is studied of high eccentric orbital (HEO) transfer under open-loop and closed-loop control respectively. The simulation results prove the validity of the proposed method.
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