Guidance and precision evaluation for spacecraft remote maneuvers with finite thrust

Based on the nonsingular Equinoctial orbital elements, an explicit guidance is proposed for spacecraft remote maneuvers with finite thrust. The end conditions of flight path can be satisfied using the explicit guidance with attitude-orbit coupling control and thrust shutdown control. The weighted numbers of the explicit guidance are optimized using numerical method. The Monte Carlo random simulation is used to calculate the statistic characteristics of the terminal orbit elements of remote maneuvers. Then, the probability density function is established using Gram-Charlier series approximation. Finally, the probability of out-of-tolerance of terminal orbit elements is calculated for remote maneuvers.