Research on TianQin-3 orbit configuration optimization based on eccentricity presetting method

To address the issue of configuration divergence in the TianQin-3 geocentric orbit caused by external perturbations, this paper investigates a rapid orbit configuration optimization method based on the eccentricity presetting method. The perturbation dynamic equations of orbital elements are established to analyse the impact of external perturbations on the orbit configuration, indicating that quasi-periodic fluctuations in the eccentricity caused by perturbations are the main reason for short-term vibrations of the constellation configuration. To minimize the impact of external perturbations on the orbit configuration, this paper proposes a rapid orbit configuration optimization method based on the eccentricity presetting method. It requires only a one-step correction to obtain initial orbital parameters that meet mission requirements. Simulation results demonstrate that for the given initial orbital parameters with deviations, the breathing angle wandering of the TianQin-3 constellation can meet the mission’s accuracy requirements during the mission period only with one-step correction. It also has a computational load significantly lower than that of various search algorithms.