## 1 Introduction
The filtering method is able to compensate for unknown maneuvers and solve the orbit determination problem for continuous thrust targets, but it cannot provide specific maneuver parameters for better subsequent target tracking, i.e., maneuver reconstruction. Filtering methods can compensate for unknown maneuvers and solve the orbit determination problem for continuous-thrust targets, but they cannot provide specific maneuver parameters for better subsequent tracking--that is, maneuver reconstruction. Maneuver reconstruction methods aim to reconstruct the actual maneuver process, including detailed information such as thrust magnitude, maneuver time, and thrust direction. Different types of thrust correspond to specific dynamic models during reconstruction. [PERSON] et al. [13] derive two maneuver models based on the integration of Lagrange equations, solving the orbit maneuver detection problem for chemical propulsion maneuvers from a dynamics perspective. Using only two orbits (pre- and post-maneuver), they can not only determine whether a maneuver occurred but also obtain detailed maneuver information, including average maneuver time and maneuver magnitude. [PERSON] et al. [14] propose an improved second-order state transition tensor orbit propagation method via orbit segmentation and segment connection, accounting for maneuver uncertainty. Theyincorporate unknown maneuver magnitude, direction, and time into the orbital state, solving for a second-order optimal orbit determination estimate for thrust parameters. This method provides an accurate solution for unknown maneuvers. [PERSON] et al. [15] investigated the effect on the maneuvers' reconfiguration success rate based on maneuver type, tracking antenna performance, antenna coverage, error covariance level, and number of satellite passes after the maneuver. [PERSON] [16] established a variable mass dynamics model for the continuous thrust control process. With the extended Kalman filter orbit determination algorithm, the continuous thrust variable acceleration can be estimated in real time, but it requires a long tracking observation arc segment. The initial values of thrust parameters used in the maneuver reconstruction process are often historical empirical values or the initial values are directly set to zero, an approach that may lead to slow or no convergence of the precision orbiting process. For non-cooperative maneuvering spacecraft with unknown orbits and thrust parameters, a set of initial values for the orbital roots and thrust parameters that are relatively close to the true values is needed to improve the accuracy and efficiency of the precision orbit setting. The paper is organized as follows: Section 2 models the continuous thrust dynamics; Section 3 describes the orbit determination method used to calculate the orbit elements; Section 4 discusses the relationship between the continuous low thrust and the variation in each orbital elements; Section 5 gives a pre-identification method for the direction and magnitude of the continuous low thrust; Section 6 describes the simulated test scenarios and gives an analysis of the results; finally, Section 7 concludes.