A Simulation Study of Orbit Determination Capability for Cislunar Space Probes Using ISL Data

Objectives To analyze the orbit determination capability of spacecraft in Cislunar Space using intersatellite Measurements. Methods According to the application requirements of Cislunar Space inter satellite link, the observation model of Dual-One-Way Measurement is established, and the algorithm for the sum combination is implemented in the realm of the General Relativity. The upcoming Cislunar DRO Exploration (CDROE) mission will utilize inter-satellites radiometric link among a LEO satellite, a DRO satellite and a RO satellite. The joint orbit determination capability using inter satellite link measurement is analyzed. Results The results show that more than 10 days of tracking data is needed to obtain an orbit better than 100m using only ISL between DRO and RO, and additional ISL data with LEO can shorten the tracking arc to 5 days. If the positioning data of LEO can be utilized, only 1-day data is needed. Conclusions The solution of systematic error is an important factor restricting the orbit determination convergence, so the calibration of systematic errors introduced by equipment delay, clock error, propagation medium, etc. is necessary.