A Practical Algorithm for LEO Orbit Determination

Abstract

The primary objective of this paper is to present a practical, fast, and effective triple‐difference algorithm for precision orbit determination (POD) of low earth orbiters (LEOs). This technique was developed for near‐real‐time POD to support occultation data processing, as well as atmospheric data retrieval from the land‐based GPS network. In particular, the paper focuses on the GPS/LEO POD, with special emphasis on the triple‐difference–based kinematic approach to LEO POD. The paper provides the theoretical foundation of the method, and presents the results of a performance analysis for the CHAMP (CHAllenging Minisatellite Payload) satellite POD. In addition, data screening and quality control procedures applied to CHAMP and ground station GPS data are presented, with preliminary statistics related to the number and distribution of cycle‐slip events. A comparison of the results from two cycle‐slip detection methods is also included.

Joint navigation performance of distant retrograde orbits and cislunar orbits via LiAISON considering dynamic and clock model errors

“…The navigation of GEO satellites, which traditionally depends on Earth‐based observations, is usually difficult due to lack of relative motion between the satellites and the tracking ground stations. The LEO satellite can be easily and precisely located using the Global Navigation Satellite System (GNSS), and its precise position solutions may be used to enhance the navigation performance via LEO‐DRO LiAISON. Using the LiAISON technique to determine the absolute states of lunar satellites has the potential to reduce their dependence on Earth‐based measurements.…”