Initial orbit association and long-term orbit prediction for low earth space objects using optical tracking data. (November 2020)

• Record Type: Journal Article
• Authors: Lee, Eunji; Park, Sang-Young; Hwang, Hyewon; Choi, Jin; Cho, Sungki; Jo, Jung Hyun
• Is Part Of: Acta astronautica. Volume 176(2020)
• Page Start: 247
• Page End: 261
• Publication Date: 2020-11
• Subjects: Ground-based optical surveillance -- Angles-only observation -- Orbit determination -- Orbit prediction -- OWL-Net; AOP argument of periapsis -- CPF Consolidated Prediction Format -- DEC declination -- ECC eccentricity -- UKF unscented Kalman filter -- GEO geosynchronous -- INC inclination -- ISON International Scientific Optical Network -- LEO low Earth orbit -- MA mean anomaly -- MJD modified Julian date -- OWL-Net Optical Wide-field Patrol Network -- RA right ascension -- RAAN right ascension of ascending node -- RTN radial-transverse-normal -- SMA semi-major axis -- SRP solar radiation pressure; Astronautics -- Periodicals; Outer space -- Exploration -- Periodicals; Astronautics; Periodicals; 629.405
• DOI: 10.1016/j.actaastro.2020.06.046
• Languages: English
• ISSNs: 0094-5765

Abstract

Abstract: Ground-based optical tracking systems used in space surveillance provide no range information, and an observed arc is too short compared to the orbital period to provide enough dynamical information, especially for objects in low Earth orbit. Thus, multiple arcs of tracking data should be accumulated and associated in case of long-range orbit prediction. In this paper, a strategy to associate multiple orbit solutions and obtain accurate orbit solution to predict long-term trajectory using an optical space surveillance system is proposed and analyzed. The strategy consists of three steps: unscented batch estimation, chi-square testing, and element fitting. Each step is validated by numerical simulations, and the practical applicability is verified by applying actual tracking data from the Optical Wide-field Patrol Network (OWL-Net). In both the simulations and the practical cases, the associations are well determined, and the post-fit orbit solution provides a predicted trajectory error of 20 km for a week. The proposed strategy is a standalone process requiring no additional observations or orbit database, and it supports successive tracking by optical equipment with a restricted field of view. Highlights: A strategy to confirm the correlation of multiple orbit solutions is proposed. The strategy consists of estimation, correlation testing, and element-fitting. Each step is validated by numerical simulations. The proposed process is applied to actual tracking data. The proposed strategy supports successive tracking by optical system.