Flyby of large-size space debris objects and their transition to the disposal orbits in LEO. Issue 12 (15th June 2017)

• Record Type: Journal Article
• Authors: Baranov, Andrey A.; Grishko, Dmitriy A.; Razoumny, Yury N.; Jun, Li
• Is Part Of: Advances in space research. Volume 59:Issue 12(2017)
• Page Start: 3011
• Page End: 3022
• Publication Date: 2017-06-15
• Subjects: Space debris -- Active debris removal (ADR) -- Satellite catalogue -- Precession of the Right Ascension of the Ascending Node -- Optimal rendezvous maneuvers -- Disposal orbit; Space sciences -- Periodicals; Astronautics -- Periodicals; Geophysics -- Periodicals; 500.505
• DOI: 10.1016/j.asr.2017.03.021
• Languages: English
• ISSNs: 0273-1177

Abstract

Abstract: The article focuses on the flyby issue involving large-size space debris (LSSD) objects in low Earth orbits. The data on overall sizes of the known upper-stages and last stages of launch-vehicles make it possible to emphasize five compact groups of such objects from the Satellite catalogue in 600–2000 km altitude interval. The flyby maneuvers are executed by a single space vehicle (SV) that transfers the current captured LSSD object to the specially selected circular or elliptical disposal orbit (DO) and after a period of time returns to capture a new one. The flight is always realized when a value of the Right Ascension of the Ascending Node (RAAN) is approximately the same for the current DO and for an orbit of the following LSSD object. Distinctive features of changes in mutual distribution of orbital planes of LSSD within a group are shown on the RAAN deviations' evolution portrait. In case of the first three groups (inclinations 71°, 74° and 81°), the lines describing the relative orientation of orbital planes are quasi-parallel. Such configuration allows easy identification of the flyby order within a group, and calculation of the mission duration and the required total Δ V . In case of the 4th and the 5th groups the RAAN deviations' evolution portrait represents a conjunction of lines chaotically intersecting. The article studies changes in mission duration and in the required Δ V depending on the catalogue number of the first object in the flyby order. The article also contains a comparative efficiency analysis of the two world-wide known schemes applicable to LSSD objects' de-orbiting; the analysis is carried out for all 5 distinguished LSSD groups.