Estimation of orbital parameters of broken-up object using in-situ debris measurement satellite
Estimation of orbital parameters of broken-up object using in-situ debris measurement satellite
Collisions and explosions of satellites generate a large amount of sub-millimeter-size debris, which can cause fatal damage to a spacecraft. However, such tiny debris cannot be tracked from the ground. Therefore, an in-situ debris measurement satellite, which can detect impacts with sub-millimeter-size debris, has been proposed. Based on this concept, previous studies proposed the method to estimate some orbital parameters of the broken-up object. In those studies, it is assumed that the measurement satellite detects impacts at the intersection of the orbital planes of the measurement satellite and the broken-up object. However, simulated measurement data includes fragments contrary to this assumption. Thus, this study introduces a new approach to estimating the orbital parameters of the broken-up object from simulated measurement data. In this study, the inclination, the right ascension of the ascending node, and the nodal precession rate are estimated from the history of geocentric declination using the iteratively reweighted nonlinear least square method.
In-situ measurement, Orbit estimation, Origin identification, Satellite fragmentation, Space debris
International Astronautical Federation
Tanahashi, Mahiro
84c2e4b3-5b94-4336-b4b5-97c7498d9273
Chen, Hongru
8286469d-afe1-46e5-b107-694017de4d97
Yoshimura, Yasuhiro
bee6a581-5176-46a6-8793-d539fa664489
Hanada, Toshiya
6a914261-4634-4e52-8605-7c7579869145
2022
Tanahashi, Mahiro
84c2e4b3-5b94-4336-b4b5-97c7498d9273
Chen, Hongru
8286469d-afe1-46e5-b107-694017de4d97
Yoshimura, Yasuhiro
bee6a581-5176-46a6-8793-d539fa664489
Hanada, Toshiya
6a914261-4634-4e52-8605-7c7579869145
Tanahashi, Mahiro, Chen, Hongru, Yoshimura, Yasuhiro and Hanada, Toshiya
(2022)
Estimation of orbital parameters of broken-up object using in-situ debris measurement satellite.
In IAC 2022.
vol. 2022-September,
International Astronautical Federation..
Record type:
Conference or Workshop Item
(Paper)
Abstract
Collisions and explosions of satellites generate a large amount of sub-millimeter-size debris, which can cause fatal damage to a spacecraft. However, such tiny debris cannot be tracked from the ground. Therefore, an in-situ debris measurement satellite, which can detect impacts with sub-millimeter-size debris, has been proposed. Based on this concept, previous studies proposed the method to estimate some orbital parameters of the broken-up object. In those studies, it is assumed that the measurement satellite detects impacts at the intersection of the orbital planes of the measurement satellite and the broken-up object. However, simulated measurement data includes fragments contrary to this assumption. Thus, this study introduces a new approach to estimating the orbital parameters of the broken-up object from simulated measurement data. In this study, the inclination, the right ascension of the ascending node, and the nodal precession rate are estimated from the history of geocentric declination using the iteratively reweighted nonlinear least square method.
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More information
Published date: 2022
Venue - Dates:
73rd International Astronautical Congress, IAC 2022, , Paris, France, 2022-09-18 - 2022-09-22
Keywords:
In-situ measurement, Orbit estimation, Origin identification, Satellite fragmentation, Space debris
Identifiers
Local EPrints ID: 496678
URI: http://eprints.soton.ac.uk/id/eprint/496678
ISSN: 0074-1795
PURE UUID: ae2c426a-3407-450c-9775-96e8c23e225e
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Date deposited: 07 Jan 2025 21:09
Last modified: 10 Jan 2025 03:19
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Contributors
Author:
Mahiro Tanahashi
Author:
Hongru Chen
Author:
Yasuhiro Yoshimura
Author:
Toshiya Hanada
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