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17 April 2020 Design principles of equatorial satellite for the concerns of space debris
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Proceedings Volume 11455, Sixth Symposium on Novel Optoelectronic Detection Technology and Applications; 1145571 (2020) https://doi.org/10.1117/12.2565313
Event: Sixth Symposium on Novel Photoelectronic Detection Technology and Application, 2019, Beijing, China
Abstract
Equatorial satellites in low or medium altitude orbits have shown great potential for monitoring space debris in the geosynchronous belt and performing remote sensing tasks in low latitudes. However, the possibility of satellite collision between proposed equatorial satellites and existed spacecraft in Sun-synchronous orbit (SSO) should be considered. In this paper, the definition and design methods of both prograde and retrograde N-hour repeating equatorial orbits are given for space debris monitoring and remote sensing. The characteristics of prograde and retrograde equatorial orbits are compared. For reducing the risk of satellite collision after retirement, this paper also makes suggestions on the system design of the equatorial satellite.
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Yuchen Bai, Huan Yin, and Zhaoguang Bai "Design principles of equatorial satellite for the concerns of space debris", Proc. SPIE 11455, Sixth Symposium on Novel Optoelectronic Detection Technology and Applications, 1145571 (17 April 2020); https://doi.org/10.1117/12.2565313
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