Abstract
It is very difficult to achieve effective coverage of hot-spot targets in a short period of time by earth perturbation for orbit adjustment, because the coverage gap of the temporary multi-satellites network is too large in certain periods. In this paper, it is assumed that the satellite payload sensor beam type is a simple conic, the beam center of the satellite payload under the maximum lateral pendulum is calculated based on the precise ephemeris, and according to the projection ellipse of the payload on the ground, the coverage ability of the satellite payload on the ground target direction is obtained. Then the satellite is designed to encounter the ground target in the nodal period between the satellite passing the intersection of the same latitude circle of the ground target. The orbit adjustment control variables are calculated from the change of nodal period, and the optimal orbit adjustment control variables are selected from a specified time period. At last, the effective coverage of the ground target within a specified time period is achieved, and the maximum revisit interval is greatly shortened.
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Yu, H., Zhao, J., Liu, J., Nie, T., Zhan, B. (2023). Orbit Optimization Technology for Multi-satellites Network Earth Observation. In: Wang, L., Wu, Y., Gong, J. (eds) Proceedings of the 8th China High Resolution Earth Observation Conference (CHREOC 2022). CHREOC 2022. Lecture Notes in Electrical Engineering, vol 969. Springer, Singapore. https://doi.org/10.1007/978-981-19-8202-6_5
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DOI: https://doi.org/10.1007/978-981-19-8202-6_5
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