A novel technique to compute the revisit time of satellites and its application in remote sensing satellite optimization design
This paper proposes a novel technique to compute the revisit time of satellites within repeat ground tracks. Different from the repeat cycle which only depends on the orbit, the revisit time is relevant to the payload of the satellite as well, such as the tilt angle and swath width. The technique is...
Gespeichert in:
| Hauptverfasser: | , |
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| Dokumenttyp: | Article (Journal) |
| Sprache: | Englisch |
| Veröffentlicht: |
2017
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| In: |
International journal of aerospace engineering
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| ISSN: | 1687-5974 |
| DOI: | 10.1155/2017/6469439 |
| Online-Zugang: | Verlag, kostenfrei, Volltext: http://dx.doi.org/10.1155/2017/6469439 Verlag, kostenfrei, Volltext: https://www.hindawi.com/journals/ijae/2017/6469439/ 
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| Verfasserangaben: | Xin Luo, Maocai Wang, Guangming Dai, and Xiaoyu Chen |
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| 245 | 1 | 2 | |a A novel technique to compute the revisit time of satellites and its application in remote sensing satellite optimization design |c Xin Luo, Maocai Wang, Guangming Dai, and Xiaoyu Chen |
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| 520 | |a This paper proposes a novel technique to compute the revisit time of satellites within repeat ground tracks. Different from the repeat cycle which only depends on the orbit, the revisit time is relevant to the payload of the satellite as well, such as the tilt angle and swath width. The technique is discussed using the Bezout equation and takes the gravitational second zonal harmonic into consideration. The concept of subcycles is defined in a general way and the general concept of “small” offset is replaced by a multiple of the minimum interval on equator when analyzing the revisit time of remote sensing satellites. This technique requires simple calculations with high efficiency. At last, this technique is used to design remote sensing satellites with desired revisit time and minimum tilt angle. When the side-lap, the range of altitude, and desired revisit time are determined, a lot of orbit solutions which meet the mission requirements will be obtained fast. Among all solutions, designers can quickly find out the optimal orbits. Through various case studies, the calculation technique is successfully demonstrated. | ||
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