[논문]Nanosat Formation Flying Design for SNIPE Mission

Kang, Seokju; Song, Youngbum; Park, Sang-Young

doi:10.5140/jass.2020.37.1.51

[국내논문] Nanosat Formation Flying Design for SNIPE Mission 원문보기

Journal of astronomy and space sciences, v.37 no.1, 2020년, pp.51 - 60

Kang, Seokju (Astrodynamics and Control Lab., Department of Astronomy, Yonsei University) , Song, Youngbum (Astrodynamics and Control Lab., Department of Astronomy, Yonsei University) , Park, Sang-Young (Astrodynamics and Control Lab., Department of Astronomy, Yonsei University)

Abstract ▼ AI-Helper

This study designs and analyzes satellite formation flying concepts for the Small scale magNetospheric and Ionospheric Plasma Experiments (SNIPE) mission, that will observe the near-Earth space environment using four nanosats. To meet the requirements to achieve the scientific objectives of the SNIPE mission, three formation flying concepts are analyzed: a cross-shape formation, a square-shape formation, and a cross-track formation. Of the three formation flying scenarios, the cross-track formation scenario is selected as the final scenario for the SNIPE mission. The result of this study suggests a relative orbit control scenario for formation maintenance and reconfiguration, and the initial relative orbits of the four nanosats meeting the formation requirements and thrust limitations of the SNIPE mission. The formation flying scenario is validated by calculating the accumulated total thrust required for the four nanosats. If the cross-track formation scenario presented in this study is applied to the SNIPE mission, it is expected that the mission will be successfully accomplished.

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표/그림 (16)

그림 Fig. 1. Observations of the SNIPE mission.
그림 Fig. 2. Relationship between relative position in LVLH coordinates with respect to reference orbit.
그림 Fig. 3. Initial relative position of the cross-shape formation on the LVLH frame.
표 Table 1. Initial relative orbit of the cross-shape (+) formation
그림 Fig. 4. Accumulative ΔV of the four nanosats in the cross-shape formation flying scenario.
표 Table 2. Desired relative orbit of a cross-shape fying formation
그림 Fig. 5. Initial relative position of the square-shape formation on the LVLH frame.
표 Table 3. Initial relative orbit of square-shape (□) formation
그림 Fig. 6. Relative position of each nanosat in the square-shape formation with respect to the reference orbit (0, 0) on the equator (a) and at latitude 70° (b) during missions.
그림 Fig. 7. Initial relative position of along-track formation flying (a) and cross-track formation flying on the LVLH frame when they pass over the equator (b) and the North Pole (c).
그림 Fig. 8. Relative position of each nanosat in cross-track formation with respect to the reference orbit (0, 0) on the equator (a) and latitude 70° (b) during missions.
표 Table 4. Initial relative orbit of cross-track (━) formation
표 Table 5. Initial orbital elements of the reference and each nanosat in cross-track (━) formation
그림 Fig. 9. Relative position of each nanosat in cross-track formation with respect to the reference orbit (0, 0) on the equator (a) and latitude 70° (b) during missions when thrust errors are applied.
표 Table 6. Accumulated ΔV of cross-shape, square-shape, and along/cross-track formation flying
표 Table 7. Accumulative ΔV in the cross-track formation simulation over three months when thrust errors are applied

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