| Project/Area Number |
22KF0420
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| Project/Area Number (Other) |
22F21061 (2022)
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| Research Category |
Grant-in-Aid for JSPS Fellows
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| Allocation Type | Multi-year Fund (2023)
Single-year Grants (2022) |
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| Section | 外国 |
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| Review Section |
Basic Section 24010:Aerospace engineering-related
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| Research Institution | Japan Aerospace EXploration Agency |
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Principal Investigator |
川勝 康弘 国立研究開発法人宇宙航空研究開発機構, 宇宙科学研究所, 教授 (80373439)
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| Co-Investigator(Kenkyū-buntansha) |
CARDOSO DOS SANT JOSUE 国立研究開発法人宇宙航空研究開発機構, 宇宙科学研究所, 外国人特別研究員
CARDOSO DOS SANTOS JOSUE 国立研究開発法人宇宙航空研究開発機構, 宇宙科学研究所, 外国人特別研究員
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| Project Period (FY) |
2023-03-08 – 2024-03-31
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| Project Status |
Completed (Fiscal Year 2023)
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| Budget Amount *help |
¥2,300,000 (Direct Cost: ¥2,300,000)
Fiscal Year 2023: ¥1,100,000 (Direct Cost: ¥1,100,000)
Fiscal Year 2022: ¥1,200,000 (Direct Cost: ¥1,200,000)
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| Keywords | low-thrust / earth perturbation / equinoctial elements / spiral trajectory / control / Low-thrust / Earth perturbation / Equinoctial Elements / Spiral trajetory / Control |
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| Outline of Research at the Start |
We plan to develop analytical and semi-analytical models to include different disturbing forces in the dynamical system, so that these models will be important tools to enable a better understanding of the dynamics of transfer trajectories from low- to high-altitude orbits with many revolutions, using low-thrusts and under different perturbations in the system.
The combination of these new tools with the fellow's expertise in other astrodynamics topics will bakery for him to pursue a research career.
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| Outline of Annual Research Achievements |
During the project's second year, an expansion of the previous work was performed by including the third-body force of the Moon and its averaged model to the dynamics which considered also the J2 term of the Earth's gravity field and low-thrust force modeled using the Fourier theorem. The outcomes confirm the importance of including J2 in the mission design analysis of DESTINY+ and similar missions, as it creates a precession rate in the perigee position, affecting the orbital strategies relying. The third-body averaged dynamics which considers the Moon fixed along one orbital period presented more efficiency in low altitudes since the ratio between the revolutions of the spacecraft and the Moon is smaller than in near-GEO cases. Therefore, these effects are important to be considered for an accurate orbit plan design and control. The adoption of equinoctial elements removed the difficulties with singularities around zero-eccentricity and zero-inclination for integration and conversion to Cartesian elements. These results were presented at the 74th International Astronautical Congress. Apart of two papers published in international conferences, the expansion of the work has been using numerical short-period corrections in the initial conditions of the analytical averaged dynamics, which improves the accuracy of the solutions obtained. Finally, the numerical average is being implemented to be compared with the analytical one proving stronger robustness to the work. These outcomes are being prepared for submission to the prestigious Journal of Guidance, Control and Dynamics.
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