| Project/Area Number |
14F04210
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| Research Category |
Grant-in-Aid for JSPS Fellows
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| Allocation Type | Single-year Grants |
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| Section | 外国 |
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| Research Field |
Aerospace engineering
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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, 准教授 (80373439)
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| Co-Investigator(Kenkyū-buntansha) |
YAM CHIT HONG 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
YAM Chit Hong 独立行政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) |
2014-04-25 – 2017-03-31
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| Project Status |
Completed (Fiscal Year 2016)
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| Budget Amount *help |
¥2,300,000 (Direct Cost: ¥2,300,000)
Fiscal Year 2016: ¥500,000 (Direct Cost: ¥500,000)
Fiscal Year 2015: ¥800,000 (Direct Cost: ¥800,000)
Fiscal Year 2014: ¥1,000,000 (Direct Cost: ¥1,000,000)
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| Keywords | space mission design / low-thrust trajectories / multi-body / optimization / gravity assists / automated design / Space orbit design / Multi-body systems / Low-thrust trajectories / Optimization |
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| Outline of Annual Research Achievements |
We have implemented an automatic approach for the design of low-thrust trajectories in multi-body dynamical systems. Our method is tested and demonstrated to aid the design of two future JAXA missions: DESTINY and a CubeSats mission scheduled to be launched in 2018-EQUULEUES. We expect our method will continue to serve as an important tool for mission planning and contribute in space exploration.
The search for the nominal trajectory for DESTINY is made in incremental steps of time on the Earth and the target asteroid-Phaethon's epoch starting from a ballistic trajectory with a high relative velocity. The initial guesses are then optimized in a low-thrust optimization tool-GALLOP and lowering its relative velocity to less than 1.5 km/s for the mission requirement. Trade-offs studies are performed automatically with GALLOP by solving new optimization problems at different Earth launch dates and Phaethon flyby dates. That can help us explore the trade-off of the trajectory's apogee and perigee distance, which have a significant impact on the spacecraft's power requirement.
For the mission analysis of EQUULEUS, a systematic method of generating a good set of transfer orbits in the Earth-Moon system is developed, which involves 5 main steps: forward propagation, computation of quasi-halo orbits, backward propagation, matching of forward and backward legs, and refinement of solutions. These steps are unified in a single toolbox for the ease of use and flexibility for updates. The design process can thus be done in a nearly automatic fashion with only a few user's interventions.
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| Research Progress Status |
28年度が最終年度であるため、記入しない。
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| Strategy for Future Research Activity |
28年度が最終年度であるため、記入しない。
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