| Budget Amount *help |
¥11,310,000 (Direct Cost: ¥8,700,000、Indirect Cost: ¥2,610,000)
Fiscal Year 2017: ¥1,300,000 (Direct Cost: ¥1,000,000、Indirect Cost: ¥300,000)
Fiscal Year 2016: ¥3,250,000 (Direct Cost: ¥2,500,000、Indirect Cost: ¥750,000)
Fiscal Year 2015: ¥3,250,000 (Direct Cost: ¥2,500,000、Indirect Cost: ¥750,000)
Fiscal Year 2014: ¥3,510,000 (Direct Cost: ¥2,700,000、Indirect Cost: ¥810,000)
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| Outline of Final Research Achievements |
Strongly perturbed orbit subject to the solar radiation pressure, gravity potential and solar tidal force is an important problem for planning small body exploration. This research has newly derived several orbit design methodology, guidance and navigation theories which take full advantage of such perturbation effect from the flight data of two Japanese deep space missions,Hayabusa and Ikaros, The typical achievement includes (1)new attitude stabilization method utilizing attitude-orbit dynamics coupling, (2)stable and operationally-practical delta-V assisted periodic orbit around small bodies and (3)database software development for small body-relative image-based navigation, and so on. These accomplishments are ready to be applied to near future practical small body exploration missions.
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