| Budget Amount *help |
¥4,420,000 (Direct Cost: ¥3,400,000、Indirect Cost: ¥1,020,000)
Fiscal Year 2017: ¥2,080,000 (Direct Cost: ¥1,600,000、Indirect Cost: ¥480,000)
Fiscal Year 2016: ¥1,300,000 (Direct Cost: ¥1,000,000、Indirect Cost: ¥300,000)
Fiscal Year 2015: ¥1,040,000 (Direct Cost: ¥800,000、Indirect Cost: ¥240,000)
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| Outline of Final Research Achievements |
Space debris are remnants of satellites and rocket bodies, which have hazardous effects on the maintenance and utilization of space infrastructures including the international space station. We investigated possible engineering approaches for tackling space debris issues from observation, modeling and removal points of view. Orbit determination and characterization of space debris are important tasks in evaluating its trajectory evolution and collision probability with resident objects in space. Several method to estimate the orbit, size, and spin of space debris were studied by investigating the profiles of received signals by the Kyoto University MU radar system. The effect of electric and magnetic fields around the Earth on long-term small-scale space debris trajectory evolution have been investigated based on numerical simulation. Furthermore, it was shown space debris with charging control system can be removed by controlling its trajectory and reentering the Earth atmosphere.
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