抄録
In recent years, the technologies of micro-satellites are growing and there are more and more needs for commercial applications including remote sensing. The problem of remote sensing satellite is a trade-off among several conflicting requirements such as high ground resolution, high time resolution and wide observational range. For example, if we choose short period sub-recurrent orbit for high time resolution, the observational range is narrowed. And if satellite observes the earth in very large off-nadiar angle for wide observational range, the ground resolution will be decreased. To solve this problem it would be preferable to perform aggressive orbital maneuvers between some sub-recurrent orbits to satisfy these three requirements altogether using only one high ground resolution remote sensing micro-satellite. However, micro-satellites can't have much fuel because of their small volume. In this paper, we suggest some orbital maneuvering methods harnessing perturbations to decrease deltaV and optimal scheduling methods for orbital changing among some sub-recurrent orbits using a Genetic Algorithm. We applied these methods under the case of "Hodoyoshi-1" which is a 6.7 m ground resolution remote sensing micro-satellite being developed by The University of Tokyo and AXELSPACE Corporation in JAPAN.
