抄録
The Engineering Test Satellite VIII(ETS-VIII), which will be launched in 2003, has large flexible appendages such as deployable antennas and paddles. On the other hand, high attitude accuracy is required, but it is hard to determine its flexibility parameters correctly under 1G circumstances of ground test facilities. The on-orbit system identification of its dynamics is very beneficial for this case, because it enables the validation of flexibility parameters used in the design phase, and besides the controllers gain tuning. The experiment of this identification is planed now. In this paper, we explain the overview of this experiment system and summarize the results of preliminary case studies for the system identification of the ETS-VIII dynamics model. In the case studies, it is assumed to use 1) attitude and translational responses during longitude station keeping maneuver, 2) step responses in normal operation mode and 3) impulse response in normal operation mode. The identification is feasible if the impulse responses are available. The responses during station keeping maneuver are not efficient for this identification without changing the conditions (e.g. the firing pattern of station keeping thrusters).
