When calculating a gimbal angle trajectory that satisfies boundary conditions set by an attitude boundary condition setter 2131 of the ground station 21, a gimbal angle trajectory calculator 2132 calculates the gimbal angle trajectory that minimizes a period of an acceleration interval within a range that satisfies driving restrictions of a gimbal, based on a gimbal angle θ0i of a start time and a gimbal angle θci of a fixed interval of an attitude change. Also, the gimbal angle trajectory is calculated that minimizes a period of a deceleration interval within a range that satisfies the driving restrictions of the gimbal, based on the gimbal angle θci of the fixed interval and a gimbal angle θfi of a completion time of the attitude change. The obtained θ0i, θci, θfi and an attitude change period τ are transmitted to the artificial satellite as gimbal angle trajectory parameters, and the control moment gyros are controlled based on the gimbal angle trajectory parameters.
ARTIFICIAL SATELLITE, ATTITUDE CONTROL SYSTEM, AND ATTITUDE CONTROL METHOD
2019-07-04
Patent
Electronic Resource
English
IPC: | B64G Raumfahrt , COSMONAUTICS |
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