抄録
This paper presents a development of a spacecraft simulator using an air bearing. The system equips with a three-axis magnetometer, a three-axis accelerometer, and three rate gyros to estimate the attitude of the satellite model. Three reaction wheels are orthogonally installed on the system and generate control torques along three body-fixed axes for the attitude control. The purpose of this study is to develop a spacecraft simulator to show the effectiveness of a three-dimensional attitude control law. The control torques generated by the reaction wheels are verified utilizing the conservation of angular momentum. Also, the sensor outputs filtered with Extend Kalman Filter (EKF) are compared with reference data to show the accuracy. Using two vector measurements of the magnetometer and accelerometer, we estimate the attitude of satellite simulator.
