The future multi beam satellite communication systems require high antenna pointing accuracy of about 0.015 degree. In geostationary orbit, several disturbance torques, such as gravity gradient torque, solar pressure torque, affect the antenna pointing accuracy. In the multi beam communication satellites, large diameter antenna reflectors and large solar paddles, which are scheduled to be used, cause large solar pressure torque. In this paper, at first the solar pressure torque of the 2-ton class satellite with two anti symmetric antenna reflectors was calculated, then, the structure which causes large solar pressure torque was considered numerically. Based on the results, especially the secular and periodical component of the roll/yaw plane solar pressure torque, it was revealed, how to decide the magnitude of the bias momentum of the bias momentum attitude control system from the point of yaw error requirement. Finally it was confirmed that simulation values agree well with the theoretical results.
抄録全体を表示