Attitude Error of Satellite Due to Gravity Gradient Boom

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  • Ueno Seiya
    横浜国立大学大学院環境情報研究院

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  • 重力傾度ブームによる姿勢精度低下
  • ジュウリョクケイド ブーム ニ ヨル シセイ セイド テイカ

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Abstract

Gravity gradient stabilization is applied to from small satellites to large space structures because energy is not necessary for attitude control and actuator is not either. The stability and accuracy of attitude depend on the mass property of satellite. Large moment of inertia is selected for suppression of the attitude error due to external disturbance torque. ‘Gravity gradient boom’ is often attached on the main body of satellite for this purpose. This paper discusses on the relation between mass property of gravity gradient boom and attitude accuracy using transfer functions from the disturbance forces to the attitude angles. The results show that gravity gradient boom does not always improve the attitude accuracy. For satellites with a long or heavy gravity gradient boom, the second orbital mode of roll and yaw angles are excited by solar radiation pressure torque when the orbit of satellite goes through the shadow of the earth.

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