重力傾度を利用する人工衛星の姿勢制御
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概要
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Abstract The gravity gradient stabilization provides a passive, long-lived and earth pointing satellite attitude control system. The fundamental principles of the gravity stabilization are showed, and then the equations of motions are derived by applying the Lagrangean equations to the proposed system which is composed of the main rod, damping rods and damper-spring mechanisms. As a result of linearization, these equations are expressed in two groups, one describing the pitch motions and the other the roll-yaw motions. The equations for pitch have two oscillatory transient modes; one is symmetric, and the other antisymmetric, and the characteristics are represented by three non-dimensional parameters related to the moment of inertia, spring constant and damping constant. Orbital eccentricity introduces a driving torque to cause the steady harmonic oscillations in pitch. <BR>There exist a cross-coupling between the roll and yaw motions due to the Coriolis forces, but if these cross terms are neglected and the time base transformation is performed, the roll equations reduce to the pitch equations. Therefore the results for pitch are applicable for roll. The effect of the coupling torque is to provide damping of the yaw motions. <BR>The method for selecting the parameters to yield optimum results is examined and the performance of the system for thus obtained parameters is that the time to half-amplitude is within 0.3 orbit and that the orientation error due to the orbital eccentricity is below 1.8° for the eccentricity of 0.01.
- 社団法人 日本航空宇宙学会の論文
社団法人 日本航空宇宙学会 | 論文
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