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本文采用虚功形式的d’A1embert原理建立了带弹性附件的卫星的姿态动力学方程。方程便于与有限元程序结合。对于非自旋卫星,可以给出线性化的方程。文中建议以各阶约束模态的角动量系数对弹性附件的惯矩的贡献作为降价的参考较为方便。文章给出了一个数字例。
In this paper, we establish the attitude dynamics equation of a satellite with elastic attachments using the principle of virtual reality, d’A1embert. The equation is easy to combine with the finite element program. For non-spin satellites, a linearized equation can be given. In this paper, it is suggested that the contribution of angular momentum coefficient of each constraint mode to the moment of inertia of attachment should be used as a reference for price reduction. The article gives a numerical example.