带挠性伸展附件的航天器姿态动力学研究

Attitude dynamics of a spacecraft with deploying flexible appendages

利用动量矩定理推导出带挠性伸展附件航天器的动力学方程。在挠性附件按指数规律和幂次规律伸展情况下，研究了附件伸展运动对弹性振动和航天器姿态的影响，得到了附件振动的振幅和姿态角速率随附件长度变化的渐近公式，得到航天器最大姿态偏差的估计式。结果表明：随着附件长度的增加，附件振动的振幅增大，而姿态角速率减小。最大姿态偏差值随着伸展速率的增加而减小。

The attitude dynamic equations of a spacecraft with flexible appendages are obtained by using the momentum theorem. The attitude dynamics of the spacecraft and the vibrations of the appendages under the influence of the extension of the appendages are investigated. The approximate formulations are given for the amplitudes of vibration of the appendage and the attitude angular velocity of the sapcecraft during exponential extension and deployment when the n th power of length varies linearly with time. A formulation of maximum attitude deviation of the spacecraft is obtained. The formulations provide results that as the length of the appendages increases, the amplitudes of vibration increase, the attitude angular velocity decreases, whereas the maximum attitude deviation decreases as deployment velocity increases.