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。

The attitude dynamic equations of a spacecraft with flexible appendages are obtained by using the momentum theorem.

youdao

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。

The attitude dynamic equations of a spacecraft with flexible appendages are obtained by using the momentum theorem.

youdao