The attitude dynamic equations of a spacecraft with flexible appendages are obtained by using the momentum theorem.
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 coupled dynamic equations of a spacecraft with tip mass attached flexible appendage which is deployable are obtained by using the momentum theorem.
结构复杂的航天器带有几十米、上百米大型挠性附件，附件末端还带有大质量刚体。
Using CBL technique, the theorem of momentum with changing force is tested. The experimental principle and procedure are introduced.
利用CBL技术在变力作用下验证了动量定理，并介绍了实验原理及实验步骤。
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