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。
The numerical simulation verified its feasibility in restraining the flexible appendage vibration, optimizing the maneuver time and promoting the system robustness in parameter Perturbation.
仿真结果表明该策略能成功地抑制柔性附件的振动及减小系统的机动时间，并使系统对参数的摄动具有鲁棒性。
The numerical simulation verified its feasibility in restraining the flexible appendage vibration, optimizing the maneuver time and promoting the system robustness in parameter Perturbation.
仿真结果表明该策略能成功地抑制柔性附件的振动及减小系统的机动时间，并使系统对参数的摄动具有鲁棒性。
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