Based on the Newton's law of motion,the law of angular momentum and the variation principle,the dynamic model of the satellite with a flexible appendage has been researched. Using this dynamic model,the influences of the flexible solar-array's rotation have been discussed.2.
主要内容有五个方面：1、运用牛顿定律、角动量定律和变分原理建立了带挠性附件的卫星动力学模型，分析了挠性太阳帆板转动对卫星动力学模型的影响。
参考来源 - 挠性卫星动力学建模与控制系统研究·2,447,543篇论文数据，部分数据来源于NoteExpress
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。
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