带有阻尼机构的多柔体航天器动力学建模

对通过阻尼机构连接的多柔体航天器动力学问题进行研究，考察的系统由航天器本体、若干六自由度刚性阻尼平台以及固连于阻尼平台的大柔性附件构成，阻尼平台与航天器本体之间以弹性 阻尼装置连接，为典型的多柔体系统.以混合坐标描述系统的运动，利用Kane方程建立了具有较强通用性且有利于系统控制器设计的含有约束阻尼的动力学模型.数值仿真结果表明，阻尼器可有效衰减柔性附件的振动，有利于星体受扰后的快速稳定

Dynamic Modeling of Flexible Multi Body Spacecraft with Damping Mechanism

The dynamics of spacecraft with root damper of antenna mast is investigated. The system consists of a spacecraft main body, several six freedom rigid damper platforms and flexible appendages which are connected with the damper platforms. The damper platforms are connected with the main body by elasticity damp mechanisms. Hybrid coordinates are used to describe the system motion. System dynamics which are established via using Kane’s equations have better versatility and are advantageous to controller design. Numerical simulation results show that the damper can efficiently attenuate elastic vibration of the appendages, which is beneficial for spacecraft rapid stabilization after disturbance.