摘要
基于单向递推组集方法,对带柔性附件的航天器进行动力学建模,研究了航天器姿态耦合系数的计算方法.单向递推组集建模方法相比传统线性化方法,其计算结果更精确,推导过程完全依照刚柔耦合动力学模型,完整保留了挠性附件弹性振动对系统质心和转动惯量的影响,未作多余近似假设.仿真算例表明,该方法计算系统的耦合系数具有更高精确性,说明了单向递推组集方法相比传统方法在挠性航天器系统刚柔耦合动力学问题中的优越性.
Dynamic forward recursive formulation of rigid-flexible coupled multi-body system is an important modeling theory of dynamics, which will not only reduce the workload but also avoid the accumulated error. It is apt to the exact solution when applied to complex systems because it retains the influence caused by elastic vibration of flexible parts to the center of mass and moment of inertia. In this paper, the general type of forward recursive formulation to rigid-flexible coupled spacecraft system was applied, and the higher accuracy in calculation was expounded. Finally, through numerical calculation, advantage of the forward recursive method in handling the coupling of flexible system than that of the traditional method was verified.
出处
《空间科学学报》
CAS
CSCD
北大核心
2012年第4期550-554,共5页
Chinese Journal of Space Science
基金
博士点基金项目(20090073110009)
上海市自然科学基金项目(11ZR1417000)共同资助
关键词
单向递推
耦合系数
挠性系统
动力学仿真
Forward recursive formulation, Coupling coefficient, Flexible system,Dynamic simulation
