【摘要】 针对当前航天器面向大型化、复杂化和精密化方向发展,为了提高航天器的使用寿命、运行精度和工作效率,考虑航天器主体和轴向运动柔性梁的刚-柔耦合作用是十分有必要的。基于Euler-Bernoulli梁理论以及刚-柔耦合建模方法,建立了航天器主体-轴向运动柔性梁刚-柔耦合系统的动力学模型。根据Hamilton原理推导出刚-柔耦合系统的动力学方程,采用分离变量法和振型叠加法求解耦合系统的动力学方程。利用四阶Runge-Kutta法进行数值计算。通过数值算例分析航天器主体半径、航天器主体面密度和柔性梁轴向速度对柔性梁横向振动以及对航天器姿态角的影响。更多还原

【Abstract】 Nowadays,spacecraft industry develops quickly to directions of large-scale,complicate and precision.Considering the rigid-flexible coupled effect of an axially moving flexible beam attached and a spacecraft’s main body is very necessary to improve service life,operation precision and working efficiency of the spacecraft. Here,based on EulerBernoulli beam theory and the rigid-flexible coupled modeling method in the flexible multi-body dynamics,the dynamic model for a rigid-flexible coupled system including an axially moving flexible beam and a spacecraft was established. The dynamic equations of the system were derived by using Hamilton principle. The dynamic equations of the system were solved with the separation variable method and the mode-superposition method. Several examples were numerically computed with the fourth order Runge-Kutta method. Finally,the effects of radius and areal density of spacecraft main body and axial velocity of flexible beam on the transverse vibration of the axially moving flexible beam and the attitude angle of the spacecraft were analyzed using the above several examples.更多还原