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本文考虑结构弹性,讨论控制飞轮的偏心对带太阳翼的三轴稳定地球同步卫星姿态运动的影响。使用Kane提出的新方法,建立系统的动力学方程组。提出一种能使方程组中姿态角变量与弹性形变量相分离的近似方法,以简化计算并有利于考虑弹性结构的阻尼效应。导出飞轮偏心引起的姿态角强迫振动的解析表达式,并进行数值计算给出各姿态角的幅频响应曲线。
This paper considers the structural flexibility and discusses the effect of controlling the eccentricity of the flywheel on the attitude movement of a three-axis stabilized geosynchronous satellite with a solar wing. Using the new method proposed by Kane, a system of kinetic equations is established. An approximate method is proposed to separate the attitude angle variables and the elastic deformations in the equations to simplify the calculation and to consider the damping effect of elastic structures. The analytic expression of forced vibration caused by flywheel eccentricity is deduced and the amplitude-frequency response curve of each attitude angle is given.