Abstract: Constrained layer damping technique is applied as an effective passive vibration control method for aerospace structures. The approach of adding viscoelastic damping to a satellite flywheel bracket is investigated in this paper. Firstly, the finite element model of the bracket is built and the vibrationmode analysis is executed to obtain basic dynamic characteristics. Distribution of modal strain energy is analyzed to determine the locations where the constrained dampers are attached. Then, the thicknesses of the constrained layer and damping layer are taken as design parameters to examine the modal loss factors for different design schemes. The optimal values of the parameters are determined under the limitations of additional weight of the dampers and the cost for damping material processing. Finally, the acceleration frequency responses of the flywheel bracket with damping and without damping, respectively, are compared mutually. The results show that applying viscoelastic constrained layer damping for flywheel bracket is reasonable and effective.

Key words: vibration and wave, satellite flywheel bracket, constrained layer damping, vibration control

摘要： 应用粘弹性约束阻尼减振技术对某卫星飞轮组件安装支架结构进行振动抑制处理。约束阻尼技术能在不对结构作大的修改的前提下，提高结构的阻尼能力。首先建立原型支架结构的有限元模型，计算了其动态特性。分析了支架结构关键模态的应变能分布规律，确定出约束阻尼处理的铺敷位置。采用参数优化方法，比较了不同约束层厚度、不同阻尼层厚度设计情况下的结构阻尼性能，在满足附加重量和工艺限制要求的前提下，确定出阻尼减振设计方案。最后，将阻尼前后支架结构的加速度频率响应结果进行了对比，验证了在飞轮安装支架上应用粘弹性阻尼减振的合理性和有效性。

关键词: 振动与波, 飞轮安装支架, 约束阻尼处理, 振动控制