小卫星舱体结构粘弹性阻尼减振优化设计

Multi-objective design optimization of viscoelastic damping structures for small satellite applications

航天器发射段动环境恶劣,需要考虑对结构进行阻尼减振设计。小卫星内部空间狭小,结构轻质化要求高,须采用自动优化设计方法进行阻尼处理敷设位置和几何参数同时优化。针对小卫星结构阻尼减振的要求,分析了初始无约束阻尼结构的动力学特性,确定出约束阻尼处理的部位;提出一种基于Layerwise有限元分析和多目标优化的粘弹性阻尼结构优化设计方法,采用非支配遗传算法求解优化问题,获得了同时兼顾附加质量和阻尼性能要求的优化结果。结果表明,对小卫星舱体安装结构进行局部粘弹性阻尼处理能够显著降低敏感设备的动响应,提出的优化方法能够同时实现阻尼敷设位置和几何参数的同时优化。

Viscoelastic damping treatment is an effective way to reduce structural vibration for spacecraft during liftoff. A simultaneously sticking positon and geometry parameter optimization is necessary for small satellites for their light weight and crawl space. In this paper, the finite element model of the satellite struc- ture without damping treatment is first analyzed to decide the treatment region. A novel optimal design me- thod based on layerwise finite element and multi-objective optimization is present. The optimization prob- lem is solved by non-soring genetic algorithm. Benefit from this method, a simultaneous minimization of added mass and maximization of damping performance is achieved. The results show that applying locally viscoelastic constrained damping treatment for the small satellite structure is reasonable and effective, and the proposed method is an effective method for simultaneous material layout and geometric optimization of viscoelastic damping structures.