摘要
在研究整星隔振过程中发现,整星的摇晃振动模态和纵向振动模态密切耦合,根据整星隔振系统基频下降的设计限制,仅采用一般的隔振器,其纵向隔振性能不易满足设计指标。针对某卫星的隔振设计要求,提出由七连杆防摇机构和隔振器组成的整星隔振防摇方案,通过有限元模型的模态分析和缩比卫星模型的性能测试,验证此方案的可行性,即在不提高整星的纵向振动模态频率下,提高摇晃振动的模态频率。
Several isolation systems have been proposed in recent years for isolating the payload from the launch vehicle vibrations. Because the rocking mode and axial bounce mode are coupled toughly, most of the proposed isolation units can't solve the conflicting requirement of low axial stiffness to attenuate axial vibration along with high rocking stiffness. In this paper, a whole-spacecraft vibration isolation system is presented for one specific type of spacecraft. The advocated vibration system consists of a mechanism that prevents the payload from rotating rocking and about the long axis of the launch vehicle. The other component of the system consists of dozens of isolators which reduce the payload vibration in the axial and the lateral directions. The finite element model of the whole-spacecraft isolation system and the modal test of the small scaled whole-spacecraft model prove the isolation system feasible.
出处
《噪声与振动控制》
CSCD
北大核心
2005年第2期29-32,共4页
Noise and Vibration Control
关键词
振动与波
卫星
整星隔离
隔振器
防摇机构
模态
vibration and wave
the satellite
the whole-spacecraft isolation
isolator
anti-rocking mechanism
mode
