整星隔振防摇装置的研究  

Research on the Anti-Rocking Mechanism of the Whole-Spacecraft System

作　　者：张军[1] 梁启明[2] 谌勇[1] 张志谊[1] 华宏星[1] 

机构地区：[1]上海交通大学振动冲击和噪声国家重点实验室,上海200240 [2]上海船用柴油机研究所,上海200011

出　　处：《噪声与振动控制》2005年第2期29-32,共4页Noise and Vibration Control

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.

关 键 词：振动与波 卫星 整星隔离 隔振器 防摇机构 模态 

分 类 号：V447[航空宇航科学与技术—飞行器设计]