空间飞行器阻尼减振设计与应用  

Damping vibration reduction design and application for spacecraft

作　　者：李海岩[1] 廉永正 吕静[1] 王彬[1] 张盛[3] 

机构地区：[1]中国运载火箭技术研究院研究发展中心,北京100076 [2]北京宇航系统工程研究所,北京100076 [3]大连理工大学工业装备结构分析国家重点实验室,辽宁大连116024

出　　处：《计算机辅助工程》2016年第6期58-62,共5页Computer Aided Engineering

摘　　要：在空间飞行器结构设计中,为改善仪器设备的振动环境,基于结构模态特性和动力学响应的关系,以某型号空间飞行器为例开展阻尼减振设计.通过仿真分析及地面试验,对减振设计的有效性进行验证.结果表明:在结构模态中的最大应变部位周围附加阻尼层可有效降低结构振动.结构测点在共振峰附近的放大倍数显著降低,最大降低幅度超过90%;结构测点的随机振动响应量级降至设备耐受能力范围之内,阻尼减振设计达到预期目的.To optimize the vibration environment for equipment in the procedure of spacecraft structural design,the damping vibration reduction design of a certain type of spacecraft is done based on the relationship between the structural modal feature and dynamic response. The effectiveness of the vibration reduction design is validated by simulation analysis and ground experiments. The results show that the structural vibration can be effectively reduced by adding damping layer around the maximum strain area.The amplification factor near the resonance peak is significantly reduced and the maximum reduction range is more than 90%. The random vibration response of the structural measure point is reduced to the range of tolerance capability. The damping vibration reduction design achieves the expected goal.

关 键 词：空间飞行器 振动 约束阻尼 减振 模态特性 动力学响应 有限元 试验 

分 类 号：V423[航空宇航科学与技术—飞行器设计]