微小卫星帆板展开火工冲击减振结构研究  

RESEARCH ON PYROSHOCK REDUCTION STRUCTURE WHEN MICRO SATELLITE DEPLOYS THE SOLAR ARRAY

作　　者：姜姝羽 谷松[1,3] 陈善搏 

机构地区：[1]中国科学院长春光学精密机械与物理研究所,长春130033 [2]中国科学院大学,北京100039 [3]长光卫星技术有限公司,长春130000

出　　处：《机械强度》2018年第1期33-38,共6页Journal of Mechanical Strength

摘　　要：以某卫星太阳帆板展开时卫星本体所受的冲击为研究对象,设计了一种蜂窝夹层板式冲击减振装置。从减振设计的角度出发,对冲击响应动力学模型、冲击减振设计要点进行了详细的说明。通过引入弹簧单元等对蜂窝夹层板及附属结构进行改进,并对该系统法向进行冲击特性试验研究,分析了该冲击减振装置应用于卫星后的动力学响应。结果表明,蜂窝夹层板减振装置具有良好抗冲击性能,应用于卫星单机安装板,能够有效减少冲击响应,同时满足发射条件,该设计合理。A kind of pyroshock reduction device of honeycomb sandwich plate is designed,which takes the impact as the research object when satellite deploys the solar array. The dynamic model of shock response and the key points in design are explained in detail from the view of vibration reduction. Spring element was introduced to improve the honeycomb sandwich plate and its accessory structure,then,the shock characteristics of the system wartested. Dynamic response of satellite after setting the damping device was analyzed. The result indicates that the honeycomb sandwich plate on mounting plate can effectively reduce shock response,and meet the launching condition,so the design is reasonable.

关 键 词：卫星 太阳帆板 冲击减振 蜂窝夹层板 

分 类 号：V414[航空宇航科学与技术—航空宇航推进理论与工程]