摘要
本文在对长 甲运载火箭仪器舱进行了试验模态分析的基础上 ,对长 甲运载火箭仪器舱进行了可控约束阻尼层主被动一体化振动控制试验研究 ,研究结果表明 。
The experimental modal analysis of the apparatus cabin of CZ 3a launch vehicle is performed firstly.In response of the dynamic characteristics of the apparatus cabin the hybrid vibration control for instrument board of apparatus cabin is experimentally performed by applying controllable constrained layer damping.Research results show it is very effective that applying the controllable constrained layer damping suppresses the vibration of the apparatus cabin of the launch vehicle.
出处
《宇航学报》
EI
CAS
CSCD
北大核心
2002年第1期76-78,共3页
Journal of Astronautics
