摘要
在侧挂构型发射任务中,中心承力筒与卫星直接连接,其动力学特性对卫星的振动响应有直接影响。首先分析中心承力筒的模态特性,据此完成粒子阻尼器的结构参数设计。随后,使用有限元--离散元耦合仿真方法,确定了阻尼器填充粒子的最佳直径和阻尼器最佳安装位置。仿真结果表明,该方案下星箭界面减振效果可达40%。最后,使用最优粒子阻尼参数开展水平激励实验。实验结果表明,与未安装粒子阻尼器相比,中心承力筒+粒子阻尼器组合体的减振效果可达35%以上,与仿真结果一致。
In the side-mounted configuration launch mission, the central bearing tube is directly connected to the satellite, and its dynamic characteristics directly impact the satellite’s vibration response. Firstly, the modal characteristics of the central bearing tube are analyzed, and then the structural parameters of the particle damper are designed. Secondly, using the coupling simulation method of the finite element-discrete element, the optimal diameter of the filler particles in the damper and the optimal position of the damper installation are determined. The simulation results show that the vibration reduction of the satellite-launch vehicle interface can reach 40% under this scheme. Finally, horizontal excitation tests are carried out with the optimal particle damping parameters. The test results show that the vibration reduction of the scaled model of the combination of ″central bearing tube & particle damper″ can reach more than 35%, which is consistent with the simulation results.
作者
肖望强
曾玉梅
张新宇
潘忠文
任兴宇
XIAO Wangqiang;ZENG Yumei;ZHANG Xinyu;PAN Zhongwen;REN Xingyu(School of Aerospace Engineering,Xiamen University,Xiamen 361000,China;Beijing Institute of Astronautical Systems Engineering,Beijing 100076,China)
出处
《宇航总体技术》
2022年第6期1-8,共8页
Astronautical Systems Engineering Technology
基金
国家自然科学基金项目(51875490)
中央高校基本科研业务费专项资金项目(20720210042)
慧眼行动项目(9350DC58)。
关键词
粒子阻尼
中心承力筒
减振
有限元—离散元
Vibration reduction
Central bearing tube
Particle damping
Finite element-discrete element
