부산대학교 도서관

Micro-vibrations on-board a satellite have degrading effects on the performance of certain payloads like observation cameras. There are numerous sources and extremely complicated transfer paths for micro-vibration in satellites. The vibration energy transfer characteristics of panels with multiple coupling forms in satellites were analyzed, which can guide the vibration isolation measures of satellites. First, the satellite was divided into honeycomb panel subsystems with multiple coupling forms. In the next phase, based on the energy finite element analysis (EFEA), the energy finite element equation of the honeycomb subsystem and the connection matrix at the coupling boundary was established to determine the energy distribution and energy flow characteristics of the multiform coupled honeycomb panels under different excitation frequencies. Finally, the finite difference approximation based on the response obtained from the measurement point array was employed to obtain the energy density. By comparing the results of the experiment and EFEA simulation under different frequency excitations, the average error of the energy density was less than 4 dB, which proved the accuracy of EFEA in the transfer characteristics analysis of the vibration energy of the satellite. The experiment method of vibration transfer based on the finite difference approximation can directly obtain the energy density of the structure.