PASSIVE ISOLATION VIBRATION SYSTEM FOR OPTICAL SATELLITE PAYLOADS

Reduction of low frequency vibration of a satellite, due to environmental conditions and operation of internal components, produces better conditions for the optical payloads. In this paper, a passive isolation system, placed between the optical payload and satellite structure, has been considered and its effect on the reduction of dynamic loads has been studied. The design and geometrical modeling of the isolation system have been carried out using CAE software, and the finite element analysis of the remote sensing satellite structure has been performed with the isolation system in place. The results so obtained were compared with the case of no isolation system. Results indicate thatwhen using the isolation system, the displacements due to the vibrations in the plate of the payload structure are much less than the corresponding displacements of the isolation system base plate. Power spectral density and time history of the acceleration response of the payload shows the RMS of the acceleration response was reduced by ۸۹%.

Keywords:

Vibration , Isolation , Satellite , Payload