Dynamic characterization of a lightweight, highly maneuverable spacecraft using modal and finite element analyses

摘要

The Lawrence Livermore National Laboratory is engaged in a technology development project which includes designing a lightweight, autonomous, highly maneuverable space vehicle, commonly referred to as a probe. The current probe design includes a guidance and control system that requires complete information on the dynamic response of the probe during operation. A finite element model of the probe was constructed to provide analytical information on the dynamic response to specific operational inputs. In order to verify the assumptions made in the model, a mass mock-up of the probe was constructed at LLNL and an experimental modal survey was performed to determine the frequencies, damping values and deflection shapes for each natural mode of the mock-up. The experimental modal parameters were compared with the parameters obtained through modal analysis of the finite element model to provide a measure of the correlation between the model and the actual structure. This report describes the experimental modal testing and analysis of the mass mock-up and compares the experimental results with the finite element results.