Abstract
Researchers at the Air Force Institute of Technology (AFIT) and Operationally Responsive Space (ORS) Office have conducted extensive vibration testing and structural modeling on the first ORS Plug-and-Play Satellite (PnPSat I). This research represents an initial step in evaluating the premise that current postintegration spacecraft environmental test requirements can be reduced or modified using accurately tuned finite element (FE) models to predict the dynamic response of various configurations of PnPSat. This research started with modal testing of two PnPSat I spacecraft structural panels followed with the tuning of FE models of the satellite panels. A complete structural model of the satellite was created from copies of the tuned panel FE models, and with the addition of satellite components, one complete satellite configuration was created. This complete satellite FE model was tuned using natural frequency data extracted from random vibration frequency response functions collected from accelerometer data. The first three natural frequencies of the tuned FE model match the measured within +/-5% for PnPSat I. The eventual goal is to evaluate the FE model for various PnPSat configurations in a frequency range of 0-300 Hz.
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