Finite Element Model Optimization of the FalconSAT-5 Structural Engineering Model
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Space launch vehicles produce tremendously harsh environments for their payloads. One of the worst contributors to this harsh environment is vibration. Launch vehicle contractors require accurate dynamic models in order to perform coupled loads analyses with each payload to mitigate risks. Accurate predictions of the dynamic response of the payload are not achieved easily. The Finite Element (FE) method has proven to be the best approach in creating accurate dynamic models of complex structures. To improve the agreement between and FE model and the structure it represents, a common practice is...
Space launch vehicles produce tremendously harsh environments for their payloads. One of the worst contributors to this harsh environment is vibration. Launch vehicle contractors require accurate dynamic models in order to perform coupled loads analyses with each payload to mitigate risks. Accurate predictions of the dynamic response of the payload are not achieved easily. The Finite Element (FE) method has proven to be the best approach in creating accurate dynamic models of complex structures. To improve the agreement between and FE model and the structure it represents, a common practice is to 'tune' or adjust parameters of the FE model to match experimentally measured data. In order to collect spatially dense and accurate dynamic responses from a satellite, a Polytec laser vibrometer is used which measures the Doppler shift to determine the frequency response from an excitation. To illustrate the benefits of employing this approach, a process is developed to measure dense modal data and tune an FE model of the US Air Force Academy's FalconSAT-5 Structural Engineering Model. The first step in the process developed in this research involves measuring and tuning models of the satellite structure panels individually.
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