172 J.M. Brown et al. Fig. 15.24 Thermal image of overheated ESC at a maximum recorded temperature of 105ı C Fig. 15.25 Photograph of overheated ESC Fig. 15.26 Closer inspection of burnt ESC 15.6 Conclusion The single rotor and quad-rotor platforms were successfully instrumented with a robust SHM system, and the value of the different sensors as damage classifiers was determined. Accelerometer information about structural vibrations proved to be the most informative measurement for damage, but temperature, power, and lift measurements also provided failure metrics. In some cases, such as vibrations in the frequency domain and temperature, the principles and damage classifiers of the single rotor platform transferred directly to the quad-rotor. Component interactions on the quad-rotor platform introduced coupling and application issues that made analysis of the magnitude of vibrations and power measurements more complex than the single rotor system. In general, data obtained from the sensors exhibited clear trends, which can be used to create statistical models for determining the current health of the vehicle. Complete damage prognosis will require additional collection of data from the SHM system, loading conditions, and environmental factors to build models that characterize a timeline for predicted failure. In the event of damage, these models can successfully estimate the remaining useful life of the vehicle and provide valuable information to actively alter or abort a mission.
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