Abstract
The post-processing analysis tools, Short Time Fourier Transform (STFT) and Dynamic Mode Decomposition (DMD) were applied to analyze dynamic characteristics of the GH₂/GO₂ rocket model combustor. The STFT analysis was performed with pressure data in the chamber to exhibit the appearance of frequency components at instant time. The STFT results indicate resonant frequencies of signal through their amplitudes. DMD analysis was conducted with the planar pressure data to extract the resonant frequencies and damping coefficients of acoustic modes. The damping coefficient is a parameter to evaluate the stability of a certain pressure oscillation in a dynamic system. By combining the results of STFT and DMD, the appearance of the resonant frequencies causing unstable combustion can be determined.
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