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In this work, we conducted a coupled dynamic loads analysis (CDLA) of satellites with an enhanced Craig–Bampton (ECB) approach to predict maximum response (acceleration, displacement, and stress). The satellite was subjected to a relatively high frequency launch vehicle (LV) interface load ( 20 – 50 Hz) when it was launched by multiple satellite launcher or experienced the combustion instability caused by LV instead of a typical low frequency LV interface load ( 0 – 10 Hz). To minimize the error caused by mode truncation, ECB-like formulation, which considers the effect of residual modes, is employed and computes the maximum response of the given dynamic system. By using this method, we found that the response by the ECB model is more accurate and efficient over the classical Craig–Bampton (CB) model due to the enhanced transformation matrix from being subjected to an unexpected high frequency LV load. To demonstrate this performance, we solved several benchmark problems associated with CDLA.