For double pressure peaks impact of gas-ejection, RNG k-ε turbulence model, Finite-Rate/Eddy- Dissipation model and layering dynamic mesh technique were adopted to establish an initial cavity secondary combustion numerical model with missile movement.Experimental data were used to verify the reliability of model.The effectiveness of smoothing pressure impact through increasing annular baffle was studied.The influence mechanism of main structural parameters of annular baffle on smoothing effect was analyzed by decoupling.A set of ideal structural parameters was obtained.The results show that as the number of annular partitions increases, the pressure peak is gradually reduced and smoothing effect of the four baffles is optimal.As the number of the height of bottom baffle increases, the pressure peak is decreased at first and then increases.When the height is 200mm, the pressure peak reaches the smallest.After baffles are arranged reasonably, the peak value of missile acceleration is reduced by 10.5%, and the velocity out of tube is decreased by 0.55% and the time out of tube is delayed by 2.6%.
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