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An experiment was conducted to establish the critical role of a detailed aspect of the amelet structure in composite propellants in determining the overall combustion response to pressure oscillations during combustor instability. Nomenclature a b = velocity of sound of gases in T-burner g c = units conversion factor L = length of interior cavity of T-burner R p = pressure-coupled response function r = burning rate S b = cross-sectional area of cavity of T-burner S c = burning surface area of propellant sample c = combustion ampli cation d = burner damping during burning 1 = exponential growth rate during burning, decay rate in pulse test 2 = decay rate after burnout 2 (t 1 ) = decay rate corrected to frequency during burning s = density of solid propellant