비선형 연소 불안정을 적용한 고체로켓모터의 내탄도 해석

Combustion instability prediction poses an obvious threat to the structural stability and performance of the motor. Elevated pressures modify the burning rate, local surface mean flow Mach number, and the apparent response function of the propellant. This phenomenon generates when acoutic mode was coupled with frequency that occurs in the combustion/flow process. In this paper, for analysis acoustic phenomenon in solid rocket motors, a nonlinear acoustic instability model which is derived from the nonlinear wave equation and is combined with the linear acoustic instability model applied to internal ballistics. The influence was concerned with combustor configuration, chamber pressure and burning rate by using this analysis method. Finally, the stability of the solid rocket motor with extending into slot was determined to perform the one-dimensional internal ballistics that was considered with erosive burning and linear/nonlinear acoustic instability analysis.