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PROPAGATION OF WEAK DISCONTINUITIES IN ROCKET MOTOR COMBUSTION CHAMBERS, PART I,
PURDUE UNIV LAFAYETTE IND JET PROPULSION CENTER
An important feature of the non-linear or nonacoustic theories of combustion pressure oscillations in rocket motors is the occurrence of weak shock-like discontinuities. The magnitude of such a discontinuity changes as it propagates in the motor due to its interaction with the different processes and gradients in flow properties occurring in the combustion chamber. The subject report presents an analysis of the interaction of the discontinuity with those processes and gradients as well as a method for computing the instantaneous magnitude of the weak shock-like discontinuity at different sections of a combustion chamber. While the method developed here is general enough for adaptation to any chemical rocket system, the particular case chosen for explaining the details of the method is related to a rocket motor equipped with an end-burning solid propellant grain. Author