Launch Vehicle Dynamic and Control Effects from Solid Rocket Motor Slag Ejection

Current solid-propellant rocket instability calculations (e.g., Standard Stability Prediction Program) account only for the evolution of acoustic energy with time. However, the acoustic component represents only part of the total unsteady system energy; additional kinetic energy resides in the shear waves that naturally accompany the acoustic oscillations. Because most solid-rocket motor combustion chamber con gurations support gas oscillations parallel to the propellant grain, an acoustic representation of the ow does not satisfy physically correct boundary conditions. It is necessary to incorporate corrections to the acoustic wave structure arising from generation of vorticity at the chamber boundaries. Modi cations of the classical acoustic stability analysis have been proposed that partially correct this defect by incorporating energy source/sink terms arising from rotational ow effects. One of these is Culick's ow-turning stability integral; related terms that are not found in the acoustic stability algorithm appear. A more complete representation of the linearized motor aeroacoustics is utilized to determine the growth or decay of the system energy with rotational ow effects accounted for already. Signi cant changes in the motor energy gain/loss balance result; these help to explain experimental ndings that are not accounted for in the present acoustic stability assessment methodology.

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Launch Vehicle Dynamic and Control Effects from Solid Rocket Motor Slag Ejection

Cited by 6 publications

References 12 publications

Experimental Characterization of a Two-Phase Flowfield in a Solid Rocket Motor Model

Experimental Characterization of a Two-Phase Flowfield in a Solid Rocket Motor Model

Single-Phase Internal Flowfield Validation with an Experimental Solid Rocket Motor Model

Aeroacoustic instability in rockets

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