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- W2183699972 abstract "SUMMARY OF RESULTS A one-dimensional, nonlinear analysis of transverse mode instability in a solid pro- pellant rocket geometry indicated the relative combustion stability based on three para- metric groupings: burning rate, wall-loss, and viscous-dissipation parameters, of which only the burning rate parameter appeared to be significant in the one-dimensional model with a nonvibrating solid phase. The results of the analysis, presented as the minimum pressure amplitude required to incite instability as a function of the burning rate parameter, showed that erosive burning was an important factor in determining sta- bility. With only a 10-percent contribution to the burning rate due to erosion, the sta- bility boundary was significantly affected so as to reduce the stable region of operation. A two-fold increase in the pressure exponent in the burning rate law also showed a de- crease in the stable operating regime. This effect was not as pronounced as the erosive effect. Increasing the" @default.
- W2183699972 created "2016-06-24" @default.
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- W2183699972 date "1966-01-01" @default.
- W2183699972 modified "2023-09-27" @default.
- W2183699972 title "ONE-DIMENSIONAL NONLINEAR MODEL FOR DETERMINING COMBUSTION INSTABILITY IN SOLID PROPELLANT ROCKET MOTORS" @default.
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