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Regression Analysis on Estimated Burn Rate of Composite Propellants

J K Bhushan

Abstract


The necessity of solid propellants in rocketry arises due to its high thrust requirements. Solid propellants are generally of two categories: homogeneous and heterogeneous solid propellants. Heterogeneous or composite solid propellants contain solid particles dispersed in a binder which altogether. Present study is aimed at achieving a fundamental understanding of the microscopic features of composite solid propellant combustion with bimodal distribution of oxidizer particles. Based on the samples prepared, the burning rate trends are investigated. The studies are pursued at different values of the composite compositions as well as for an appreciable range of pressure. The linearity in the burn rate with respect to increase in pressure on the rocket motor was found and the regression analysis was made on the results.


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References


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