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• W2316899238 abstract "We examine the combustion response of homogeneous and heterogeneous solid propellants to an imposed velocity field, as a model for erosive burning. The imposed velocity field has its roots in a multiscale analysis of a planar or cylindrical rocket. For homogeneous solid propellants we show that for certain realistic choices of the parameters both positive and negative erosion can take place. The underlying mechanism for erosive burning is flame stretch, induced by the imposed velocity field. For heterogeneous solid propellants we show enhancement of the burn rate as a function of propellant morphology. I. Introduction - the basic model Over the past decade a considerable amount of effort has been dedicated to computational simulations of heterogeneous solid propellant combustion. This work has a number of ingredients, the most important of which are: a random-packing model of the propellant that simulates particles of oxidizer embedded in fuel-binder; homogenization into an oxidizer/fuel blend of particles too small to be numerically resolved; unsteady three-dimensional heat conduction within the solid, that takes into account material properties of the different ingredients; a gas-phase description using the zero Mach-number Navier-Stokes equations and global kinetics; a representation of the propellant surface that is either explicit or implicit (via a level-set strategy); a full coupling between the solid and the gas across the surface; and the ability to account for the presence of aluminum particles. The complete code can predict the effects of morphology on burning rates; provide insights into the nature of the combustion field; calculate the amplitude and phase-shift of an acoustic wave impinging on the burning propellant, a matter of great importance in rocket chamber stability; predict the velocity and temperature fluctuations on the millimeter scale above the surface, boundary conditions for LES simulations of the chamber flow; provide a foundation for a rational one-dimensional description of the combustion field, needed for whole-rocket simulations on large length scales; provide a framework for modeling aluminum agglomeration; and provide a framework for erosive burning investigations of both homogeneous and heterogeneous propellants. Figure (1a) is a cartoon of the combustion system, and gives some sense of its complexity. In examining" @default.
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• W2316899238 date "2009-08-02" @default.
• W2316899238 modified "2023-09-27" @default.
• W2316899238 title "Erosive Burning of Homogeneous and Heterogeneous Solid Propellants" @default.
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• W2316899238 doi "https://doi.org/10.2514/6.2009-5498" @default.
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