THEORETICAL INVESTIGATION OF EROSIVE BURNING OF SOLID PROPELLANTS
BRUSSELS UNIV (BELGIUM)
Pagination or Media Count:
After a critical survey of existing theories of erosive burning and of published experimental data, the combustion mechnism of NH4Cl04 propellants is discussed and a model of erosive burning of these formulations is proposed. Erosion is assumed to smooth the surface whose burning rat is then controlled by oxidizer regression, no energy being supplied by the main diffusion flame. Furthermore the adiabatic decomposition temperature of the perchlorate is assumed to be obtained at the end of the laminar sublayer whose thickness can be related to mean flow velocity through fluid dynamics. Correlation of test data permits to determine the transition point. Grain design and motor scale are taken into account through local hydraulics radius. Low pressures, large radii and high burning rates are shown to reduce erosive burning. An attempt is made to explain irregular burning by surface nature and roughness, through erosivity.
- Solid Rocket Propellants