ESCI SJR: 0.149 SNIP: 0.16 CiteScore™: 0.29
ISSN 打印: 2150-766X
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Ignition and Unsteady Combustion of AP-based Composite Propellants in Subscale Solid Rocket Motors
Office National d'Etudes et de Recherches Aerospatiales Chatillon, France
The description of the unsteady combustion mechanisms of solid propellants and the numerical solution of the solid rocket internal flow are the two key factors in determining the unsteady behavior during the ignition transient inside a solid rocket motor. The objective of this study is to develop a numerical tool able to predict the flow-solid propellant interaction responsible for the ignition process. The numerical package developed for the simulations comprises a multi-dimensional CFD code using a k-∈ turbulence model which is associated with two main components: a one-dimensional unsteady heat conduction analytical solution for the propellant surface temperature or burning rate and a one-dimensional Couette flow solution for the wall boundary layer. In addition, one considers that an ignition propagation occurs by conduction at the gas side propellant surface when the critical inflammation conditions to sustain such a propagation are satisfied.
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