Efficient, Intelligent Solution for Viscous Flows Inside Solid Rocket Motors

摘要

An efficient, intelligent method has been developed for the solution ofaxisymmetric, compressible viscous flows inside solid rocket motors. The method applies an adaptive, unstructured, finite-element mesh generation technique and a cell-centered, second-order, flux correction transport scheme for the solution of Navier-Stokes equations. With known, initial motor interior configuration, the method developed in this study allows the computational boundaries to be determined intelligently, the finite-element meshes and remeshes to be generated efficiently, and the corresponding compressible viscous flow fields to be produced expeditiously. Very good agreement between analysis results and test data is obtained for flow inside the Jet Propulsion Laboratory nozzle. Application of the method to analyze flows inside the Titan IV solid rocket motor upgrade and the Star-48 motor with very complicated chamber and nozzle geometry is illustrated.