Development of Commercially Useable Codes to Simulate Aluminized Propellant Combustion and Related Issues.

摘要

We have modified and developed a large number of codes relevant to the task including: a packing code to generate propellant morphology models; a homogenization code to predict homogenized properties of a heterogeneous propellant; a combustion code that predicts fluctuations in the hot gases coming off the propellant surface; and fluids codes that describe the rocket chamber flow, the rocket nozzle flow, aluminum transport, and nozzle erosion. The packing code is marketable; the homogenization code will be available as an addendum to the packing code in a few months; a fluids code that simulates the chamber flow using approximations valid for slender chambers is marketable, albeit without a user manual at this time; and further development of a nozzle code that accounts for nonuniform inlet conditions (at the nozzle inlet) is under further development under a recently awarded SBIR contract.