NUMERICAL AND PARAMETRIC STUDY OF ALUMINU M PARTICLE COMBUSTION

Several numerical models have been investigated to study the reactivit y of aluminium particles coming from the combustion of solid propellan ts in spatial launchers. The Law model has been rapidly selected as it yields a continuous model from an aluminium drop to an oxide drop. Th e model also gives the residue size at the end of the combustion proce ss. This could explain the scaling observed in the rocket engines. In order to study the coupling between the flaw and the combustion, the c ombusion of aluminium drops has been widely analyzed with 0D computati on. The main mechanisms of the combustion process have been identified .