On the possibility to modify the performance of propellant mixtures used in RAMAC by addition of metallic particles

To explain the experimental results obtained in the 30 mm Ram accelerator a t ISL, showing that in the subdetonative mode, the terminal velocity of mag nesium projectiles at the end of Ramac tube is higher than the CJ detonatio n of the propellant gaseous mixture, whereas the projectile undergoes a mas s loss during the propagation, the assumption is made that metallic particl es ablated from the projectile react with the gaseous species and modify th e performances of the propellant mixture. The problem is examined by compar ing experimental and calculation results in an analogous situation of fine aluminum particles suspended in hydrogen-air mixtures. It is demonstrated t hat the classical thermodynamic model is unsuitable for explaining correctl y the experimental observations. Prediction of changes in performances of t he propellant mixture requires that two-phase now effects be taken into acc ount. These changes depend on the mass concentration, size and shape of the solid particles.