Nine solid rocket propellants consisting of a com. rubber binder, NH4NO3, NaNO3, KNO3, Al/Mg and Al powders, dimeryl diisocyanate and dioctyl adipate were characterized by thermodynamic calculations. Three of the propellants were tested exptl. for friction and impact sensitivities, hardness, calorific value, decompn. temp., and combustion time. The emission of HCI in the combustion product was decreased down to below 1%.