This paper presents technological research on the storage time of a composite rocket propellant with a low HCl content in combustion products, based on sodium nitrate. For research were prepared and casted in laboratory scale, a composite rocket propellant based on sodium nitrate and HTPB system, and as the reference sample, the classic composite rocket propellants based on the HTPB/AP system. Both propellants have been subjected to laboratory-scale aging in accordance with the STANAG accelerated aging protocol, by 5 and 10 years. For each propellant, aged and not aged, parameters such as calorific value, hardness, sensitivity to the mechanical stimuli and decomposition temperature were determined. For the ballistic evaluation of the investigated propellants, the Laboratory Rocket Motor technique with the indirect burning rate determination method, was used. Based on the obtained data, was found that the composite rocket propellants based on sodium nitrate are technological and can be used in the rocket propulsion applications.