20. Studying the possibility of alternating delivery of rocket propellant wastes to a common thermal neutralization facility

Annotation: The possibility is considered of using rocket propellant thermal neutralization units for decontamination of dangerous industrial wastes. The advantages of thermal neutralization units are considered, their operating principle is described, by the example of high-temperature toxic rocket propellants, the chemical reactions that take place in combustion chamber are formulated. The combustion chamber is a component of the neu tralization unit, it is in the combustion chamber, in the environment of created high temperatures, that the process of elimination of dangerous substances takes place. Taking into consideration the high cost of neutralization units, which will be a factor hindering the wide-scale introduction of neutralization units to decrease technogenic load on environment of Ukraine, the option is proposed of reducing the costs during the use of thermal neutralization units by way of combining the function of oxidizer neutralization unit and fuel neutralization unit in a single universal neutralization unit. The article substantiates the topicality and necessity of works to create the universal thermal neutralization unit from the viewpoint of economic and ecological aspects. The article presents a generalized description of technology and methodology of research tests of pilot samples of assemblies for high-temperature rocket propellants vapor and industrial wastewater supply into the neutralization unit. The assemblies for high-temperature rocket propellants vapor and industrial wastewater supply are considered as most critical components of the universal neutralization unit from the viewpoint of neutralized substance changing. The experiments were conducted on water solutions of rocket propellants that in this case simulated the contact of internal cavities of supply assemblies with aggressive toxic media. The conditions were created at which the probability existed of interaction of rocket propellants residues in stagnation zones at the moment of changing the supplied propellant component. In the frameworks of research tests of pilot samples, the obtained results were considered and analyzed. The findings are presented that confirm practical feasibility of using integrated supply assemblies.