Investigation of the basic parameters for alternative solid rocket propellant engines for research and civilian use

Abstract

Investigation of the basic parameters for new generation of alternative solid rocket propellant engines for research and civilian use was implemented. This was caused from needs for substitution of the widely used construction materials of the aircraft units based on polymers and of petroleum composites. Numerous fire tests, both static and flight, in a real working environment of a new generation of environmentally friendly solid rocket propellant engines that are completely degradable in the nature were carried out. The obtained results after burning of rocket fuel for internal engine ballistics and thermo-mechanical coupled characteristics of composite materials are presented.