OPTIMIZATION OF THE DESIGN OF PULSE SOLID-PROPELLANT ROCKET ENGINES WITH METAL BODIES BY THEIR ASSOCIATION IN THE MONOBLOCK COMPARTMENT MADE OF HIGH-STRENGTH PLASTIC

The article concerns the pulse solid-propellant rocket engines intended for flight control of aerodynamic and space objects. Flight control of aerodynamic and space objects can be implemented by means of the solid-propellant rocket engines equipped with special devices, allowing changing a thrust vector direction (rotating nozzles, jet vanes, etc.). However, these devices do not always provide the necessary dynamics of thrust vector change. Therefore, the flight control procedure can occur through the application of a set of small-size pulse solid-propellant rocket engines firing at the right time and in the demanded direction. We consider the design of pulse solid-propellant rocket engines with metal bodies, as well as a design that allows integration of engines into the monoblock compartment made of high-strength plastic using additive technologies. The substitution of the set of separate engines with metal bodies by the monoblock of integrated engines and elimination of each engine mounting elements should provide the reduction of the weight of a propulsion compartment. The comparative analysis is given, and the design features of pulse solid-propellant rocket engines with metal bodies are described along with a design that allows them to be integrated into the monoblock compartment made of high-strength plastic. The results of calculating the safety factor of the pulse solid-propellant rocket engine body in the joint compartment are presented along with comparative weight characteristics, which can be used for the assessment of the advisability of design change to monoblock one.