РАЗРАБОТКА ТЕХНОЛОГИИ ПРОЕКТИРОВАНИЯ ОПТИМАЛЬНЫХ КОЛЬЦЕВЫХ СОПЕЛ ВЫСОКОЭФФЕКТИВНЫХ РАКЕТНЫХ ДВИГАТЕЛЕЙ В СОСТАВЕ РАКЕТЫ-НОСИТЕЛЯ

Abstract

The technology of designing optimal annular nozzles of high-performance
rocket propulsion is considered. Decomposition of system “launcher – rocket
propulsion – nozzle of rocket propulsion” is realized of systems approach. Subsystems
in considered system are studied, the special attention given for subsystem
“nozzle of rocket propulsion”. Stated principles are applied for development
technology of designing optimal by energy-propulsion characteristics annular
nozzles taking into account feature of flow, typical for annular nozzles. The system
of mathematical modeling, realized the technology of designing annular nozzles
of high-performance rocket propulsion in structure of launcher is introduce.