Reduction of the Pressurization System Final Mass for a Modern Rocket Launcher

The work focuses on optimizing the pressurization system’s operating performance for a fuel tank of turbo-pumped liquid propellant rocket engine. This system is most complex and expensive in medium-size launch vehicle, after A new patented methodology reducing final mass stage proposed, studied, validated. application proposed method efficient at end engine operation sequence during throttling regime. calculation helium excess high-pressure cylinders uses model real gas. It also involves empirical relations describing nonstationary heat transfer system. As an innovative technical solution, authors propose to estimate gas discharge from tanks engine’s last throttling. practical research allows saving tenths kilograms payload with implementation simple modification launcher control program. results demonstrated effectiveness example RD-171