Design of Cryogenic Propulsion Feeding System for Second Stage of Special Rocket Based on Space Standards

In general, according to the Russian Gost standard, the space propulsion engine system includes injection subsystems, a thrust chamber, a heat transfers and cooling system, a launch system, a feeding system, a thrust vector control system, and fuel and oxidizer tanks, which due to overlap and penetration The manifolds between the engine reservoirs and the fuel system are usually designed as a pair. In the conducted investigations, in addition to knowing the elements of the circuit and how to arrange the circuit, it also leads to knowing the requirements, goals, and main requirements of the system design. Then, based on the studies, the circuit design of the feeding system and the selection of its elements have been done. By using simple fluid relations, the pressure drop of each of these elements is calculated and extracted by establishing the pressure energy balance of the reservoirs. After that, taking into account the remaining mass of pressurized gas in the tanks, the total required mass of pressurized gas has been calculated. Considering the cryogenic (super-cold) propellants in this project, considerations for the design of routes and tanks will be more important, and finally, after presenting pressure changes in both fuel and oxidizer routes, piping and instrumentation diagrams have been discussed. One of the main goals of this research is to design based on standards to achieve high reliability. In this article, the types of feeding systems, ahead problems, and challenges are discussed. Finally, the two-dimensional model of this subsystem will be presented based on the country's TRL level.