Statistical Analysis of Mass-Energy Parameters of Multi-stage and Clustered Liquid Propellant Engines

Increasing the orbital height and mass of the satellites' cargo, in addition to multi-staging the satellites, requires use of stronger propulsion systems. One of the commonly used methods to provide the required thrust in each stage is proper arrangement of several engines in conjunction with each other, in order to provide the amount of propulsion needed to carry out the mission. The overall purpose of this paper is to present the results of a statistical study of massive energy and system parameters of satellites and missiles in countries that use clustered or multi-compartment engines in their propulsion system. Extracting thrusts, trust weights, specific impulse, chamber pressure of these engines, and examining the type of pressurizing system, vector control system, etc. It is possible to compare the mass-energy parameters and system characteristics of propulsion systems. The results show that the C* efficiency of the liquid-gas injection system for both components of the crosene and liquid hydrogen injector is higher than that of the liquid-liquid injection systems, indicating the superiority of the propellants in comparison to refractory propellants. On the other hand, the pressure of the open-cycle engine compartment with a storable propellant is more than that of engines with cryogenic propellant.