The problem of selecting the design parameters of a small space tug propulsion system, which is one of the key tasks in shaping the vehicle configuration since it significantly affects the spacecraft layout, is considered. A methodology for solving the complex problem of forming the architecture and selecting the parameters of the pneumatic system of a propulsion system using gaseous oxygen-methane propellants is developed. The methodology, based on digital 1D modeling technology, is implemented in the Russian software package MDS (Modeling of Dynamic Systems). As a result of applying the methodology, a rational architecture of the pneumatic system was selected, making it possible to avoid thermal stabilization of the gaseous components by using adiabatic compression of the working fluids. The possibility of parametric tuning of the system to ensure the most rational temperature regime is demonstrated. Schemes of the fuel and oxidizer subsystems are presented. The solutions found are planned to be used in the creation of the small space tug “BOT”. 

EDN  ENWDSM