Development of A Tool For Conceptual Design of Closed-loop Liquid Propellant Propulsion Systems

The reduction of Liquid Rocket Propulsion System (LRPS) conceptual design costs in conjunction with an increase in engine’s performance caused to develop a noticeable engineering software to simulate and optimize LRPS with staged combustion cycle and oxidizer rich pre-burner. An enabling static mathematical modeling core feature of this tool has the ability to rapidly produce closed solutions for engine power balance and engine independent parameters (combustion chamber pressure, combustion chamber mixture ratio, expansion ratio of turbine nozzle and etc.)with respect to maximize performance (specific impulse) of LPRS and managed to select optimum regime .The developed algorithm is applied to RD-253 engine, and the results are compared with the modified RD-253. This software is written in the modern engineering, object-oriented Compaq Visual FORTRAN 6.6 programming language.

کلیدواژه ها:

closed-Loop liquid propellant propulsion system ، specific impulse ، oxidizer rich pre-burner