Development of a new algorithm for optimization of closed-loop liquid rocket engines
Last modified: 2010-04-15
Abstract
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 as objective function) of LPRS and managed to select optimum regime.
Finally, it must be finalized selection of optimum regime or optimum parameters. The developed algorithm has applied for RD-253 engine, and results have compared with the modified RD-253. According to the developed algorithm, a software is written in the modern engineering, object-oriented Compaq visual Fortran 6.6 programming language. Execution times are approximately 5 to 10 seconds.