Conceptual Design of Liquid Propellant Propulsion System based on Optimizing Combination of the Main Independent Parameters of the Engine

Optimization of complex engineering systems such as Liquid Rocket Propulsion Systems (LRPS), which are popular because of high specific impulse levels, has always been an integral part of design. A newly generic simulation and optimization engineering software of system parameters for the LRPS with gas generator cycle (turbopump-opened cycle) is developed to optimize conceptual design based on the combination of the main independent parameters of the engine such as combustion chamber pressure, combustion chamber mixture ratio, expansion ratio of turbine nozzle and etc. The objective function of this code is to maximize the specific impulse of LRPS. The developed algorithm is applied for US F-1 engine, and results are compared with the modified F-1. This software is written in the modern engineering, object-oriented Compaq visual Fortran 6.6 programming language and will execute on PC. Execution times are approximately 5 to 15 seconds.