Turbopompa sisteminin RPM düzenlemesi için kullanılacak oransal tahliye vanasının modellenmesi ve testi

Launch vehicles use pump-fed pressurization systems, and the energy to drive the pump can be obtained in various ways. Small rockets may use electric motors, but larger liquid rocket engines often use gas generator cycles, where the turbine is driven by pre-combustion chamber products. In this study, a novel PID controller system has been proposed in which the hot gas resulting from the combustion of a hybrid rocket motor or cold gas resulting from pressurized tank is regulated before entering the turbine, similar to the turbochargers in cars. Due to the characteristics of the hybrid rocket used in the hot gas generator, the energy produced decreases over time, and therefore the system produces more energy during operation than the turbopump system requires. The required amount of the produced gas is directed to the turbopump system and the rest is exhausted using a proportional wastegate. The excess energy produced ensures that RPM stays constant during pressure fluctuations in the combustion chamber. The proposed system employs a closed-loop control strategy, where feedback from the turbine speed is measured with a distance sensor and this feedback is used to adjust the wastegate position and maintain the desired RPM. In this study, modeling and characterization of the proportional wastegate were conducted, and a turbine speed sensor was developed using a proximity sensor. System was modeled in MATLAB Simulink, and control algorithm was developed. Then, tests were conducted with both hot and cold gas generators to validate the system's performance. Both simulation and test results demonstrate that the proposed control system can effectively regulates the turbopump speed within a desired range, even under disturbances.