The electric pump cycle is a kind of propellant supply method for a bipropellant liquid rocket engine. The electric pump cycle has advantages in that the system configuration is simple and the combustion chamber pressure is easy to increase. Although research on electric pump cycles is actively conducted around the world, there are few cases where the whole supply system has been experimentally studied. In this thesis, test equipment that simulates the propellant supply system of an electric pump cycle was constructed, and water flow tests were performed to verify the design program for an electric pump cycle. The injector and combustion chamber were simulated as separate needle valves that make differential pressure for each component.
As a result of conducting experiments for verifying the design program, the error was generally within 1% at a mass flow rate of 0.117 kg/s, which is near the target oxidizer flow rate of 0.127 kg/s. Through this, it can be seen that the configuration of the design program and the verification process through experiments were effectively performed.
Also, the number of needle valve turns that make the target volume flow rate and the injector and combustion chamber differential pressure were calculated by drawing a certain curve according to the volume flow rate change in the sum of the differential pressures by two needle valves simulating the injector and the combustion chamber. By verifying this through an experiment, it was shown that it is possible to simulate the differential pressure of components using a needle valve.
Measurement uncertainty evaluation was performed, and the reliability of the experimental results was secured by showing an average of 0.85% expanded uncertainty at the 95% confidence level.