Experimental Investigation of Throttleable H2O2 and Polypropylene Hybrid Rocket Motor

Abstract

This study experimentally investigated the propulsion performance of a swirling-type throttleable hybrid rocket motor using hydrogen peroxide and polypropylene. An in-house throttle valve consisted of a servomotor, and an industrial ball valve was integrated to instantaneously control the oxidizer mass flow rate. Several ground static hot-fire tests with fixed oxidizer mass flow rates of [Formula: see text] (100%) and [Formula: see text] (82%) and many step-varying oxidizer mass flow rates were performed to examine its propulsion performance. The hybrid rocket motor achieved an impressive sea-level [Formula: see text] of 240 s, an engine [Formula: see text] efficiency of more than 97%, and a thrust uncertainty of less than 5% when the oxidizer flow rate was fixed as [Formula: see text]. For the multiple-step hot-fire test results, the thrusts and chamber pressures were both found nearly proportional to the oxidizer mass flow rates with different proportionalities. The overall [Formula: see text] ratio of the tests is 5.61, which is hardly shifted, unlike most hybrid rocket data reported previously. In summary, the total impulse and thrust are both linear to total oxidizer mass consumption in the range of 50–100% of [Formula: see text]. This major finding would indeed broaden the application of hybrid rocket motors to future space technology.