Development of a Throttleable 6 kN H 2 O 2 /Butyl Alcohol Rocket Engine

The increasing demand for versatile and sustainable propulsion systems has intensified research into green propellants and advanced thrust modulation technologies. This study presents the development and testing of a throttleable rocket engine utilizing 98% hydrogen peroxide by mass as the oxidizer and butyl alcohol (as isomers n-butanol) as the fuel. Combining the environmental benefits of green propellants with variable thrust capabilities, the system addresses the challenges of modern space missions. Butyl alcohol was selected for its low toxicity, safety, storability, and favorable combustion performance, making it a strong candidate for future applications. The engine was designed to deliver a nominal thrust of 6 kN with the capability to throttle down to 1.2 kN. Experiments investigated the effects of pintle injector positions, supply pressures, and combustion chamber parameters on performance. Results demonstrated stable and efficient combustion across a wide operating range, highlighting the critical role of injector design and chamber geometry in ensuring consistent thrust and combustion efficiency. This research validates the potential of hydrogen peroxide and butyl alcohol as a sustainable propellant pair, particularly for planetary landers requiring precise thrust modulation for controlled descent. It marks a significant step in advancing sustainable propulsion technologies, contributing to the future of planetary exploration and interplanetary mission capabilities.

Abstract licence: CC BY

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