Thermal ignition system for green rocket propulsion

Experimental study on thermal ignition of high concentration hydrogen peroxide and ethanol propellant

Master thesis (2022)

Authors

E. Tambağ Aerospace Engineering

Contributors

B.V.S. Jyoti Space Systems Egineering (mentor)
Faculty
Aerospace Engineering, Aerospace Engineering
Copyright: © 2022 Emre Tambağ
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Published Date

23-08-2022

Language

English

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Faculty

Aerospace Engineering

Abstract

With hydrazine on the list of "substances of very high concern" by the European Chemicals Agency; hence alternative (storable) liquid rocket propellants are being developed which are less hazardous. During this feasibility study, experiments have been performed with a thermal ignition system in combination with hydrogen peroxide and ethanol as green propellants to achieve ignition followed by self-sustained combustion at the lowest possible power consumption. The experiments have been followed up by a computer model that has been simulated in COMSOL.