Print Email Facebook Twitter Thermal ignition system for green rocket propulsion Title Thermal ignition system for green rocket propulsion: Experimental study on thermal ignition of high concentration hydrogen peroxide and ethanol propellant Author Tambağ, Emre (TU Delft Aerospace Engineering) Contributor Jyoti, B.V.S. (mentor) Degree granting institution Delft University of Technology Programme Aerospace Engineering Date 2022-08-23 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. Subject Thermal ignitionGreen propulsionHydrogen peroxideH2O2EthanolHTP To reference this document use: http://resolver.tudelft.nl/uuid:951c9f37-4128-4d87-b834-7872a9b57670 Coordinates 51.990243, 4.376090 Part of collection Student theses Document type master thesis Rights © 2022 Emre Tambağ Files PDF ThesisReport_EmreTambag_4973631.pdf 58.18 MB Close viewer /islandora/object/uuid:951c9f37-4128-4d87-b834-7872a9b57670/datastream/OBJ/view