Print Email Facebook Twitter Cryogenic propellant tank pressurization Title Cryogenic propellant tank pressurization Author Hermsen, R.J.G. Contributor Zandbergen, B.T.C. (mentor) Faculty Aerospace Engineering Department Space Engineering Date 2017-06-29 Abstract To launch a rocket to the edge of space using a pressure fed rocket system with liquid oxygen as propellant, you need to know exactly how much pressurant gas (helium) you need to take along. In this thesis a practical investigation on cryogenic tank pressurization is conducted together with DARE. The measurement results are used to validate numerical simulations that model the tank pressurization system. Subject cryogenichigh-pressurepropellanttank pressurizationrocketDelft Aerospace Rocket EngineeringDAREpressurant injectorpressure-fedrocket engine To reference this document use: http://resolver.tudelft.nl/uuid:048e34e9-9af6-4b3c-9249-576d192fa7bd Part of collection Student theses Document type master thesis Rights (c) 2017 Hermsen, R.J.G. Files PDF Rob Hermsen - Cryogenic p ... n V1.1.pdf 8.64 MB Close viewer /islandora/object/uuid:048e34e9-9af6-4b3c-9249-576d192fa7bd/datastream/OBJ/view