Cryogenic propellant tank pressurization
Master Thesis
(2017)
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Copyright
© 2017 Hermsen, R.J.G.
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Publication Year
2017
Copyright
© 2017 Hermsen, R.J.G.
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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.