Cryogenic propellant tank pressurization

Master thesis (2017)

Authors

Contributors

Department
Space Engineering (Aerospace Engineering) (TU Delft)
Copyright: © 2017 Hermsen, R.J.G.
High-pressure Rocket engine Cryogenic Propellant DARE Rocket Tank pressurization Delft Aerospace Rocket Engineering Pressurant injector Pressure-fed
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Published Date

29-06-2017

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Faculty

Aerospace Engineering

Department

Space Engineering

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.