Cryogenic propellant tank pressurization

Hermsen, R.J.G.

Cryogenic propellant tank pressurization

Master thesis (2017)

Authors

R.J.G. Hermsen

Contributors

B.T.C. Zandbergen (mentor)

Department

Space Engineering

High-pressure Rocket engine Cryogenic Propellant DARE Rocket Tank pressurization Delft Aerospace Rocket Engineering Pressurant injector Pressure-fed

To reference this document use:

http://resolver.tudelft.nl/uuid:048e34e9-9af6-4b3c-9249-576d192fa7bd

More Info

expand_more

Published Date

29-06-2017

Reuse Rights

Other than for strictly personal use, it is not permitted to download, forward or distribute the text or part of it, without the consent of the author(s) and/or copyright holder(s), unless the work is under an open content license such as Creative Commons.

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.

Files

Rob Hermsen - Cryogenic propel... (pdf)

(pdf | 8.64 Mb)

License info not available