The design and testing of an injector for anadvanced hypergolic dual-mode propulsionsystem

Master thesis (2021)

Authors

T. Borsboom Aerospace Engineering

Contributors

B.V.S. Jyoti Space Systems Egineering (mentor)
R. Noomen Astrodynamics & Space Missions - Aerospace Engineering (graduation committee member)
E.K.A. Gill Space Engineering (graduation committee member)
Faculty
Aerospace Engineering, Aerospace Engineering
Copyright: © 2021 Tommy Borsboom
More Info
expand_more

Published Date

28-04-2021

Language

English

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

Abstract

An important topic in the field of rocket propulsion is the development of a new green advanced hypergolic rocket propulsion system. The current hypergolic propellants have one large drawback, namely the toxic properties. The injector has a crucial role in the performance of a liquid engine. Therefore, the next step in the development of this novel propulsion system is the development of the injector. The purpose of this master thesis is to design, manufacture, and test this novel injector. The injector is designed to operate in monopropellant and bi-propellant modes, which is supported by the new green hypergolic propellants. In total, four different configurations of the injector are developed. Different testing objectives are defined for the experiments to test all the injector configurations. These testing objectives are atomization behavior, atomization performance, the mixing process in bi-propellant mode operation, and atomized flow in combination with the heating element.

Files

THESIS_report_Tommy_Borsboom_4... (pdf)
(pdf | 21.7 Mb)
- Embargo expired in 18-05-2022
Unknown license