Design, Fabrication, Testing and Modeling of a Vaporizing Liquid Micro-Propulsion System

Conference paper (2016)

Authors

A. Cervone Space Systems Egineering
B.T.C. Zandbergen Space Systems Egineering
H.W. van Zeijl EKL Processing - EEMCS
Research Group
Space Systems Egineering
Copyright: © 2016 T. van Wees, C.A.J. Hanselaar, E Jansen, A. Cervone, B.T.C. Zandbergen, H.W. van Zeijl
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Published Date

2016

Language

English

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Research Group

Space Systems Egineering

Abstract

In the last decade, CubeSat development has shown the potential to allow for low-risk, low-cost space missions. To further improve the capabilities of CubeSats in large scale missions, a novel micro-propulsion system is being developed at Delft University of Technology. The system is based on a Vaporizing Liquid Microthruster (VLM), which is manufactured by means of Micro Electro-Mechanical Systems (MEMS) technology. It aims to achieve a specific impulse of 100 s and thrust of 1.4 mN, using water as propellant. This paper presents a status update of the development project. Design solutions are shown to circumvent manufacturing tolerances in the wafer-bonding and sealing of the interfaces of the VLM. Secondly, performance analysis based on a 1D-flow approximation is shown to provide a useful tool to quickly predict VLM performance. Next, a detailed design of the propellant storage tank for the CubeSat micro-propulsion system is presented. Finally, the test plan and test setup for the VLM are elaborated, presenting solutions to determine chamber temperature and pressure without directly sensing it.