Design, Fabrication and Characterization of MEMS Micro-resistojet Thrusters

Small satellites require efficient propulsion systems for attitude and orbit control. This thesis focuses on the development and characterization of two distinct types of micro-resistojet thrusters, namely Vaporizing Liquid Micro-resistojet (VLM) and Low Pressure Micro-resistojet (LPM). Both concepts are developed at TU Delft and are designed to...

Feasibility study of additive manufacturing techniques applicable to resistojet propulsion systems

The use of additive manufacturing (AM) can potentially offer significant benefits to the design and performance of resistojet components but has so far only seen limited research in this application. The goal of this study was to investigate the possibility of 3D printing a functional resistojet heating chamber and the potential benefits that...

Vaporizing Liquid Micro-resistojet experimentation

The Delfi program at the Delft University of Technology aims to develop nano satellites between 1 and 10 kg to provide high level education and to develop a platform for novel space technologies. Miniaturized satellites require miniaturized propulsion systems to provide orbital adjustments for functions like station keeping, extending mission...

On the Design of a Propulsion System for the Lunar Meteoroid Impact Observer (LUMIO)

LUMIO is a 12U CubeSat destined for a halo orbit around the Earth-Moon L2 point, requiring 203 m/s of delta V for orbital transfer, station-keeping and disposal manoeuvres, to be delivered by its Main Propulsion System (MPS). A total impulse of 170 N-s is required to be delivered by its Reaction Control System (RCS) for de-tumbling and reaction...

Response Surface Based Design Optimization of a Low-Pressure Microresistojet's Heat Exchanger

A Low-Pressure Micro-resistojet (LPM) is a type of in-space electrothermal propulsion system for satellites that works by heating low-pressure (50 to 300 Pa) fluid flowing through microchannels/slots (typically <1 mm diameter) using resistive heating elements like thin-film Molybdenum. This thesis delineates a response surface based method to...

Micronozzle Performance: A Numerical and Experimental Study

Micropropulsion is universally considered to be a key technology enabling nano- and pico- satellites to perform more complex missions. However, past research has shown that nozzle efficiencies at the microscale are far inferior to their macro scale counterparts. These low efficiencies can be attributed to the relatively high viscous losses...

Performance of the MEMS Vaporizing Liquid Microthruster using cold nitrogen gas as propellant: An experimental study

This thesis includes an experimental study about the performance of a third generation MEMS-VLM chip. The influence of the throat Reynolds number on the discharge factor and the nozzle quality was investigated. This was done by measuring the mass flow and thrust force for a chamber pressure range of 2-5 [bar] using nitrogen gas as propellant. It...