Date of Award:
5-2013
Document Type:
Thesis
Degree Name:
Master of Science (MS)
Department:
Mechanical and Aerospace Engineering
Committee Chair(s)
Stephen Whitmore
Committee
Stephen Whitmore
Committee
David Geller
Committee
Rees Fullmer
Abstract
Nitrous oxide (N2O), a commonly-used industrial gas, is also often used as a rocket motor oxidizer. It has been used in both hybrid rocket motors (using a solid fuel and a liquid oxidizer) and liquid rocket engines (using liquid fuel and oxidizer).
As a liquid form, nitrous oxide is highly stable, but in vapor form it can be decomposed, releasing large amounts of heat as it dissociates into nitrogen and oxygen. This project investigates using the energy from decomposing nitrous oxide to ignite a hybrid or liquid rocket. Such a system would be practical in rocket systems that already use nitrous oxide as the oxidizer.
Because nitrous oxide is so stable in liquid form, the necessary energy to begin the decomposition process is very high; without any other influences the decomposition of vapor nitrous oxide cannot occur until temperatures are above 800 C. However, a catalytic material can decrease the necessary energy for decomposition, and can begin nitrous oxide decomposition at temperatures near 400 C.
This research looks at the possibility of using a catalytic material made from ruthenium deposited on aluminum oxide to decompose nitrous oxide, and then to use the hot nitrogen and oxygen to ignite a hybrid rocket motor.
Checksum
8d45484d4d55b4bd9a5d4cf9ac2b4027
Recommended Citation
Wilson, Matthew D., "Catalytic Decomposition of Nitrous Oxide Monopropellant for Hybrid Motor Ignition" (2013). All Graduate Theses and Dissertations, Spring 1920 to Summer 2023. 1496.
https://digitalcommons.usu.edu/etd/1496
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