Keywords and Phrases
Aerospike; CFD; CubeSats; Nozzle; Plug; Satellites
"The cold-gas propulsion system being developed by M-SAT requires improvements to its original nozzle design. This study documents the research, design, and analysis of a supersonic plug nozzle concept that could be integrated to the refrigerant-based cold-gas propulsion system to possibly improve its performance. As documented in this thesis, CFD analysis showed that the outlined nozzle design method resulted in a feasible nozzle concept that has the ability to out-perform a conventional nozzle of the same area ratio. The flow-fields and thrust of the aerospike nozzle, for the full and truncated nozzles, were investigated. The purpose of this study is to investigate other rocket nozzles that might have the ability to improve performance of a propulsion system without a large penalty on vehicle mass or cost. Based on the information presented in this thesis, university-based satellite teams can manipulate the inputs of the design and analysis methods to investigate the use of an aerospike nozzle design concept to meet their design goals"--Abstract, page iii.
Riggins, David W.
Rovey, Joshua L.
Mechanical and Aerospace Engineering
M.S. in Mechanical Engineering
Missouri University of Science and Technology
xi, 134 pages
© Abdalla Ali Bani
Thesis - Open Access
Library of Congress Subject Headings
Propellants -- Design -- Analysis
Artificial satellites -- Propulsion systems
Electronic OCLC #
Bani, Abdalla Ali, "Design and analysis of an axisymmetric aerospike supersonic micro-nozzle for a refrigerant-based cold-gas propulsion system for small satellites" (2016). Masters Theses. 7591.