![]() An analysis of the flow of propellant through the thruster was completed, utilizing low Mach number flow theory. A survey of past helicon experiment parameters was completed, made possible largely due to the wealth of data provided by helicon plasma use in academia and for research and development. This thesis will focus on the author's specific contributions to this larger effort, which included the following elements. A design process was undertaken for the creation of this experimental setup, with the aid of a number of students and researchers at the MIT SPL. This effort may lead to the development of a new electric propulsion device, the Mini-Helicon Plasma Thruster. The goal was to create a robust and flexible experimental system which would allow optimization of the source and system parameters for efficient thrust generation, and would permit for correlation between helicon theory and experiment. Historical helicon experiment data have been applied to help size the experiment. ![]() ![]() This experiment allows study of the intrinsic advantages of efficient helicon plasma production for use in space electric propulsion. A helicon plasma source experiment has been developed and then constructed in the MIT Space Propulsion Laboratory (SPL) vacuum chamber. ![]()
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