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Title:Computational and experimental analysis of HIIPER MPD propulsion system
Author(s):Puri, Rohan
Advisor(s):Miley, George H.
Department / Program:Aerospace Engineering
Discipline:Aerospace Engineering
Degree Granting Institution:University of Illinois at Urbana-Champaign
Subject(s):Space Propulsion
Electric Propulsion
Helicon Thruster
Abstract:Helicon Injected Inertial Plasma Electrostatic Rocket (HIIPER) is a deep space electric propulsion system developed on the principles of inertial electrostatic confinement (IEC) fusion and helicon plasma injection. It is a stepping stone towards a variable impulse pulsed fusion rocket. HIIPER involves a three-stage mechanism for propulsion – high-density ion generation in a helicon tube, extraction of these ions inside the fusion chamber using IEC cathode grids and finally expelling the plasma out of the system through a magnetic nozzle (MN). Currently, the first two stages are being studied experimentally and the third stage is in the design phase. Prior research has established HIIPER as an innovative concept for space propulsion with numerous advantages, some of them as follows – compatible with many propellants, high-density plasma plume and electrically neutral exhaust. The shortcomings of HIIPER, low thrust values recorded in the past, are a result of ion-wall collisions inside the helicon-IEC coupling. A possible solution to the low thrust problem is investigated for this thesis and future experiments will involve using it to rectify the issue and revaluating the performance of HIIPER. This study also involves validation of a numerical model of HIIPER using experimental results and computationally proving the advantages of a MN integrated with HIIPER. The model was then used to extrapolate the performance trends to optimize HIIPER and lay the foundation for future experimental work.
Issue Date:2021-04-28
Rights Information:Copyright 2021 Rohan Puri
Date Available in IDEALS:2021-09-17
Date Deposited:2021-05

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