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Performance evaluation of existing experimental setup after reducing excessive RF noise. 2.ĜOMSOL simulations to ascertain the advantages of integrating HIIPER with a MN. Numerical studies using COMSOL to find the position of ion loss inside the experimental setup. Overall study is involved the following – 1. Numerical data from simulations is used to measure the deviation/error and estimate the accuracy of the experimental setup. New Langmuir probe measurements with reduced noise are used to gather ion densities at different positions to confirm the point of ion loss inside the setup. Excessive radio frequency (RF) noise in the experimental setup had interfered with the acquired data in prior studies. Addition of a magnetic nozzle as the third stage of HIIPER, for thrust augmentation, has been studied computationally. These shortcomings can be overcome by reducing the ion loss to the walls of different components inside the system and improving the plasma acceleration with the help of a magnetic nozzle (MN). One of the main shortcomings is the low thrust generated and hence low overall efficiency of the propulsion system.
Research in the past has established HIIPER as a successful concept for space propulsion with numerous advantages – high-density plume, compatibility with different propellants and neutral exhaust. Another feature is that IEC grids produce a stream of electrons that are used to neutralize the plasma during the exhaust stage. It combines a helicon source (used to generate high density plasma at low input power) and an inertial electrostatic confinement (IEC) chamber to extract the ions from helicon using Nickel grids. Helicon Injected Inertial Plasma Electrostatic Rocket (HIIPER) is an electric propulsion concept specifically being developed for space vehicles.
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