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Proceedings of the 25th National and 3rd International ISHMT-ASTFE Heat and Mass Transfer Conference (IHMTC-2019)

ISBN Druckformat: 978-1-56700-497-7 (Flash Drive)
ISBN Online: 978-1-56700-496-0

SIMULATION OF HELICON DISCHARGES

DOI: 10.1615/IHMTC-2019.110
pages 62-67

Savit Anantaram
Department of Aerospace Engineering, Indian Institute of Space Science and Technology

Surabhi Shivhare
Department of Aerospace Engineering, Indian Institute of Space Science and Technology

Abstrakt

The Variable Specific Impulse Magnetoplasma Rocket (VASIMR) is an electromagnetic thruster under development for possible use in spacecraft propulsion. The first stage of this engine namely the Helicon Stage was simulated using Particle in Cell Methodology in VSIM software. The antenna field in the absence of the plasma medium was simulated to verify the production of spatially rotating electric field pattern. The plasma was simulated in the presence of an external magnetic field and a helicon antenna for both collisionless and collisional plasmas. The presence of both Helicon waves and Trivelpiece-Gould waves were verified in the excited plasma. Radial power deposition curves at various axial positions were plotted for both models: collisionless as well as plasma with collisions. Power deposition was confirmed to be zero at the center for collisionless plasma. Peak power deposition at a particular radius was verified in the case of collisional plasma. Verification of helicon plasma production for argon gas with experimental Ar+ light intensity was performed, and suggested that at low magnetic fields helicon waves are evanescent and TG waves are dominant.