Empirical Determination of Performance Characteristics for Busek 1cm Micro Radio-Frequency Ion Propulsion System

Date of Award

3-2016

Document Type

Thesis

Degree Name

Master of Science in Astronautical Engineering

Department

Department of Aeronautics and Astronautics

First Advisor

Carl R. Hartsfield, PhD

Abstract

Performance characterization for the Busek 1 cm micro radio-frequency ion engine was experimentally accomplished across its full regime of operating conditions. The thrust was determined at the nominal operating condition using a known relationship for ion engines between beam current, screen voltage, and the mass of the propellant used. Specific impulse was found at the nominal operating condition by its relation to the thrust and mass flow rate. The divergence angle of the plume of the ion engine was calculated using readings from a Faraday probe. The probe collected current density data at various angles in front of the ion engine, and with integration, the divergence angle was found. The thrust and specific impulse of the ion engine varied linearly with the total power input, or the radio-frequency power plus the beam current times the screen voltage. This trait is very important for throttle ability purposes, a useful capability for a thruster. The divergence angle of the 1 cm ion engine was calculated to be 19.3 degrees, a parameter that is ideally minimized to reduce cosine losses. Preliminary testing of this micro ion engine indicates that thrusters of this size may have potential in future CubeSat missions.

AFIT Designator

AFIT-ENY-MS-16-M-231

DTIC Accession Number

AD1054188

Comments

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