Standardization of Hall Thruster Efficiency Analysis: Methodology and Historical Perspective
Abstract
The rocket power efficiency equation was analytically decomposed to explicitly account for the effects of energy conversion losses, plume divergence, and the velocity distribution function of the propellant jet. In this approach, thruster efficiency is the product of (1) energy efficiency and (2) propellant utilization efficiency. Energy efficiency is expressed as the product of voltage utilization efficiency and current utilization efficiency, and incorporates losses from Joule heating, radiation, and ionization processes. Energy efficiency contains no information about the vector properties of the jet. Propellant utilization efficiency incorporates losses from plume divergence and ion jet composition, and is unity for 100% ionization to a single ion species whose velocity vectors are directed along the thrust axis. The efficiency architecture is derived from first principles and is applicable to all propulsion employing electrostatic acceleration, including Hall thrusters and ion engines. The analysis is compared to past methodologies and is illustrated with thrust and far-field plume measurements of a laboratory Hall thruster.
Document Details
- Document Type
- Technical Report
- Publication Date
- Feb 25, 2008
- Accession Number
- ADA489529
Entities
People
- Alec D. Gallimore
- Carl William Larson
- Daniel L. Brown
- William A. Hargus
Organizations
- Air Force Research Laboratory