A thrust stand for high-power steady-state plasma thrusters

L. D. Cassady, A. D. Kodys, E. Y. Choueiri

Research output: Chapter in Book/Report/Conference proceedingConference contribution

11 Scopus citations

Abstract

The operation of an inverted-pendulum thrust stand to measure thrust for high-power steady-state plasma thrusters is presented. An extensive calibration procedure that characterizes the thrust stand response to thrust and forces induced by the interaction of current carrying conductors is discussed. Techniques are also described that reduce thrust measurement errors induced by thermal effects on the stand. Sensitivities of 3.00±0.32 mV/mN are achieved using a laser-based system to measure stand deflection. Data taken with the 30 kW Lorentz Force Accelerator with lithium vapor propellant operating at 500 A, 9.5 mg/s lithium flow rate and a 0.07 T applied field give a measured thrust of 265±48 mN and a nominal 20% thrust efficiency.

Original languageEnglish (US)
Title of host publication38th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit
PublisherAmerican Institute of Aeronautics and Astronautics Inc.
ISBN (Print)9781624101151
DOIs
StatePublished - 2002
Event38th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit 2002 - Indianapolis, IN, United States
Duration: Jul 7 2002Jul 10 2002

Publication series

Name38th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit

Other

Other38th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit 2002
CountryUnited States
CityIndianapolis, IN
Period7/7/027/10/02

All Science Journal Classification (ASJC) codes

  • Aerospace Engineering
  • Control and Systems Engineering
  • Electrical and Electronic Engineering

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