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Preliminary Evaluation of a 10 KW Hall Thruster

National Aeronautics and Space Administration

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Description:A 10 kW Hall thruster was characterized over a range of discharge voltages from 300-500 V and a range of discharge currents from 15-23 A. This corresponds to power levels from a low of 4.6 kW to a high of 10.7 kW. Over this range of discharge powers, thrust varied from 278 mN to 524 mN, specific impulse ranged from 1644 to 2392 seconds, and efficiency peaked at approximately 59%. A continuous 40 hour test was also undertaken in an attempt to gain insight with regard to long term operation of the engine. For this portion of the testing the thruster was operated at a discharge voltage of 500 V and a discharge current of 20 A. Steady-state temperatures were achieved after 3-5 hrs and very little variation in performance was detected. Jankovsky, Robert S. and McLean, Chris and McVey, John Glenn Research Center NASA/TM-1999-209075, NAS 1.15:209075, AIAA Paper 99-0456, E-11636We have made it easy for you to find a PDF Ebooks without any digging. And by having access to our ebooks online or by storing it on your computer, you have convenient answers with Preliminary Evaluation of a 10 KW Hall Thruster. To get started finding Preliminary Evaluation of a 10 KW Hall Thruster, you are right to find our website which has a comprehensive collection of manuals listed.
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Pages: 34

Format: PDF, EPUB & Kindle Edition

Publisher: Createspace Independent Publishing Platform

Release: 2018

ISBN: 1721181040

Description: A 10 kW Hall thruster was characterized over a range of discharge voltages from 300-500 V and a range of discharge currents from 15-23 A. This corresponds to power levels from a low of 4.6 kW to a high of 10.7 kW. Over this range of discharge powers, thrust varied from 278 mN to 524 mN, specific impulse ranged from 1644 to 2392 seconds, and efficiency peaked at approximately 59%. A continuous 40 hour test was also undertaken in an attempt to gain insight with regard to long term operation of the engine. For this portion of the testing the thruster was operated at a discharge voltage of 500 V and a discharge current of 20 A. Steady-state temperatures were achieved after 3-5 hrs and very little variation in performance was detected. Jankovsky, Robert S. and McLean, Chris and McVey, John Glenn Research Center NASA/TM-1999-209075, NAS 1.15:209075, AIAA Paper 99-0456, E-11636We have made it easy for you to find a PDF Ebooks without any digging. And by having access to our ebooks online or by storing it on your computer, you have convenient answers with Preliminary Evaluation of a 10 KW Hall Thruster. To get started finding Preliminary Evaluation of a 10 KW Hall Thruster, you are right to find our website which has a comprehensive collection of manuals listed.
Our library is the biggest of these that have literally hundreds of thousands of different products represented.

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Preliminary Evaluation of a 10 KW Hall Thruster

Preliminary Evaluation of a 10 KW Hall Thruster

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