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A comparison of potential electric propulsion systems for orbit transferElectric propulsion concepts are compared on the basis of trip time for the low earth orbit (LEO) to geosynchronous earth orbit (GEO) mission. Resistojet, arcjet, magnetoplasmadynamic (MPD), pulsed inductive, and ion engine thruster concepts are included. The optimum (minimum trip time) value of specific impulse is found to be dependent upon the specific mission and system being considered. As expected, the devices which can deliver good efficiency at low specific impulses promise the fastest trip times. The solution for trip time and propellant mass for the constant power, continuous low acceleration orbit transfer problem (one way and round trip) is presented in nomograph form. The influences of mission Delta V, thruster efficiency, specific impulse, power, power and propulsion system mass, and payload mass are clearly illustrated.
Document ID
19830033157
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Jones, R. M.
(California Institute of Technology, Jet Propulsion Laboratory, Electric Power Systems Section, Pasadena CA, United States)
Date Acquired
August 11, 2013
Publication Date
November 1, 1982
Subject Category
Astrodynamics
Report/Patent Number
AIAA PAPER 82-1871
Meeting Information
Meeting: Japan Society for Aeronautical and Space Sciences, and DGLR, International Electric Propulsion Conference
Location: New Orleans, LA
Start Date: November 17, 1982
End Date: November 19, 1982
Sponsors: AIAA
Accession Number
83A14375
Distribution Limits
Public
Copyright
Other

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