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Propellant management for low thrust chemical propulsion systemsLow-thrust chemical propulsion systems (LTPS) will be required for orbital transfer of large space systems (LSS). The work reported in this paper was conducted to determine the propellant requirements, preferred propellant management technique, and propulsion system sizes for the LTPS. Propellants were liquid oxygen (LO2) combined with liquid hydrogen (LH2), liquid methane or kerosene. Thrust levels of 100, 500, and 1000 lbf were combined with 1, 4, and 8 perigee burns for transfer from low earth orbit to geosynchronous earth orbit. This matrix of systems was evaluated with a multilayer insulation (MLI) or a spray-on-foam insulation. Vehicle sizing results indicate that a toroidal tank configuration is needed for the LO2/LH2 system. Multiple perigee burns and MLI allow far superior LSS payload capability. Propellant settling, combined with a single screen device, was found to be the lightest and least complex propellant management technique.
Document ID
19810057794
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Hamlyn, K. M.
(Martin Marietta Aerospace Denver, CO, United States)
Dergance, R. H.
(Martin Marietta Aerospace Denver, CO, United States)
Aydelott, J. C.
(NASA Lewis Research Center Cleveland, OH, United States)
Date Acquired
August 11, 2013
Publication Date
July 1, 1981
Subject Category
Spacecraft Propulsion And Power
Report/Patent Number
AIAA PAPER 81-1453
Meeting Information
Meeting: Joint Propulsion Conference
Location: Colorado Springs, CO
Country: US
Start Date: July 27, 1981
End Date: July 29, 1981
Sponsors: ASME, SAE, AIAA
Accession Number
81A42198
Distribution Limits
Public
Copyright
Other

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