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Introduction: The challenge of optimum integration of propulsion systems and large space structuresA functional matrix of possible propulsion system characteristics for a spacecraft for deployable and assembled spacecraft structures shows that either electric propulsion or low thrust chemical propulsion systems could provide the propulsion required. The trade-off considerations of a single propulsion engine or multiengines are outlined and it is shown that a single point engine is bounded by some upper limit of thrust for assembled spacecraft. The matrix also shows several additional functions that can be provided to the spacecraft if a propulsion system is an integral part of the spacecraft. A review of all of the functions that can be provided for a spacecraft by an integral propulsion system may result in the inclusion of the propulsion for several functions even if no single function were mandatory. Propulsion interface issues for each combination of engines are identified.
Document ID
19800022944
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Carlisle, R. F. (NASA Headquarters Washington, DC United States)
Date Acquired
August 10, 2013
Publication Date
July 1, 1980
Publication Information
Publication: NASA. Lewis Research Center Large Space Systems(Low-Thrust Propulsion Technol.
Subject Category
Spacecraft Propulsion And Power
Accession Number
80N31450
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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IDRelationTitle19800022943Collected WorksLarge Space Systems/Low-Thrust Propulsion Technology
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