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Mass driver reaction engine characteristics and performance in earth orbital transfer missionsConfigurations of a typical mass driver reaction engine (MDRE) are presented and its use for delivery of payloads to geosynchronous orbit (GEO) from low earth orbit (LEO) is discussed. Basic rocket equations are developed for LEO to GEO round-trip missions using a single exhaust velocity. It is shown that exhaust velocities in the 5-10 km/sec range (specific impulse of 500-1000 sec) are well suited for mass drivers, minimizing the overall cost of missions. Payload delivery rate fractions show that there is little to be gained by stretching out LEO to GEO transfer times from 90 to 180 days. It therefore pays to use the shorter trip time, approximately doubling the amount of delivered payload during any fixed time of use of the MDRE.
Document ID
19820034664
Acquisition Source
Legacy CDMS
Document Type
Reprint (Version printed in journal)
Authors
Snow, W. R.
(Princeton Univ. NJ, United States)
Dunbar, R. S.
(Princeton University Princeton, NJ, United States)
Date Acquired
August 10, 2013
Publication Date
January 1, 1982
Subject Category
Spacecraft Propulsion And Power
Accession Number
82A18199
Funding Number(s)
CONTRACT_GRANT: NSG-3176
Distribution Limits
Public
Copyright
Other

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