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Atomic hydrogen rocket engineA rocket using atomic hydrogen propellant is discussed. An essential feature of the proposed engine is that the atomic hydrogen fuel is used as it is produced, thus eliminating the necessity of storage. The atomic hydrogen flows into a combustion chamber and recombines, producing high velocity molecular hydrogen which flows out an exhaust port. Standard thermodynamics, kinetic theory and wall recombination cross-sections are used to predict a thrust of approximately 1.4 N for a RF hydrogen flow rate of 4 x 10 to the 22nd/sec. Specific impulses are nominally from 1000 to 2000 sec. It is predicted that thrusts on the order of one Newton and specific impulses of up to 2200 sec are attainable with nominal RF discharge fluxes on the order of 10 to the 22nd atoms/sec; further refinements will probably not alter these predictions by more than a factor of two.
Document ID
19810045130
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Etters, R. D.
(Colorado State Univ. Fort Collins, CO, United States)
Flurchick, K.
(Colorado State University Fort Collins, Colo., United States)
Date Acquired
August 11, 2013
Publication Date
April 1, 1981
Subject Category
Spacecraft Propulsion And Power
Report/Patent Number
AIAA PAPER 81-0677
Meeting Information
Meeting: International Electric Propulsion Conference
Location: Las Vegas, NV
Country: US
Start Date: April 21, 1981
End Date: April 23, 1981
Sponsors: AIAA, Japan Society for Aeronautical and Space Sciences, DGLR
Accession Number
81A29534
Funding Number(s)
CONTRACT_GRANT: NAG3-34
Distribution Limits
Public
Copyright
Other

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