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Thrust vector control by liquid injection for solid propellant rocketsIn liquid injection thrust vector control, a rocket jet is deflected for steering purposed by injecting a liquid into the nozzle exit cone. The liquid is preferably both dense and reactive so that it adds mass and energy and generates shocks in the supersonic exhaust. This behavior increases thrust in the affected part of the jet producing not only a side force for steering but an addition to axial thrust. This paper presents a summary of current liquid injection thrust vector control technology, including procedures for design, development, analysis, testing and evaluation, together with supporting data and references.
Document ID
19750061568
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Zeamer, R. J.
(Hercules, Inc. Magna, Utah, United States)
Date Acquired
August 8, 2013
Publication Date
September 1, 1975
Subject Category
Spacecraft Propulsion And Power
Report/Patent Number
AIAA PAPER 75-1225
Accession Number
75A45640
Funding Number(s)
CONTRACT_GRANT: NAS3-13322
Distribution Limits
Public
Copyright
Other

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