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Advanced space engine component technology statusKey to the achievement of maximum benefit from the Space Tug transportation system is the availability of a low-cost, high-performance engine system. To define this engine system, studies have been conducted under Air Force and NASA direction, and pertinent hardware technology programs have been initiated. From among the several candidate systems studied, the cryogenic, staged-combustion cycle, high chamber pressure system in conjunction with a large-area-ratio nozzle was selected for component and subsystem demonstration. Main turbopump, high-area-ratio thrust chamber, preburner, and igniter components are being evaluated. A brief description of the engine capabilities, the main liquid hydrogen and liquid oxygen turbopump/preburner, and the main thrust chamber programs are presented; designs and progress in fabrication are shown and test results discussed.
Document ID
19760029896
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Zachary, A. T.
(Rockwell International Corp. Rocketdyne Div., Canoga Park, Calif., United States)
Date Acquired
August 8, 2013
Publication Date
August 1, 1975
Subject Category
Spacecraft Propulsion And Power
Report/Patent Number
AAS PAPER 75-156
Meeting Information
Meeting: Meeting on Space Shuttle Missions of the 80''s
Location: Denver, CO
Start Date: August 26, 1975
End Date: August 28, 1975
Sponsors: AAS, AIAA, IEEE, ORSA, and IMS,
Accession Number
76A12862
Funding Number(s)
CONTRACT_GRANT: NAS3-17800
CONTRACT_GRANT: NAS3-17794
CONTRACT_GRANT: NAS3-17825
Distribution Limits
Public
Copyright
Other

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