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Upper Stage Engine Composite Nozzle ExtensionsCarbon-carbon (C-C) composite nozzle extensions are of interest for use on a variety of launch vehicle upper stage engines and in-space propulsion systems. The C-C nozzle extension technology and test capabilities being developed are intended to support National Aeronautics and Space Administration (NASA) and United States Air Force (USAF) requirements, as well as broader industry needs. Recent and on-going efforts at the Marshall Space Flight Center (MSFC) are aimed at both (a) further developing the technology and databases for nozzle extensions fabricated from specific CC materials, and (b) developing and demonstrating low-cost capabilities for testing composite nozzle extensions. At present, materials development work is concentrating on developing a database for lyocell-based C-C that can be used for upper stage engine nozzle extension design, modeling, and analysis efforts. Lyocell-based C-C behaves in a manner similar to rayon-based CC, but does not have the environmental issues associated with the use of rayon. Future work will also further investigate technology and database gaps and needs for more-established polyacrylonitrile- (PAN-) based C-C's. As a low-cost means of being able to rapidly test and screen nozzle extension materials and structures, MSFC has recently established and demonstrated a test rig at MSFC's Test Stand (TS) 115 for testing subscale nozzle extensions with 3.5-inch inside diameters at the attachment plane. Test durations of up to 120 seconds have been demonstrated using oxygen/hydrogen propellants. Other propellant combinations, including the use of hydrocarbon fuels, can be used if desired. Another test capability being developed will allow the testing of larger nozzle extensions (13.5- inch inside diameters at the attachment plane) in environments more similar to those of actual oxygen/hydrogen upper stage engines. Two C-C nozzle extensions (one lyocell-based, one PAN-based) have been fabricated for testing with the larger-scale facility.
Document ID
20150016247
Acquisition Source
Marshall Space Flight Center
Document Type
Abstract
Authors
Valentine, Peter G.
(NASA Marshall Space Flight Center Huntsville, AL, United States)
Allen, Lee R.
(NASA Marshall Space Flight Center Huntsville, AL, United States)
Gradl, Paul R.
(NASA Marshall Space Flight Center Huntsville, AL, United States)
Greene, Sandra E.
(NASA Marshall Space Flight Center Huntsville, AL, United States)
Sullivan, Brian J.
(Materials Research and Design, Inc. Wayne, PA, United States)
Weller, Leslie J.
(Materials Research and Design, Inc. Wayne, PA, United States)
Koenig, John R.
(Southern Research Inst. Birmingham, AL, United States)
Cuneo, Jacques C.
(Southern Research Inst. Birmingham, AL, United States)
Thompson, James
(Carbon Carbon Advanced Technologies, Inc. Kennedale, TX, United States)
Brown, Aaron
(Carbon Carbon Advanced Technologies, Inc. Kennedale, TX, United States)
Shigley, John K.
(Orbital ATK, Inc. Brigham City, UT, United States)
Dovey, Henry N.
(Orbital ATK, Inc. Brigham City, UT, United States)
Roberts, Robert K.
(Orbital ATK, Inc. Brigham City, UT, United States)
Date Acquired
August 21, 2015
Publication Date
June 22, 2015
Subject Category
Spacecraft Propulsion And Power
Spacecraft Design, Testing And Performance
Ground Support Systems And Facilities (Space)
Report/Patent Number
M15-4521
Meeting Information
Meeting: 2015 National Space & Missile Materials Symposium (NSMMS)
Location: Chantilly, VA
Country: United States
Start Date: June 22, 2015
End Date: June 25, 2015
Sponsors: NASA Headquarters, Federal Aviation Administration, Department of Energy, National Space and Missiles Materials, Department of Defense
Distribution Limits
Public
Copyright
Public Use Permitted.
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