Alternative Fabrication Designs for Carbon-Carbon (C-C) Nozzle Extensions

Award Information
Agency: National Aeronautics and Space Administration
Branch: N/A
Contract: NNX12CF53P
Agency Tracking Number: 115467
Amount: $124,989.00
Phase: Phase I
Program: SBIR
Awards Year: 2012
Solicitation Year: 2011
Solicitation Topic Code: X2.01
Solicitation Number: N/A
Small Business Information
Materials Research and Design
PA, Wayne, PA, 19087-1858
DUNS: 966563884
HUBZone Owned: N
Woman Owned: N
Socially and Economically Disadvantaged: N
Principal Investigator
 Tiffany Boarts
 Principal Investigator
 (610) 964-9000
 tiffany.boarts@m-r-d.com
Business Contact
 Brian Sullivan
Title: Director
Phone: (610) 964-6131
Email: brian.sullivan@m-r-d.com
Research Institution
 Stub
Abstract
In order for carbon-carbon nozzle extensions and exit cones to serve as practical, low cost components for future Earth-to-Orbit propulsion systems, it is necessary to develop alternative fabrication methods coupled with proven design and analysis tools. Two-dimensional (2D) C-C components are typically less expensive and potentially lower weight than C-C parts fabricated using 3D woven preforms. One typical 2D C-C fabrication method uses a tape-wrapping technique in which a bias-ply C/Ph tape is wrapped over a mandrel, cured, carbonized, and graphitized to form a carbon-carbon part. Tape-wrapping has been applied successfully to the development of erosion-resistant carbon-carbon exit cones. An alternative fabrication technique is to replace the flat 2D lay-ups with an involute construction. The involute plies spiral from the inner to outer diameter of the carbon-carbon part providing through-thickness reinforcement to reduce the potential for delaminations. In addition, each ply extends from the forward to the aft end of the part, increasing its axial strength considerably.The overall objective of this program is to design and demonstrate an alternative fabrication technique of nozzle extensions and exit cones on Earth-to-Orbit (ETO) propulsion systems. The Phase I program will be performed by a team of MR & D and ATK Aerospace Systems. The MR & D team is uniquely suited to perform the proposed effort because of previous experience on developing alternative fabrication methods of high-temperature C-C components such as exit cones and aeroshells. MR & D will manage the program, develop the processing and operational models, and design the C-C subcomponents to be fabricated. ATK Aerospace Systems will provide guidance and information as well as fabricate the C-C subcomponents.

* information listed above is at the time of submission.

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