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.
More »The Phase I program will lead to improved C-C nozzle extension components for ETO propulsion systems via alternate fabrication methods coupled with proven design and analysis tools. The models developed here will allow various material candidates and involute configurations to be auditioned prior to fabrication and testing, reducing the cost of developing these higher-performance materials considerably. The technology developed here will also have a direct impact on the design and manufacturing of alternative C-C fabrication methods, and metal-to-composite nozzle joints for all future propulsion system designs by offering a domestically available alternative to the non-domestic state-of-the-art, such as the nozzle extension designed for RL 10B-2. Benefits include increased performance, and weight and cost savings, together with a larger supplier base for the fabrication of refractory composite nozzles and nozzle extensions for future heavy-lift launch propulsion systems.
MR&D's core business is to provide design services to the aerospace materials community, so the methods developed here can be used to support other SBIR awardees, or transferred to other propulsion system designers. MR&D is involved in the development of C-C materials on several programs which will serve to establish standardized methods for the design and analysis of propulsion materials and structures for years to come.
Organizations Performing Work | Role | Type | Location |
---|---|---|---|
Materials Research and Design, Inc. | Lead Organization | Industry | Wayne, Pennsylvania |
Marshall Space Flight Center (MSFC) | Supporting Organization | NASA Center | Huntsville, Alabama |
This is a historic project that was completed before the creation of TechPort on October 1, 2012. Available data has been included. This record may contain less data than currently active projects.