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Metallic Joining to Advanced Ceramic Composites

Award Information
Agency: National Aeronautics and Space Administration
Branch: N/A
Contract: NNX15CM46P
Agency Tracking Number: 154773
Amount: $125,000.00
Phase: Phase I
Program: SBIR
Solicitation Topic Code: H5.02
Solicitation Number: N/A
Solicitation Year: 2015
Award Year: 2015
Award Start Date (Proposal Award Date): 2015-06-17
Award End Date (Contract End Date): 2015-12-17
Small Business Information
4914 Moores Mill Road
Huntsville, AL 35811-1558
United States
DUNS: 799114574
HUBZone Owned: No
Woman Owned: No
Socially and Economically Disadvantaged: No
Principal Investigator
 Timothy McKechnie
 (256) 851-7653
Business Contact
 Angela Hattaway
Title: Business Official
Phone: (256) 851-7653
Research Institution

Currently, advanced ceramic composites are state-of-the-art for hypersonic airbreathing and space propulsion applications. The Launch Abort System (LAS) of the Orion Multi-Crew Exploration Vehicle (MCEV) will provide a safe escape for the crew in the event of an emergency during launch. A key component of the LAS is its Attitude Control Motor (ACM) containing numerous advanced ceramic composite subcomponents. To fully utilize the high specific strengths and temperature capabilities of these composites, reliable high-temperature joining techniques are needed for attachment to metallic structures. Typical joining technologies such as epoxy, brazing and soldering are not useful in high-temperature applications. Currently, pintles and hot structures are mechanically fastened through highly stressed joints to metallic rods and actuators. Mechanical fastening is not an ideal solution since it causes stress concentrations and destruction of continuous fibers by through holes and threads reducing the mechanical properties of the composite structure. A solution that will resolve joining of numerous composites to metallic components is being pursued. During Phase I, techniques to join metallic structures to advanced ceramic composites will be investigated resulting in structural qualification testing for the ACM pintle assembly. During Phase II, ACM hot gas components will be fabricated and hot fire tested.

* Information listed above is at the time of submission. *

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