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The National Aeronautics and Space Administration

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The National Aeronautics and Space Administration

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    1. The National Aeronautics and Space Administration

    2. Responsibilities as an Intern My internship consisted of two different projects: Business/ Engineering Management Internship Mentor: Marty Kress, VSCI CEO & NSSTC Executive Director Location: The National Space Science and Technology Center Cryogenic Material Testing Mentor: Gail Gordon, Mike Watwood, & Mike Pendleton Location: The Hydrogen Test Facility, MSFC 4628

    3. VCSI Current and Future Projects “VCSI – New Huntsville Thrust – New Model for Collaborative R&D”

    4. Not-for-profit organization (501(c) 3) incorporated in August 2006 VCSI’s objectives are to: Develop and implement requirements-driven technology programs Identify and link emerging technologies from the national R&T community to address customer requirements Promote/implement innovative management approaches to technical solutions Most importantly – expand the R&D base in Huntsville

    6. Board of Directors and Liaisons Board Chairmen : Marty Kress Government/University Liaison MSFC, NASA: Dave King, Center Director, John Horack, Director S&MS Aviation & Missile R&D and Engineering Center, Suzy Young, Director Adv S&T Space and Missile Defense Command, Rodney Robertson, Director of Technology Tennessee Valley Authority: Howard Thrailkill, Commissioner VP Research UAH, Ron Greenwood Missile Defense Agency: Gen. Chris Anzalone, Deputy Director Academia – Voting University of Auburn, Ralph Zee (SSTA) UAH, Dave Williams, President Corporate Members - Voting SAIC: Bill Gurley Dynetics: Marc Bendickson Gray Research: Ron Gray Lockheed: John Holly Beason and Nalley: Gail Wall Sirote and Permutt: Joe Ritch COLSA: Anthony DiRienzo Strategic Solutions: Glenn Priddy Schafer: Charles Chitwood VCSI: Marty Kress, Ex. Dir. Ex Officio Univ. of Alabama,Chuck Karr

    7. Current Projects 1. TVA Rain Gauge Initiative 2. Tawani 2008 International Antarctica Expedition 3. Army RS JPO Marcbot Project 4. NASA mission studies/instrument plan 5. AMRDEC/NASA – Distributed Systems Integrated Test Bed

    8. Pending Proposals / Awaiting Final Authorization NOAA HIRAD Initiative 2. Ares Project Office Initiatives NDE, Wind Lidar, etc NSF Proposal – Miniature Electron Scanning Microscope SERVIR – expansion to Africa – other nations FY 09 Congressional Asks – NOAA, SMDC, AMRDEC SMDC Flight Project Lunar Lander Technology Testbed – Integrated IR&D/COTS Concept 8. Reverse Venture Forum

    9. Cryoflex Thermal Protection System Material Testing The testing was implemented in order to find a new TPS material for Ares I CLV The EPA no longer approved the TPS that was designed for the shuttles external tank A variety of different TPS will be tested in the future The goal is to find a TPS that will meet both NASA and EPA requirements

    10. Background The cryoflex foam stress analysis will determine the structural integrity of the new foam thermal protective system (TPS) for the upper stage of Ares I CV The testing will expose the foam to a hydrogen pressure vessel This vessel will simulate the liquid fuel tanks in the upper stage Liquid hydrogen will be used as the cryogenic testing material The liquid hydrogen will be -423oF while in the pressure vessel A tensile load will simulate the rapid filling and expending of the liquid fuels

    11. Test Procedure The vessel is purged with helium Eliminating oxygen and nitrogen condensate Liquid hydrogen is then pumped into the vessel The thermocouple must read approximately -320oF for the test to begin The colder the better A tensile load is applied once the required temperature is achieved The load is released and the specimen is inspected The tensile load increase incrementally until failure occurs Failure is defined as the TPS delaminating from the bracket of at least 0.3 in The temperature and tensile load is recorded at the failure conditions

    12. Apparatus The test apparatus consist of: An insulated pressure vessel (As seen on the left) TPS specimens mounted to an aluminum bracket A Load frame Gaseous helium and liquid hydrogen Type E thermocouples ( 2 on bracket, 1 in vessel) The redesigned apparatus will consist of: An exterior insulating foam box (see right in white) A wooded frame to fit the pressure vessel A helium purge A mounting frame (seen on right in red) A camera capable of operation in cryogenic environments

    13. My Contributions

    14. Current Progress The initial testing did not achieve the desired -320oF environment The apparatus was redesigned to eliminate possible heat sinks Since the initial testing the following was redesigned for the apparatus Mounting frame Wood frame over the pressure vessel An exterior insulating foam box An insulated camera The next set of test will continue in mid august, once the new apparatus is built

    15. Marshall Space Flight Center The National Space Science and Technology Center The Vermont Space Grant Acknowledgements

    16. Questions?

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