{"project":{"acronym":"","projectId":33552,"title":"Metallic Joining to Advanced Ceramic Composites","primaryTaxonomyNodes":[{"taxonomyNodeId":10856,"taxonomyRootId":8816,"parentNodeId":10855,"level":3,"code":"TX12.1.1","title":"Lightweight Structural Materials","definition":"Lightweight structural materials reduce the mass and increase the efficiency of structures and structure components including advanced metallics, nanomaterials, polymers, matrix composites, multifunctional materials, damage detecting/damage tolerant materials, and self-repairing/self-healing materials.","exampleTechnologies":"Nanofibers, fibers, resins and adhesives that enable the tailoring of large monolithic structures; materials that perform multiple functions, materials that include mechanisms for fast, in-situ repairs; topology optimized structures; architectured foams; novel low density metal; composite alloys","hasChildren":false,"hasInteriorContent":true}],"startTrl":2,"currentTrl":4,"endTrl":4,"benefits":"Plasma's targeted NASA application is the Orion ACM program and launch abort systems for current and future missions. Other NASA applications include In Space Propulsion components for attitude control, orbit maintenance, repositioning of satellites/spacecraft, reaction control systems, hypersonic vehicle hot structure control surface actuation rod/support attachment, descent/ascent engines, nuclear power/propulsion, and reusable launch vehicle propulsion applications.
Both government and commercial entities in the following sectors use advanced high-temperature materials for the following applications: coatings, defense, material R&D, nuclear power, aeronautics, aerospace, propulsion, and automotive. Plasma's targeted commercial applications include joining composites to metals for aircraft composite components, thermal protection systems, rocket nozzles, heat pipes, and propulsion subcomponents.","description":"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.","startYear":2015,"startMonth":6,"endYear":2015,"endMonth":12,"statusDescription":"Completed","principalInvestigators":[{"contactId":469921,"canUserEdit":false,"firstName":"Timothy","lastName":"Mckechnie","fullName":"Timothy N Mckechnie","fullNameInverted":"Mckechnie, Timothy N","middleInitial":"N","primaryEmail":"timothy.n.mckechnie@nasa.gov","publicEmail":true,"nacontact":false},{"contactId":467924,"canUserEdit":false,"firstName":"Timothy","lastName":"McKechnie","fullName":"Timothy Mckechnie","fullNameInverted":"McKechnie, Timothy","primaryEmail":"timmck@plasmapros.com","publicEmail":true,"nacontact":false}],"programDirectors":[{"contactId":206378,"canUserEdit":false,"firstName":"Jason","lastName":"Kessler","fullName":"Jason L Kessler","fullNameInverted":"Kessler, Jason L","middleInitial":"L","primaryEmail":"jason.l.kessler@nasa.gov","publicEmail":true,"nacontact":false}],"programExecutives":[{"contactId":215154,"canUserEdit":false,"firstName":"Jennifer","lastName":"Gustetic","fullName":"Jennifer L Gustetic","fullNameInverted":"Gustetic, Jennifer L","middleInitial":"L","primaryEmail":"jennifer.l.gustetic@nasa.gov","publicEmail":true,"nacontact":false}],"programManagers":[{"contactId":62051,"canUserEdit":false,"firstName":"Carlos","lastName":"Torrez","fullName":"Carlos Torrez","fullNameInverted":"Torrez, Carlos","primaryEmail":"carlos.torrez@nasa.gov","publicEmail":true,"nacontact":false}],"projectManagers":[{"contactId":3164187,"canUserEdit":false,"firstName":"Peter","lastName":"Valentine","fullName":"Peter Valentine","fullNameInverted":"Valentine, Peter","primaryEmail":"Peter.G.Valentine@nasa.gov","publicEmail":true,"nacontact":false},{"contactId":461333,"canUserEdit":false,"firstName":"Theresa","lastName":"Stanley","fullName":"Theresa M Stanley","fullNameInverted":"Stanley, Theresa M","middleInitial":"M","primaryEmail":"theresa.m.stanley@nasa.gov","publicEmail":true,"nacontact":false}],"website":"","libraryItems":[{"file":{"fileExtension":"pdf","fileId":291807,"fileName":"SBIR_2015_1_BC_H5.02-9227","fileSize":115415,"objectId":288322,"objectType":{"lkuCodeId":889,"code":"LIBRARY_ITEMS","description":"Library Items","lkuCodeTypeId":182,"lkuCodeType":{"codeType":"OBJECT_TYPE","description":"Object Type"}},"objectTypeId":889,"fileSizeString":"112.7 KB"},"files":[{"fileExtension":"pdf","fileId":291807,"fileName":"SBIR_2015_1_BC_H5.02-9227","fileSize":115415,"objectId":288322,"objectType":{"lkuCodeId":889,"code":"LIBRARY_ITEMS","description":"Library Items","lkuCodeTypeId":182,"lkuCodeType":{"codeType":"OBJECT_TYPE","description":"Object Type"}},"objectTypeId":889,"fileSizeString":"112.7 KB"}],"id":288322,"title":"Briefing Chart","description":"Metallic Joining to Advanced Ceramic Composites Briefing 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Image","file":{"fileExtension":"jpg","fileId":306414,"fileName":"SBIR_15_1_H5.02-9227","fileSize":396989,"objectId":66573,"objectType":{"lkuCodeId":1841,"code":"TRANSITION_FILES","description":"Transition Files","lkuCodeTypeId":182,"lkuCodeType":{"codeType":"OBJECT_TYPE","description":"Object Type"}},"fileSizeString":"387.7 KB"},"transitionId":66573,"fileId":306414}],"infoText":"Closed out","infoTextExtra":"","dateText":"December 2015"},{"transitionId":66574,"projectId":33552,"partner":"Other","transitionDate":"2016-06-01","path":"Advanced To","relatedProjectId":89853,"relatedProject":{"acronym":"","projectId":89853,"title":"Metallic Joining to Advanced Ceramic Composites","startTrl":4,"currentTrl":6,"endTrl":6,"benefits":"Results of the Phase II will support the insertion of the joining technology of metallic to ceramic composite hot structures in the Attitude Control Motor of the Launch Abort System for SLS/Orion.
Joining advanced composites to metal structures is applicable to existing and future NASA programs including the ACM motors of Orion MPCV�s Launch Abort System, human Lunar ascent/decent, and the Commercial Crew motors; Nozzle extensions of upper stage engines for nanosatellite launch (e.g. ORBITEC�s vortex liquid rocket engine) and ISS resupply (e.g. SpaceX�s Merlin Vacuum liquid rocket engines); and RL10 engines, upper stage nozzle extensions; Nosetips, leading edges and control surfaces for hypersonic vehicles; turbine engine components, and exit cones and control vanes for tactical missiles.","description":"The Orion Launch Abort System (LAS) utilizes attitude control motors (ACM) with advanced ceramic composite components that function as a valve control system to allow for safe maneuverability away from danger. This system is made steerable due to the valve controlled thrusters which utilize advanced ceramic pintles made of 4D C/C-SiC that are attached to metallic structures and actuated. During the Phase I effort, an innovative technique to join metallics with the advanced ceramic composites was demonstrated. Detailed characterization confirmed the deposited metal (Inconel 625) produced during this investigation had good adherence to C-C/SiC pintles and no interfacial reactions occurred during deposition or elevated temperature exposure. In Phase II, the joining interface will be optimized and pintle assembles will be produced for hot fire testing with Orbital ATK. Additional CMC materials and components will also be developed.","startYear":2016,"startMonth":6,"endYear":2020,"endMonth":8,"statusDescription":"Completed","website":"","program":{"acronym":"SBIR/STTR","active":true,"description":"
The NASA SBIR and STTR programs fund the research, development, and demonstration of innovative technologies that fulfill NASA needs as described in the annual Solicitations and have significant potential for successful commercialization. If you are a small business concern (SBC) with 500 or fewer employees or a non-profit RI such as a university or a research laboratory with ties to an SBC, then NASA encourages you to learn more about the SBIR and STTR programs as a potential source of seed funding for the development of your innovations.
The SBIR and STTR programs have 3 phases:
The SBIR and STTR Phase I contracts last for 6 months with a maximum funding of $125,000, and Phase II contracts last for 24 months with a maximum funding of $750,000 - $1.5 million.
Opportunity for Continued Technology Development Post-Phase II:
The NASA SBIR/STTR Program currently has in place two initiatives for supporting its small business partners past the basic Phase I and Phase II elements of the program that emphasize opportunities for commercialization. Specifically, the NASA SBIR/STTR Program has the Phase II Enhancement (Phase II-E) and Phase II eXpanded (Phase II-X) contract options.
Please review the links below to obtain more information on the SBIR/STTR programs.
Provides an overview of the SBIR and STTR programs as implemented by NASA
Provides access to the annual SBIR/STTR Solicitations containing detailed information on the program eligibility requirements, proposal instructions and research topics and subtopics
Schedule and links for the SBIR/STTR solicitations and selection announcements
Federal and non-Federal sources of assistance for small business
Search our complete archive of awarded project abstracts to learn about what NASA has funded
Still have questions? Visit the program FAQs
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The SBIR and STTR programs have 3 phases:
The SBIR and STTR Phase I contracts last for 6 months with a maximum funding of $125,000, and Phase II contracts last for 24 months with a maximum funding of $750,000 - $1.5 million.
Opportunity for Continued Technology Development Post-Phase II:
The NASA SBIR/STTR Program currently has in place two initiatives for supporting its small business partners past the basic Phase I and Phase II elements of the program that emphasize opportunities for commercialization. Specifically, the NASA SBIR/STTR Program has the Phase II Enhancement (Phase II-E) and Phase II eXpanded (Phase II-X) contract options.
Please review the links below to obtain more information on the SBIR/STTR programs.
Provides an overview of the SBIR and STTR programs as implemented by NASA
Provides access to the annual SBIR/STTR Solicitations containing detailed information on the program eligibility requirements, proposal instructions and research topics and subtopics
Schedule and links for the SBIR/STTR solicitations and selection announcements
Federal and non-Federal sources of assistance for small business
Search our complete archive of awarded project abstracts to learn about what NASA has funded
Still have questions? Visit the program FAQs
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