{"project":{"acronym":"","projectId":91674,"title":"Creating and Understanding Hybrid Interfaces of Multifunctional Composite Laminates for Extreme Environments","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":3,"endTrl":3,"benefits":"Hybrid composites are of high interest due to increasing needs for lightweight and multifunctional structures and materials that can operate at and sustain extreme environments such as high temperature and pressure. Because of the mismatch in properties of different layers, the interfacial regions in these hybrid systems are critical for reliability.","description":"Due to increasing needs for lightweight and multifunctional structures and materials that can operate at and sustain the extreme environment such as high temperature and pressure, hybrid composites are of high interests and being developed recently. Because of the mismatch in properties of different layers, the interfacial regions in these hybrid systems are critical for reliability. The objectives of this work are to develop a robust and multifunctional interface between shape memory alloys and polymer matrix composite for hybrid materials that undergoes elevated temperatures at the operating environment. Functionalities of this interface include thermo-mechanical capability together with self-sensing and self-healing abilities. Approaches from experimental techniques for manufacturing and characterizing will be used. Computational models across the scales utilizing molecular dynamics, micromechanics and finite element methods will be developed to assist the understanding and interpreting the complex phenomena observed at the interface as well as to help design the interface that meets the specific needs.","startYear":2014,"startMonth":8,"endYear":2016,"endMonth":5,"statusDescription":"Completed","principalInvestigators":[{"contactId":362667,"canUserEdit":false,"firstName":"Ozden","lastName":"Ochoa","fullName":"Ozden Ochoa","fullNameInverted":"Ochoa, Ozden","publicEmail":false,"nacontact":false}],"programDirectors":[{"contactId":84634,"canUserEdit":false,"firstName":"Claudia","lastName":"Meyer","fullName":"Claudia M Meyer","fullNameInverted":"Meyer, Claudia M","middleInitial":"M","primaryEmail":"claudia.m.meyer@nasa.gov","publicEmail":true,"nacontact":false}],"programExecutives":[{"contactId":84634,"canUserEdit":false,"firstName":"Claudia","lastName":"Meyer","fullName":"Claudia M Meyer","fullNameInverted":"Meyer, Claudia M","middleInitial":"M","primaryEmail":"claudia.m.meyer@nasa.gov","publicEmail":true,"nacontact":false}],"programManagers":[{"contactId":183514,"canUserEdit":false,"firstName":"Hung","lastName":"Nguyen","fullName":"Hung D Nguyen","fullNameInverted":"Nguyen, Hung D","middleInitial":"D","primaryEmail":"hung.d.nguyen@nasa.gov","publicEmail":true,"nacontact":false}],"projectManagers":[{"contactId":228327,"canUserEdit":false,"firstName":"John","lastName":"Connell","fullName":"John W Connell","fullNameInverted":"Connell, John W","middleInitial":"W","primaryEmail":"john.w.connell@nasa.gov","publicEmail":true,"nacontact":false}],"coInvestigators":[{"contactId":180563,"canUserEdit":false,"firstName":"Hieu","lastName":"Truong","fullName":"Hieu Q Truong","fullNameInverted":"Truong, Hieu Q","middleInitial":"Q","primaryEmail":"hieu.q.truong@nasa.gov","publicEmail":true,"nacontact":false}],"website":"https://www.nasa.gov/directorates/spacetech/home/index.html","libraryItems":[],"transitions":[{"transitionId":75798,"projectId":91674,"partner":"Other","transitionDate":"2014-08-01","path":"Advanced From","relatedProjectId":91354,"relatedProject":{"acronym":"","projectId":91354,"title":"Electric-hydrodynamic Control of Two-Phase Heat Transfer in Microgravity Testing","startTrl":3,"currentTrl":3,"endTrl":3,"benefits":"The technology of novel heat transfer systems that employ boiling in microgravity will provide new transformational capabilities for proven two-phase thermal systems through incremental modifications to handle high heat load when local boiling takes place. These systems will benefit the commercial space industry, future NASA missions, and other government agences such as the military.","description":"The main outcome of the proposed effort is the validation of a novel electro-hydrodynamic (EHD) technology to intensify and control two-phase heat transfer in microgravity. Flight tests will advance the EHD technology maturity from Proof of Concept (TRL 3-4) to Demonstration in Microgravity (TRL 6-7). The work is related to the major technical challenges prioritized by NASA Space Technology Roadmap, Technology Area 14 Thermal Management Systems and NASA Space Technology Grand Challenges.
This effort is related to T0043.
Publication (November 2018): Single-bubble water boiling on small heater under Earth’s and low gravity.","startYear":2012,"startMonth":3,"endYear":2016,"endMonth":5,"statusDescription":"Completed","website":"https://www.nasa.gov/directorates/spacetech/home/index.html","program":{"acronym":"FO","active":true,"description":"
The President’s 2010 National Space Policy:
“A robust and competitive commercial space sector is vital to continued progress in space. The United States is committed to encouraging and facilitating the growth of a U.S. commercial space sector that supports U.S. needs, is globally competitive, and advances U.S. leadership in the generation of new markets and innovation-driven entrepreneurship.”
Flight Opportunities directly answers the call of the President’s policy through the acquisition of suborbital launch services on commercial suborbital launch vehicles. By purchasing flight opportunities on U.S. commercial vehicles the Flight Opportunities program is encouraging and facilitating the growth of this market while simultaneously providing pathways to advance the technology readiness of a wide range of new launch vehicle and space technologies.
One of the greatest challenges NASA faces in incorporating advanced technologies into future missions is bridging the mid-technology readiness level (TRL) (4-7) gap (or “valley of death”), between component or prototype testing in a lab or ground facility setting, and the final infusion of a new technology into critical path exploration or science mission development. To cross this gap, the proposed new technology must pass system level testing in a relevant operational environment. Maturing a space technology to flight readiness status through relevant environment testing is a significant challenge from cost, schedule, and technical risk perspectives.
FO has its lineage from the former Innovative Partnership Program (IPP) of FY09, specifically the Facilitated Access to the Space Environment for Technology (FAST) project and the Commercial Reusable Suborbital Research (CRuSR) project. The FAST and CRuSR activities are continued within the FO Program, as the parabolic and suborbital, flight campaigns, respectively. The flights will provide opportunities to expose new technologies to low-g environments and/or high altitude environments. The intent is to demonstrate and mature various technologies for future applications. These emerging technologies will come from the nine other programs within the Space Technology Mission Directorate, from the other Mission Directorates and external sources (other Government Agencies, Academia, and Commercial Industries.
The NASA Flight Opportunities (FO) Program has been established as a part of the Space Technologies Mission Directorate (STMD) to rapidly develop, demonstrate and infuse revolutionary, high-payoff technologies through transparent, collaborative partnerships, expanding the boundaries of the aerospace enterprise by providing the nation’s investments in space technologies to make a difference in the world around us. FO focuses on maturation of technologies that are of benefit to multiple customers, to flight readiness status with an outcome of Technology Readiness Level (TRL) 6 or higher. These crosscutting capabilities are those that advance multiple future aerospace missions, including flight projects where near-space or in-space demonstration is needed before the capability can transition to direct mission application. Maturing technologies to a higher TRL status through relevant flight opportunities testing is a significant challenge from both a cost and risk perspective.
","programId":72,"responsibleMd":{"acronym":"STMD","canUserEdit":false,"city":"","external":false,"linkCount":0,"organizationId":4875,"organizationName":"Space Technology Mission Directorate","organizationType":"NASA_Mission_Directorate","naorganization":false,"organizationTypePretty":"NASA Mission Directorate"},"responsibleMdId":4875,"stockImageFileId":36656,"title":"Flight Opportunities"},"lastUpdated":"2024-2-6","releaseStatusString":"Released","viewCount":99,"endDateString":"May 2016","startDateString":"Mar 2012"},"infoText":"Advanced from another project within the program","infoTextExtra":"Another project within the program (Electric-hydrodynamic Control of Two-Phase Heat Transfer in Microgravity Testing)","dateText":"August 2014"},{"transitionId":75799,"projectId":91674,"transitionDate":"2016-05-01","path":"Closed Out","details":"The primary goal of this work is to develop robust hybrid interfaces between metal/alloy and polymer matrix composites (PMC) in composite laminates for high temperature (200-300oC) applications, taking into account the consideration of the following factors: • Surface chemistry and topography • Reinforcement architecture • Damage initiation and delamination • Thermal degradation More specifically, this research is to experimentally and computationally investigate the “fracture toughness” of the hybrid metal-PMC interface as a function of temperature and interfacial architecture. In this work, hybrid composite laminates were successfully created using out-ofautoclave processing techniques. The laminates contained one single layer of metal foil sandwiched between a number (four or eight) of layers of carbon fabric reinforcement that created a symmetric layup with respect to the metal foil. In these hybrid laminates, the hybrid interfaces between metal and polymer composite were created via co-curing. Different metal foils, fabric reinforcement types and polymer matrix were investigated. In addition, a variety of surface treatment techniques were employed on the metal foil prior to placing in in the hybrid laminate layup. The fracture behavior of the fabricated hybrid interfaces was investigated at both room and elevated temperature. Furthermore, physical, thermal-mechanical as well as microscopy of the laminates were performed. It was found that in order to create strong hybrid metal-resin interface, the surface chemistry on the metal side plays a significant role. Robust hybrid interfaces should be created via formation of covalent bonds at the interface region. This could be achieved via sol-gel surface treatment method as demonstrated in this work. Other important aspects of consideration include not only thermal degradation of the surface treatment but also the compatibility of the sol-gel chemistry with the polymer resin. It was shown in this work that the fracture behavior of the hybrid interfaces depends not only on the properties of polymer resin, which dictate whether the crack propagates in a stable or unstable manner, or whether the hybrid interface exhibits brittle or ductile-like failure, but also the architecture of the reinforcement in the composite. Moreover, the loading configuration also has an important impact on the mode of failure at these hybrid interfaces. It was shown that the same hybrid interface that exhibits cohesive failure mode after the mode I fracture toughness test failed adhesively under mode II loading. In addition, surface roughness or architecture of metallic surface played an important role. Fracture toughness could be higher where rougher metallic surfaces are present at the hybrid interface. This is ascribed to the more energy released when micro-cracks formed during the fracture process due to stress concentration caused by the surface roughness. One of the most significant contributions of this work is that for the first time, robust high temperature hybrid interfaces between metal (Ti)/shape memory alloy (NiTi) and polyimide matrix composite were successfully fabricated and tested. Laser ablation and a customsynthesized sol-gel treatment were employed to prepare the Ti and NiTi foils surfaces for strong, direct adhesion with the polyimide AFR-PE-4 resin system. This high temperature interface could sustain temperature up to 250 oC. One interesting finding was revealed by SEM/EDS and nanoIR analysis of the hybrid interface cross-section where it was observed that Si from the solgel treatment solution clearly penetrated into the ablated Ti surface. This was attributed to the porosities on the Ti surface created during laser ablation. Evidence of covalent bonds formation between the sol-gel treatment solution and Ti foil was confirmed by nanoIR analysis. It was found that the degree of hydrolyzation of the custom- synthesized sol-gel treatment solution or the time associated with sol-gel hydrolysis was important. In this work, the best results were achieved with a 16-hour hydrolysis although further optimization could be possible. It was also demonstrated in this work that in-situ Rayleigh backscattering fiber optics measurements were obtained during DCB experiments. This new technique to measure distributed strains allows us to interpret the DCB experiment in a new way and enables the visualization of strain energy release upon crack propagation. In addition to the experimental investigation, finite element analysis was carried out to model the double cantilever beam experiment performed. Axial strain profiles along the specimen’s edge obtained from FEA were compared to those measured in the experiment using optical fibers. Thermal residual stresses due to thermal curing and their effects on the strain energy release rates upon crack propagation were analyzed. In addition, shape memory alloy phase transformation in the hybrid DCB specimens containing NiTi foil occurring during the test at room temperature was observed experimentally. This phase transformation was captured and illustrated by the FEA performed. The FEA results obtained in this work further support experimental observations. Furthermore, microscale finite element model to study the effect of micro-roughness pattern created by laser ablation of the metal surface on crack initiation and propagation behavior at the hybrid interface was carried out. The results obtained from this model supported the evidence of micro-crack formation on the fracture surfaces observed from the SEM analysis.","infoText":"Closed out","infoTextExtra":"","dateText":"May 2016"}],"responsibleMd":{"acronym":"STMD","canUserEdit":false,"city":"","external":false,"linkCount":0,"organizationId":4875,"organizationName":"Space Technology Mission Directorate","organizationType":"NASA_Mission_Directorate","naorganization":false,"organizationTypePretty":"NASA Mission Directorate"},"program":{"acronym":"STRG","active":true,"description":"\tThe Space Technology Research Grants Program will accelerate the development of "push" technologies to support the future space science and exploration needs of NASA, other government agencies and the commercial space sector. Innovative efforts with high risk and high payoff will be encouraged. The program is composed of two competitively awarded components.
","programId":69,"responsibleMd":{"acronym":"STMD","canUserEdit":false,"city":"","external":false,"linkCount":0,"organizationId":4875,"organizationName":"Space Technology Mission Directorate","organizationType":"NASA_Mission_Directorate","naorganization":false,"organizationTypePretty":"NASA Mission Directorate"},"responsibleMdId":4875,"stockImageFileId":36658,"title":"Space Technology Research Grants"},"leadOrganization":{"acronym":"Texas A&M","canUserEdit":false,"city":"College Station","country":{"abbreviation":"US","countryId":236,"name":"United States"},"countryId":236,"external":true,"linkCount":0,"organizationId":3185,"organizationName":"Texas A & M University-College Station","organizationType":"Academia","stateTerritory":{"abbreviation":"TX","country":{"abbreviation":"US","countryId":236,"name":"United States"},"countryId":236,"name":"Texas","stateTerritoryId":29},"stateTerritoryId":29,"msiData":{"2017":["Hispanic Serving Institutions (HSI)"],"2023":["Hispanic Serving Institutions (HSI)"]},"setAsideData":[],"murepUnitId":228723,"naorganization":false,"organizationTypePretty":"Academia"},"supportingOrganizations":[{"acronym":"LaRC","canUserEdit":false,"city":"Hampton","country":{"abbreviation":"US","countryId":236,"name":"United States"},"countryId":236,"external":false,"linkCount":0,"organizationId":4852,"organizationName":"Langley Research Center","organizationType":"NASA_Center","stateTerritory":{"abbreviation":"VA","country":{"abbreviation":"US","countryId":236,"name":"United States"},"countryId":236,"name":"Virginia","stateTerritoryId":7},"stateTerritoryId":7,"naorganization":false,"organizationTypePretty":"NASA Center"}],"statesWithWork":[{"abbreviation":"TX","country":{"abbreviation":"US","countryId":236,"name":"United States"},"countryId":236,"name":"Texas","stateTerritoryId":29}],"lastUpdated":"2024-2-6","releaseStatusString":"Released","viewCount":755,"endDateString":"May 2016","startDateString":"Aug 2014"}}