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Through the Independent Research and Developments activity, NASA Langley Research Center allocates funds to invest in early stage, high-payoff technologies and systems that are aligned with the NASA and Langley strategic plans and have high potential for future applications.
Some projects will align only with either CIF or IRAD support, but many are supported by a combination of both programs to leverage the most from limited resources. The investment in these early stage technologies is intended to mature them to the point that, if successful, they can substantially influence future Mission Directorate programs and projects, and receive follow-on support from NASA programs, external partners, or through commercialization.
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Some projects will align only with either CIF or IRAD support, but many are supported by a combination of both programs to leverage the most from limited resources. The investment in these early stage technologies is intended to mature them to the point that, if successful, they can substantially influence future Mission Directorate programs and projects, and receive follow-on support from NASA programs, external partners, or through commercialization.
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The preliminary results indicate that the concept has the potential to save both mass and volume with significantly less recession compared to traditional heat shield designs, and thus provide potential to enable new planetary missions. Initially, an earth return mission was evaluated using a spherical section type heat shield concept for a traditional earth entry capsule. Then a Mars entry sphere-cone concept was evaluated. Currently, a Mid-L/D concept for Mars entry is being studied. 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This epoxy is being exclusively formulated for cryogenic use. Utilizing storage tanks fabricated from fiber reinforced polymeric composites for storing cryogenic fluids such as liquid oxygen and liquid hydrogen under pressure is of great interest to NASA. In particular, their high strength to weight ratio gives them a clear advantage over strictly aluminum alloy components; a 20-40% weight reduction can also be expected. Unfortunately such composites, especially at cryogenic temperatures, develop stiffness that diminishes the desired toughness; this promotes delamination and crack growth which leads to leaking of the fuel component; this detriment is exacerbated if the component is cycled between room and cryogenic temperatures. The work proposed here intends to eliminate that concern by utilizing a unique, and patented, ionic liquid (IL) epoxy. Our novel, to date, results supporting that supposition include: · A viable means to synthesize high-quality ionic liquid epoxy monomer has been established. · Nano-scale Core-Shell-Rubber (CSR) particles designed to toughen polymers have been successfully and uniformly incorporated into the epoxy matrix. · Shock cycling of the epoxy between room (RT) and Liquid Nitrogen (LN2) temperatures, with and without CSR, does not appreciably affect the fracture energy at RT establishing that micro-cracking does not develop in the samples. · Testing shows that adding CSR particles improve toughness and strength at RT and LN2 temperatures. · Measurements of the epoxy Coefficient of Thermal Expansion from cryogenic to room temperature is very favorable at 35 ppm which places it amongst the lowest of the common polymers. · CSR increased the glass transition temperature (0% CSR = 61.5°; 8.8% CSR = 95.5°C) allowing a higher working range. · Carbon-fiber test articles utilizing CSR containing epoxy have been made and show no cracking or delamination when repeatedly cycled in LN2. Relevant test results show improvements over commercial products at both room and LN2 temperatures. Slight additions of CSR significantly increases the impact toughness which appears maximized near an 8.8% addition. Considerable improvements were also noted here at both room and LN2 temperatures. It was also noted that shocking the samples between room and LN2 temperatures, up to 10 times before testing, had no obvious effect in diminishing properties, i.e. no induced micro-cracking. Earlier, it had been shown that a carbon fiber composite cylinder fabricated with the ionic liquid epoxy performed better at room and LN2 temperatures than the commercially used Hexcel®. We have since successfully made some carbon fiber layups utilizing CSR containing epoxy for preliminary examination and testing. Composite integrity was maintained on these layups with no separation, delamination, or cracking. Finally, ionic liquids have a number of additional advantages as a base for epoxy resins. Their extremely low vapor pressures, good temperature stability, and low flammability further enhance their use for NASA deep space, cryogenic, applications. They have a comparatively \"greener\" manufacturing process than their counterparts. Low permeability to hydrogen, and trivial moisture uptake after several days of submersion in salt water was also established. The epoxy has also demonstrated strong binding to aluminum. In short, ionic liquid based epoxies and composites are ideally suited to meet challenges associated with achieving NASA's space exploration goals.","releaseStatus":"Released","status":"Completed","destinationType":[],"trlBegin":4,"trlCurrent":6,"trlEnd":6,"favorited":false,"detailedFunding":false,"programContacts":[{"contactId":159179,"canUserEdit":false,"firstName":"Gary","lastName":"Fleming","fullName":"Gary A Fleming","fullNameInverted":"Fleming, Gary A","middleInitial":"A","email":"gary.a.fleming@nasa.gov","receiveEmail":"Subscribed_User","programContactRole":"Program_Manager","programContactId":218,"programId":168,"programContactRolePretty":"Program Manager","projectContactRolePretty":""},{"contactId":233104,"canUserEdit":false,"firstName":"John","lastName":"Nelson","fullName":"John C Nelson","fullNameInverted":"Nelson, John C","middleInitial":"C","email":"john.c.nelson@nasa.gov","receiveEmail":"Subscribed_User","programContactRole":"Program_Director","programContactId":216,"programId":168,"programContactRolePretty":"Program Director","projectContactRolePretty":""}],"endDateString":"Oct 2015","startDateString":"Nov 2014"},"technologyOutcomePartner":"Other","technologyOutcomeDate":"2014-11-01","technologyOutcomePath":"Advanced_To","infoText":"Advanced within the program","infoTextExtra":"Another project within the program (Evaluation of Carbon Composite Overwrap Pressure Vessels Fabricated using Ionic Liquid Epoxies)","isIndirect":false,"technologyOutcomeRationalePretty":"","infusionPretty":"","isBiDirectional":true,"technologyOutcomeDateString":"Nov 2014","technologyOutcomeDateFullString":"November 2014","technologyOutcomePartnerPretty":"Other","technologyOutcomePathPretty":"Advanced To"},{"technologyOutcomeId":94403,"projectId":12022,"project":{"projectId":12022,"title":"Multifunctional Hot Structures Heat Shield","startDate":"2012-10-01","startYear":2012,"startMonth":10,"endDate":"2015-10-01","endYear":2015,"endMonth":10,"programId":167,"program":{"ableToSelect":false,"acronym":"LaRC CIF","isActive":true,"description":"
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Some projects will align only with either CIF or IRAD support, but many are supported by a combination of both programs to leverage the most from limited resources. The investment in these early stage technologies is intended to mature them to the point that, if successful, they can substantially influence future Mission Directorate programs and projects, and receive follow-on support from NASA programs, external partners, or through commercialization.
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Activities with in the Center Innovation Fund are proposed and led by NASA scientists and engineers. These activities and creative initiatives pursue emerging technologies that leverage talent and capabilities at the NASA Centers. ","parentProgram":{"ableToSelect":false,"acronym":"CIF","isActive":true,"description":"
Through the Center Innovation Fund, the Space Technology Mission Directorate allocates a small portion of the NASA workforce and procurement budget to internal research and development to feed early stage innovation in technology and exploration. Activities with in the Center Innovation Fund are proposed and led by NASA scientists and engineers. These activities and creative initiatives pursue emerging technologies that leverage talent and capabilities at the NASA Centers.
","parentProgram":{"ableToSelect":false,"isActive":true,"description":"Catalyst is a portfolio of early stage programs that specialize in different innovation constituencies and mechanisms to push the state of the art in aerospace technology development","programId":92327,"responsibleMd":{"canUserEdit":false,"locationEdit":false,"organizationRolePretty":"","organizationTypePretty":""},"title":"Catalyst","acronymOrTitle":"Catalyst"},"parentProgramId":92327,"programId":64,"responsibleMd":{"canUserEdit":false,"locationEdit":false,"organizationRolePretty":"","organizationTypePretty":""},"stockImageFileId":36643,"title":"Center Innovation Fund","acronymOrTitle":"CIF"},"parentProgramId":64,"programId":168,"responsibleMd":{"organizationId":4875,"organizationName":"Space Technology Mission Directorate","acronym":"STMD","organizationType":"NASA_Mission_Directorate","canUserEdit":false,"locationEdit":false,"organizationRolePretty":"","organizationTypePretty":"NASA Mission Directorate"},"responsibleMdOffice":4875,"stockImageFileId":36644,"title":"Center Innovation Fund: MSFC CIF","acronymOrTitle":"MSFC CIF"},"description":"In terms of \"Innovation\" this is a unique epoxy with unique properties, and NASA co-holds the patent. This epoxy is being exclusively formulated for cryogenic use. Utilizing storage tanks fabricated from fiber reinforced polymeric composites for storing cryogenic fluids such as liquid oxygen and liquid hydrogen under pressure is of great interest to NASA. In particular, their high strength to weight ratio gives them a clear advantage over strictly aluminum alloy components; a 20-40% weight reduction can also be expected. Unfortunately such composites, especially at cryogenic temperatures, develop stiffness that diminishes the desired toughness; this promotes delamination and crack growth which leads to leaking of the fuel component; this detriment is exacerbated if the component is cycled between room and cryogenic temperatures. The work proposed here intends to eliminate that concern by utilizing a unique, and patented, ionic liquid (IL) epoxy. Our novel, to date, results supporting that supposition include: · A viable means to synthesize high-quality ionic liquid epoxy monomer has been established. · Nano-scale Core-Shell-Rubber (CSR) particles designed to toughen polymers have been successfully and uniformly incorporated into the epoxy matrix. · Shock cycling of the epoxy between room (RT) and Liquid Nitrogen (LN2) temperatures, with and without CSR, does not appreciably affect the fracture energy at RT establishing that micro-cracking does not develop in the samples. · Testing shows that adding CSR particles improve toughness and strength at RT and LN2 temperatures. · Measurements of the epoxy Coefficient of Thermal Expansion from cryogenic to room temperature is very favorable at 35 ppm which places it amongst the lowest of the common polymers. · CSR increased the glass transition temperature (0% CSR = 61.5°; 8.8% CSR = 95.5°C) allowing a higher working range. · Carbon-fiber test articles utilizing CSR containing epoxy have been made and show no cracking or delamination when repeatedly cycled in LN2. Relevant test results show improvements over commercial products at both room and LN2 temperatures. Slight additions of CSR significantly increases the impact toughness which appears maximized near an 8.8% addition. Considerable improvements were also noted here at both room and LN2 temperatures. It was also noted that shocking the samples between room and LN2 temperatures, up to 10 times before testing, had no obvious effect in diminishing properties, i.e. no induced micro-cracking. Earlier, it had been shown that a carbon fiber composite cylinder fabricated with the ionic liquid epoxy performed better at room and LN2 temperatures than the commercially used Hexcel®. We have since successfully made some carbon fiber layups utilizing CSR containing epoxy for preliminary examination and testing. Composite integrity was maintained on these layups with no separation, delamination, or cracking. Finally, ionic liquids have a number of additional advantages as a base for epoxy resins. Their extremely low vapor pressures, good temperature stability, and low flammability further enhance their use for NASA deep space, cryogenic, applications. They have a comparatively \"greener\" manufacturing process than their counterparts. Low permeability to hydrogen, and trivial moisture uptake after several days of submersion in salt water was also established. The epoxy has also demonstrated strong binding to aluminum. In short, ionic liquid based epoxies and composites are ideally suited to meet challenges associated with achieving NASA's space exploration goals.","releaseStatus":"Released","status":"Completed","destinationType":[],"trlBegin":4,"trlCurrent":6,"trlEnd":6,"favorited":false,"detailedFunding":false,"programContacts":[{"contactId":159179,"canUserEdit":false,"firstName":"Gary","lastName":"Fleming","fullName":"Gary A Fleming","fullNameInverted":"Fleming, Gary A","middleInitial":"A","email":"gary.a.fleming@nasa.gov","receiveEmail":"Subscribed_User","programContactRole":"Program_Manager","programContactId":218,"programId":168,"programContactRolePretty":"Program Manager","projectContactRolePretty":""},{"contactId":233104,"canUserEdit":false,"firstName":"John","lastName":"Nelson","fullName":"John C Nelson","fullNameInverted":"Nelson, John C","middleInitial":"C","email":"john.c.nelson@nasa.gov","receiveEmail":"Subscribed_User","programContactRole":"Program_Director","programContactId":216,"programId":168,"programContactRolePretty":"Program Director","projectContactRolePretty":""}],"endDateString":"Oct 2015","startDateString":"Nov 2014"},"technologyOutcomePartner":"Other","technologyOutcomeDate":"2014-11-01","technologyOutcomePath":"Advanced_To","infoText":"Advanced within the program","infoTextExtra":"Another project within the program (Evaluation of Carbon Composite Overwrap Pressure Vessels Fabricated using Ionic Liquid Epoxies)","isIndirect":true,"technologyOutcomeRationalePretty":"","infusionPretty":"","isBiDirectional":true,"technologyOutcomeDateString":"Nov 2014","technologyOutcomeDateFullString":"November 2014","technologyOutcomePartnerPretty":"Other","technologyOutcomePathPretty":"Advanced To"}],"primaryImage":{"file":{"fileExtension":"png","fileId":355831,"presignedUpload":false,"fileSizeString":"0 Byte"},"libraryItemId":354951,"description":"Project Image Multifunctional Hot Structure Heat Shield","projectId":12022,"publishedDateString":"","entryDateString":"","libraryItemTypePretty":"","modifiedDateString":""},"libraryItems":[{"file":{"fileExtension":"png","fileId":355831,"fileName":"12022-1378761519314","fileSize":496132,"objectId":354951,"objectType":"libraryItemFiles","presignedUpload":false,"fileSizeString":"484.5 KB"},"files":[{"fileExtension":"png","fileId":355831,"fileName":"12022-1378761519314","fileSize":496132,"objectId":354951,"objectType":"libraryItemFiles","presignedUpload":false,"fileSizeString":"484.5 KB"}],"libraryItemId":354951,"title":"12022-1378761519314.png","description":"Project Image Multifunctional Hot Structure Heat Shield","libraryItemType":"Image","projectId":12022,"isPrimary":true,"internalOnly":false,"publishedDateString":"","entryDateString":"01/22/25 01:10 AM","libraryItemTypePretty":"Image","modifiedDateString":"05/22/23 02:25 PM"},{"files":[],"libraryItemId":354952,"title":"Preliminary Development of a Multifunctional Hot Structure Heat Shield","description":"
Walker, S. P., Daryabeigi, K., Samareh, J. A., Armand, S. C., & Perino, S. V. Preliminary Development of a Multifunctional Hot Structure Heat Shield, AIAA SciTech, 13-17 January 2014, National Harbor, Maryland, AIAA 2014-0350.
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