{"project":{"acronym":"","projectId":32751,"title":"Large Propellant Tank Cryo-Cooler (LPTC) Project","startTrl":4,"currentTrl":6,"endTrl":6,"benefits":"This technology could make ground testing associated with development and qualification of propulsion systems and ground operations associated with launch and access to space less expensive. This technology could make ground testing associated with development and qualification of propulsion systems and ground operations associated with launch and access to space less expensive. This technology could make ground testing associated with development and qualification of propulsion systems and ground operations associated with launch and access to space less expensive.","description":"In rocket test and launch facilities, cryogenic propellants stored in tanks boils off due to heat leakage, with the following impacts: Ø Waste, propellants boil off & requires replacement Ø Concentrates impurities which do not boil off Ø Imposes a thermal cycle on their finite service life Boil-off of is currently managed by purchasing more propellants; adaption of cryogenic-cooler technology will reduce heat buildup in the storage tanks thereby reducing boil-off, impurities and increasing life expectancy. In laboratory settings, cryogenic-coolers are used to minimize boil-off from dewars containing cryogens, however there is nothing available off-the-shelf that is designed for large cryogenic storage tanks located at present day launch and test facilities. The goal of this project is the development of a design concept that adapts scalable off-the-shelf cryogenic-cooler technology required for test and launch facility cryogenic-storage tanks, while optionally powering the system with off the grid electricity or solar energy in order to eliminate propellant boil-off. The development of this technology would save money spent on rocket engine testing at test facilities and on ground operations at launch facilities for propellant purchases, operations, maintenance, and problems associated with impurities in propellant stores, therefore enabling access to space by making it less expensive.","startYear":2014,"startMonth":11,"endYear":2015,"endMonth":10,"statusDescription":"Completed","principalInvestigators":[{"contactId":224773,"canUserEdit":false,"firstName":"Jody","lastName":"Woods","fullName":"Jody L Woods","fullNameInverted":"Woods, Jody L","middleInitial":"L","primaryEmail":"jwoods@relativityspace.com","publicEmail":false,"nacontact":false}],"programDirectors":[{"contactId":335305,"canUserEdit":false,"firstName":"Michael","lastName":"Lapointe","fullName":"Michael R Lapointe","fullNameInverted":"Lapointe, Michael R","middleInitial":"R","primaryEmail":"michael.r.lapointe@nasa.gov","publicEmail":true,"nacontact":false}],"programExecutives":[{"contactId":392233,"canUserEdit":false,"firstName":"Richard","lastName":"Howard","fullName":"Richard W Howard","fullNameInverted":"Howard, Richard W","middleInitial":"W","primaryEmail":"richard.w.howard@nasa.gov","publicEmail":true,"nacontact":false}],"programManagers":[{"contactId":382478,"canUserEdit":false,"firstName":"Ramona","lastName":"Travis","fullName":"Ramona E Travis","fullNameInverted":"Travis, Ramona E","middleInitial":"E","primaryEmail":"ramona.e.travis@nasa.gov","publicEmail":true,"nacontact":false}],"coInvestigators":[{"contactId":105154,"canUserEdit":false,"firstName":"David","lastName":"Coote","fullName":"David J Coote","fullNameInverted":"Coote, David J","middleInitial":"J","primaryEmail":"david.j.coote@nasa.gov","publicEmail":true,"nacontact":false}],"website":"https://www.nasa.gov/directorates/spacetech/home/index.html","libraryItems":[{"caption":"Technology Transfer Program Logo","file":{"fileExtension":"jpg","fileId":266597,"fileName":"OCTech","fileSize":6645,"objectId":266250,"objectType":{"lkuCodeId":889,"code":"LIBRARY_ITEMS","description":"Library Items","lkuCodeTypeId":182,"lkuCodeType":{"codeType":"OBJECT_TYPE","description":"Object Type"}},"objectTypeId":889,"fileSizeString":"6.5 KB"},"files":[{"fileExtension":"jpg","fileId":266597,"fileName":"OCTech","fileSize":6645,"objectId":266250,"objectType":{"lkuCodeId":889,"code":"LIBRARY_ITEMS","description":"Library Items","lkuCodeTypeId":182,"lkuCodeType":{"codeType":"OBJECT_TYPE","description":"Object Type"}},"objectTypeId":889,"fileSizeString":"6.5 KB"}],"id":266250,"title":"Large Propellant Tank Cryo-Cooler (LPTC)","description":"Technology Transfer Program Logo","libraryItemTypeId":1095,"projectId":32751,"primary":true,"publishedDateString":"","contentType":{"lkuCodeId":1095,"code":"IMAGE","description":"Image","lkuCodeTypeId":341,"lkuCodeType":{"codeType":"LIBRARY_ITEM_TYPE","description":"Library Item Type"}}}],"transitions":[{"transitionId":53484,"projectId":32751,"partner":"Other","transitionDate":"2014-11-01","path":"Advanced From","relatedProjectId":32416,"relatedProject":{"acronym":"","projectId":32416,"title":"High-Power Full-Scale Annular Plasma Engine Demonstration","startTrl":5,"currentTrl":6,"endTrl":6,"benefits":"This concept is also the most promising candidate to address the NASA Grand Challenge of Efficient In-Space Transportation over the next several decades. In the mid to far term, as defined in the In-Space Propulsion Systems Roadmap, Solar Electric Propulsion (SEP) provides the most credible approach to provide improved propulsion performance. This technology would benefit Earth- and Planetary Orbital applications including orbital transfers and orbital debris mitigation, and would benefit science missions in Earth Observatory, Cis-Lunar, and interplanetary, as well as cargo missions in support of human architectures. This technology has potential direct application to future commercial missions requiring Elecltic Propulsion for Low Earth Orbit, NASA's Meteoroid Environment Office (MEO) , and Group Earth Observations spacecraft platforms. This technology has potential direct application to future National Security Space missions.","description":"The performance, and development and infusion rates of in-space electric propulsion (EP) systems must be increased to increase mission operational capabilities. Today these systems are: unaffordable for many applications; and there is no EP technology that is scalable from 1600s to >4000s at power levels of interest. We believe these objectives can be achieved by developing the Next Generation Electric Propulsion Thruster (NGEPT); a GRC-patented modular EP device based on a new arrangement of relatively mature and proven technologies with the potential to yield revolutionary capabilities. The design basis for the NGEPT is the Annular Engine (AE). The AE delivers two revolutionary capabilities: It Enables Extensibility of Ion Technology to High Power at High Thrust Density It Creates a New Cost Paradigm for EP by Enabling a Reconfigurable Architecture","startYear":2014,"startMonth":11,"endYear":2015,"endMonth":10,"statusDescription":"Completed","website":"","program":{"acronym":"GRC CIF","active":true,"description":"
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