{"project":{"acronym":"","projectId":94776,"title":"Toxicity Mitigating Single-Fluid Cooling System for Manned Spacecraft","primaryTaxonomyNodes":[{"taxonomyNodeId":10932,"taxonomyRootId":8816,"parentNodeId":10929,"level":3,"code":"TX14.2.3","title":"Heat Rejection and Storage","definition":"This area includes technologies to more effectively reject heat on a flight. Technologies are needed to make these methods more reliable and standardized and increase the capability for effective ground testing. This area includes technologies that manage system heat primarily through the use of the thermal and/or optical properties of a given material. This area includes in-space and ground applications.","exampleTechnologies":"Radiators, radiator turn-down devices (e.g. louvers, heat switches, variable conductance heat pipes), phase change materials, transpiration cooling, heat sinks, optical coatings, variable coatings, sunshades, molten salts, cryogens, evaporation, boiling, condensation, autonomous radiator maintenance, dust tolerant radiators, high heat load 500 - 500 kW rejection","hasChildren":false,"hasInteriorContent":true}],"startTrl":1,"currentTrl":3,"endTrl":3,"benefits":"NASA applications for the proposed toxicity mitigating thermal control system include future Orion-like manned missions and Deep Space Gateway and Transport missions. Any manned space vehicle would benefit from the expected weight and crew safety advantage offered by the innovative thermal control system proposed.
Non-NASA applications for the proposed technology include any manned space vehicle launch for exploration or tourism purposes. The European Space Agency has an aggressive interest in a moon landing in the near future. Additionally, non-government commercial entities such as Space-X, Blue Origin, Bigelow Aerospace, and others include space tourism as a future goal.","description":"The thermal control systems (TCS) for manned spacecraft are typically two-loop designs where a low freezing point single-phase liquid is used exterior to the manned vessel to reject heat through the radiator array, and a single-phase thermal loop inside the manned vessel that uses a non-toxic liquid is used for payload cooling and space conditioning. As an example, the Orion TCS uses HFE-7200 liquid (-138°C pour point) in the radiators, and PGW in the manned cabin. These loops interface through a shared heat exchanger that is external to the manned vessel to ensure that the working fluid for the external loop cannot leak into the manned cabin. This architecture is necessary for crew safety (most very low freezing point fluids are somewhat toxic or untested) but comes with a mass penalty due to the duplicity of prime movers (pumps), mass of the intermediate heat exchanger, and extra radiator surface area to account for the additional temperature delta required for the intermediate heat exchange process. The two-loop mass penalty is a driving force toward reducing the TCS to a single working fluid. However, the toxicity risk must be mitigated for this architecture to be realized. Mainstream proposes to replace the two loop TCS architecture with a single loop TCS architecture that has toxicity mitigating technology.","startYear":2018,"startMonth":7,"endYear":2019,"endMonth":2,"statusDescription":"Completed","principalInvestigators":[{"contactId":506854,"canUserEdit":false,"firstName":"David","lastName":"Sykes","fullName":"David Sykes","fullNameInverted":"Sykes, David","primaryEmail":"dsykes@mainstream-engr.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 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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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