{"project":{"acronym":"","projectId":93658,"title":"Multiphase Modeling of Solid Rocket Motor Internal Environment","primaryTaxonomyNodes":[{"taxonomyNodeId":10537,"taxonomyRootId":8816,"parentNodeId":10533,"level":3,"code":"TX01.1.4","title":"Solids","definition":"This area covers propulsion systems that operate with solid propellants, where the propellants are pre-mixed oxidizers and fuels.","exampleTechnologies":"Polybutadiene Acrylic Acid Acrylonitrile Prepolymer (PBAN), Hydroxyl Terminated Poly Butadiene (HTPB)","hasChildren":false,"hasInteriorContent":true}],"startTrl":2,"currentTrl":3,"endTrl":3,"benefits":"The proposed physics-based multiphase model for the SRM environment will find a multitude of applications at NASA and for DoD and industry customers. The applications include: (1) Accurate modeling of slag accumulation during the operating of an SRM, (2) Quantitative analysis of the effect of slag accumulation on propellant conversion efficiency (3) Analysis of sloshing and the potential effects on SRM conning, (4) Assessment of slag as a potential debris hazard, and (5) Assessment of new concepts for SRM design and trade studies. At the end of Phase II, a well-validated suite of tools will be available to NASA and its government contractors to better understand SRM combustion and dynamics in large-scale solid rocket motors.
Companies such as Aerojet-Rocketdyne and Lockheed Martin can benefit from the advanced SRM modeling capabilities in the same way NASA can. The potential of understanding slag accumulation/dynamics in SRM can aid in designing high performance-cost ratio systems. In addition, the proposed slag model will have the capability to account for slag after SRM burnout, time at which slag poses as a potential hazard. This is of particular interest to the Missile Defense Agency (MDA). The transport of slag during operation of the SRM and after burnout are of critical importance to MDA to understand the radiation signature of the plume at burnout. The developed tools will be directly apply to these applications.","description":"Solid rocket motor (SRM) design requires thorough understanding of the slag accumulation process in order to: predict thrust continuity, optimize propellant conversion efficiency, predict coning effects from sloshing, and assess potential orbital debris (slag) hazard. Current state-of-the-art models for SRM environment do not have the capability to simulate the accumulation and dynamics of slag in SRMs as they rely on a Lagrangian particle approach that is only capable of predicting the location of accumulation. In this STTR effort, CFDRC will team up with Mississippi State University and Tetra Research to develop models for quantifying the effects of slag accumulation and dynamics on SRM performance. To enhance current slag modeling capabilities, an Eulerian-Lagrangian approach to accurately model a slag-phase is proposed, in which Lagrangian particles can be converted to an Eulerian description and vice-versa. The Phase I project aims at developing the basic numerical model for the transport and accumulation of a slag-phase in Loci/CHEM. The multiphase framework, comprising of gas-phase, a dense slag-phase, and Lagrangian particles representing aluminum and alumina, will be developed and demonstrated in the Phase I effort with a TRL starting at 2 and ending at 3. In Phase II, the models will be extended and validated to provide an accurate numerical approach for slag dynamics that incorporates many of the physical phenomena present during SRM operation, including the transfer from Eulerian to Lagrangian description of slag at burnout, increasing the technology readiness level by the end of a Phase II project from 3 to 5.","startYear":2017,"startMonth":6,"endYear":2018,"endMonth":6,"statusDescription":"Completed","principalInvestigators":[{"contactId":303928,"canUserEdit":false,"firstName":"Manuel","lastName":"Gale","fullName":"Manuel Gale","fullNameInverted":"Gale, Manuel","primaryEmail":"manuel.gale@cfdrc.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":53359,"canUserEdit":false,"firstName":"Brian","lastName":"Richardson","fullName":"Brian R Richardson","fullNameInverted":"Richardson, Brian R","middleInitial":"R","primaryEmail":"brian.r.richardson@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":294322,"fileName":"briefchart","fileSize":5722439,"objectId":290843,"objectType":{"lkuCodeId":889,"code":"LIBRARY_ITEMS","description":"Library Items","lkuCodeTypeId":182,"lkuCodeType":{"codeType":"OBJECT_TYPE","description":"Object Type"}},"objectTypeId":889,"fileSizeString":"5.5 MB"},"files":[{"fileExtension":"pdf","fileId":294322,"fileName":"briefchart","fileSize":5722439,"objectId":290843,"objectType":{"lkuCodeId":889,"code":"LIBRARY_ITEMS","description":"Library Items","lkuCodeTypeId":182,"lkuCodeType":{"codeType":"OBJECT_TYPE","description":"Object 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Chart","file":{"fileExtension":"pdf","fileId":308022,"fileName":"finalSummaryChart","fileSize":159614,"objectId":69590,"objectType":{"lkuCodeId":1841,"code":"TRANSITION_FILES","description":"Transition Files","lkuCodeTypeId":182,"lkuCodeType":{"codeType":"OBJECT_TYPE","description":"Object Type"}},"fileSizeString":"155.9 KB"},"transitionId":69590,"fileId":308022}],"infoText":"Closed out","infoTextExtra":"","dateText":"June 2018"},{"transitionId":69589,"projectId":93658,"partner":"Other","transitionDate":"2018-09-01","path":"Advanced To","relatedProjectId":95012,"relatedProject":{"acronym":"","projectId":95012,"title":"Multiphase Modeling of Solid Rocket Motor Internal Environment","startTrl":3,"currentTrl":5,"endTrl":5,"benefits":"Prediction of slag accumulation during SRM operation, Analysis of slag accumulation effects on propellant conversion efficiency, Prediction of sloshing and the potential effects on SRM conning, Assessment of slag as a potential debris hazard, Support new SRM concept and trade studies analysis
Military application: Prediction of SRM burnout and time at which slag poses as a potential hazard; prediction of thermal signatures associated with slag for both tactical and missile defense. Civilian Applications: Analysis of volcano eruptions and dispersion of hazardous lava; slosh predictions for ships and civil transport applications.","description":"Solid rocket motor (SRM) design requires detailed understanding of the slag accumulation process in order to: predict thrust continuity, optimize propellant conversion efficiency, predict coning effects from sloshing, and to assess potential orbital debris (slag) hazard. Current state-of-the-art models for SRM environment do not have the capability to simulate the accumulation and dynamics of slag in SRMs as they rely on a Lagrangian particle approach that are only capable of predicting the location of accumulation. In Phase I, a multiphase framework comprising of gas-phase, a dense slag-phase, and Lagrangian particles representing aluminum and alumina was developed and demonstrated. Phase II effort will focus on extending the developed approach by a) incorporating improved transport and thermal properties of slag, b) improving numerical approach for solving transport of gas and slag-phase in SRM environment, c) enhancing the coupled flow simulation capabilities including accelerated frame of reference to predict slag dynamics and d) providing detailed verification and validation of sub-models and overall simulation capabilities. The tools developed will be of great use in designing and developing next generation SRMs and effect of slag on thrust oscillations, coning and debris prediction.","startYear":2018,"startMonth":9,"endYear":2020,"endMonth":9,"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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