{"project":{"acronym":"","projectId":88502,"title":"Development of High-Fidelity Material Response Modeling for Resin-Infused Woven Thermal Protection Systems","primaryTaxonomyNodes":[{"taxonomyNodeId":10775,"taxonomyRootId":8816,"parentNodeId":10770,"level":3,"code":"TX09.4.5","title":"Modeling and Simulation for EDL","definition":"Modeling and simulation for EDL refers to the computer codes, underlying physical models, and processes that enable configuration definition and design verification and validation for systems that—short of a full scale flight test—cannot be tested exactly in the configuration and environment for which it is intended to operate. The models cover both the environmental response to the presence of the system in operation, and the operational performance of the system in the environment. A key concern is understanding and modeling of interactions between rocket plumes and the ground.","exampleTechnologies":"Multi-disciplinary coupled analysis tools, aerothermodynamics modeling, ablative material response models, non-ablative material response models, TPS quantification models and processes, numerical methodologies and techniques, autonomous aerobraking, orbital debris entry and breakup modeling, meteor entry and breakup modeling, Fluid Structure Interaction (FSI) tools, SRP modeling tools, aerodynamic modeling tools, plume-surface interaction, multi-scale simulation tools","hasChildren":false,"hasInteriorContent":true}],"startTrl":2,"currentTrl":3,"endTrl":3,"benefits":"The products of the proposed research will be pivotal in guiding the design and sizing of WTPS for future NASA missions and experiments. This will be critical in transforming NASA missions and advancing the Nation's capabilities by maturing crosscutting and innovative space technologies.","description":"For future space exploration missions, it is essential for the thermal protection system (TPS) found on hypersonic vehicles or atmospheric entry probes to be well-designed in order to ensure mission safety. TPS materials can be classified as either ablative (e.g., ablators such as the Phenolic Impregnated Carbon Ablator, or PICA, used on Stardust) or non-ablative (e.g., reusable materials such as ceramic tiles used on the Space Shuttle). The former class is typically used in extreme entry conditions and the latter in milder environments. The proposed work seeks to use computational modeling techniques to provide essential tools to assist in the design of ablative TPS. In particular, the proposed work plan intends to develop a high-fidelity modeling framework for the new promising family of ablators, woven TPS (WTPS), a class of TPS known for its diversity and flexibility in design. The proposed modeling is divided into two main components: (i) coupled computational fluid dynamics-surface chemistry modeling of the gas-surface interaction in the vicinity of the TPS surface with inclusion of finite rate surface chemistry effects, (ii) high-fidelity material response modeling of the WTPS material. Emphasis is placed on the latter as high-fidelity modeling of woven systems is unprecedented. Both a macroscopic and microscopic level of analysis is proposed to study the multiscale aspects of WTPS. The proposed work will target modeling of WTPS for the Adaptive Deployable Entry Placement Technology (ADEPT) system due to the availability of high-quality experimental results from progressive arc jet testing. This will allow for an excellent validation campaign for the model developed. The products of the proposed research will be pivotal in guiding the design and sizing of WTPS for future NASA missions and experiments. This will be critical in transforming NASA missions and advancing the Nation's capabilities by maturing crosscutting and innovative space technologies. The proposed modeling effort is aligned with the goals of NASA's Entry Systems Modeling project under the Space Technology Mission Directorate and is of highly relevant interest to the entry systems modeling group at the NASA ARC.","startYear":2016,"startMonth":9,"endYear":2020,"endMonth":12,"statusDescription":"Completed","principalInvestigators":[{"contactId":29802,"canUserEdit":false,"firstName":"Anthony","lastName":"Waas","fullName":"Anthony Waas","fullNameInverted":"Waas, Anthony","primaryEmail":"dcw@umich.edu","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":144091,"canUserEdit":false,"firstName":"Eric","lastName":"Stern","fullName":"Eric C Stern","fullNameInverted":"Stern, Eric C","middleInitial":"C","primaryEmail":"eric.c.stern@nasa.gov","publicEmail":true,"nacontact":false}],"coInvestigators":[{"contactId":113629,"canUserEdit":false,"firstName":"David","lastName":"Zhenzhong Dang","fullName":"David Zhenzhong Dang","fullNameInverted":"Zhenzhong Dang, David","publicEmail":false,"nacontact":false}],"website":"https://www.nasa.gov/strg#.VQb6T0jJzyE","libraryItems":[],"transitions":[{"transitionId":75901,"projectId":88502,"transitionDate":"2020-12-01","path":"Closed Out","details":"The primary objective of the research was to advance the predictive capability for modeling woven thermal protection systems (TPS), in particular, the Heatshield for Extreme Entry Environment Technology (HEEET), a dual-layer woven TPS developed at the NASA Ames Research Center. The accomplishments and results can be divided into three aspects. First, a constrained optimization approach was used to infer an orthotropic thermal conductivity model for HEEET. Specifically, the model provides thermal conductivity properties for HEEET in the 295 - 2000 K temperature range in all three orthogonal directions for both layers of the HEEET material. When using the inferred thermal conductivity model, higher fidelity simulations can be performed, producing results that are in much better agreement with experimental measurements. The model will continue to be used in future simulation efforts to guide the design of HEEET and TPS for space exploration missions. Second, the manufacturing process for HEEET has changed in recent years, which has led to observable changes in the stiffness properties. Again, a constrained optimization approach was applied to infer room temperature stiffness properties, as well as properties at elevated temperatures. The properties at elevated temperatures result in a stiffness reduction model that can be used in simulations involving combined thermal and mechanical effects, increasing the predictive capability of modeling HEEET in a multiphysics environment. The stiffness reduction model will be particularly useful in future simulation efforts to guide the design of HEEET and TPS for space exploration missions. Finally, a linear elasticity solver was developed to model the effects of mechanical loading on thermal protection systems. The linear elasticity solver was implemented within a thermal response solver in a coupled manner, allowing for modeling the simultaneous effects of thermal and mechanical loading on TPS. Specifically, the coupling allows for the computation of deformation due to increased temperature as well as applied mechanical loading. The coupled solver will continue to be used to guide design, research, and TPS developmental efforts for future space exploration missions. These unique research contributions will be very useful for guiding future design, research, and experimental efforts of HEEET and woven TPS. ","infoText":"Closed out","infoTextExtra":"","dateText":"December 2020"}],"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.
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