{"project":{"acronym":"","projectId":93939,"title":"Multi-Fidelity Modeling and Simulation for the Analysis of Deployable Re-Entry Technologies Under Uncertainty","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 results from the reliability analysis will be useful to NASA for the decision making process during the mission design phase. It is expected that the methodologies developed under this research can also be used to benefit the development of any present or future spacecraft technology that may be considered by NASA.
","description":"The objective of the proposed research will be to identify and validate multi-fidelity modeling methods for the modeling and simulation of the flow field and thermal response of ADEPT and HIAD deployable re-entry technologies, and to implement these tools in the analysis and design of the two technologies under uncertainty. The proposed research will also compare the performance and reliability of ADEPT and the HIAD concepts for similar missions and corresponding re-entry trajectories subject to uncertainties in the operating (free-stream) conditions, geometry, and the physical modeling parameters. Due to the significant amount of aeroheating, re-entry system designs need to be robust and reliable. High-fidelity computational fluid dynamics and thermal response simulations can be computationally very expensive due to the complex physics seen at these flow regimes (turbulence modeling, non-equilibrium thermo-chemistry, radiation heat transfer, etc.) and may not be practical for direct use in the design and reliability assessment of re-entry technologies under uncertainty because of the large number of simulations required. The main idea behind multi-fidelity modeling is to combine a large number of data points from low and mid-fidelity models with a small number of data points from the high-fidelity models in a way that obtains a corrected model which maintains the accuracy of the high-fidelity model while reducing the computational cost. The key research components of the proposed project will include: (1) investigation of multi-fidelity approaches suitable for the problem, (2) integration of multi-fidelity modeling into an uncertainty quantification (UQ) framework, (3) comparison of the performance and reliability of HIAD and ADEPT configurations under uncertainty, and (4) investigation of multi-fidelity modeling for design optimization of deployable re-entry technologies under uncertainty. Component 1 includes an investigation into which low-, mid-, and high-fidelity computational tools should be used to create accurate multi-fidelity models for different output quantities of interest such as the surface pressure, shear, convective, and radiation heat flux. This component will also involve an investigation into the different types of multi-fidelity analysis including co-Kriging, polynomial chaos expansion, and support vector analysis. In component 2, the multi-fidelity modeling techniques will be integrated into a UQ framework in order to perform reliability analyses of ADEPT and HIAD configurations. In component 3, with multi-fidelity analysis and the UQ framework, a comparison of the performance and reliability of HIAD and ADEPT configurations will be done. The comparison will be made for similar missions subject to uncertainties in the operating conditions, geometry, and the physical modeling parameters in flow field and thermal response simulations. Finally, in component 4, an investigation into the use of multi-fidelity modeling for the design optimization of ADEPT or HIAD technologies under uncertainty will be performed. The multi-fidelity modeling approach will allow computationally efficient and accurate design of deployable re-entry technologies under uncertainty. The proposed research will focus on reducing computational cost while maintaining a high accuracy in modeling and simulation of robust and reliable re-entry technologies with the consideration of uncertainty in the design process, and seek to demonstrate the use of multi-fidelity modeling for this purpose. The project will include strong collaboration with researchers from NASA Langley and ARCs. The results from the reliability analysis will be useful to NASA for the decision making process during the mission design phase. It is expected that the methodologies developed under this research can also be used to benefit the development of any present or future spacecraft technology that may be considered by NASA.
","startYear":2017,"startMonth":8,"endYear":2021,"endMonth":7,"statusDescription":"Completed","principalInvestigators":[{"contactId":430738,"canUserEdit":false,"firstName":"Serhat","lastName":"Hosder","fullName":"Serhat Hosder","fullNameInverted":"Hosder, Serhat","primaryEmail":"hosders@mst.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":466725,"canUserEdit":false,"firstName":"Thomas","lastName":"West","fullName":"Thomas K West","fullNameInverted":"West, Thomas K","middleInitial":"K","primaryEmail":"thomas.k.west@nasa.gov","publicEmail":true,"nacontact":false}],"coInvestigators":[{"contactId":309661,"canUserEdit":false,"firstName":"Mario","lastName":"Santos","fullName":"Mario J Santos","fullNameInverted":"Santos, Mario J","middleInitial":"J","primaryEmail":"mario.santos@nasa.gov","publicEmail":true,"nacontact":false}],"website":"","libraryItems":[],"transitions":[{"transitionId":75334,"projectId":93939,"transitionDate":"2021-07-01","path":"Closed Out","details":"The primary objective this research project is the identification and validation of multi-fidelity modeling techniques for accurate, computationally efficient modeling and simulation of hypersonic flows, aerodynamic heating and thermal response of deployable re-entry technologies, specifically the Hypersonic Inflatable Aerodynamic Decelerator (HIAD) and the Adaptable, Deployable Entry Placement Technology (ADEPT). To increase capability of human and robotic exploration of the solar system, new cutting-edge technologies need to be developed. One of these cutting-edge technologies being developed that will allow for greater flexibility in landing site location and payload size are deployable re-entry technologies. However, these deployable re-entry technologies are still very much in the design and development phase, and timely and accurate uncertainty quantification (UQ) of the thermal and flow field response of these deployable configurations are essential for risk assessment, improving robustness and reliability, and eventually mission certification of these technologies. Previously, high fidelity surrogate models have been used to reduce computational costs of UQ analysis of deployable re-entry technologies, specifically the HIAD technology of NASA Langley. However, multi-fidelity model surrogates have the potential to reduce computational costs below that of high-fidelity surrogate models while retaining the high-fidelity accuracy level. In this project, several computational tools and multi-fidelity modeling methods were investigated and the most efficient approach for multi-fidelity modeling of the thermal and flow field response of deployable entry vehicle configurations was identified. The project found that using a co-Kriging based multi-fidelity approach with Hicks-Henne surface response parameterization resulted in accurate and efficient models of the laminar aerothermal loads on large diameter deployable entry vehicles and that these multi-fidelity models outperformed single fidelity methods in terms of cost and accuracy. Using a combination of high-fidelity LAURA CFD simulations along with low-fidelity surface methods (e.g. Sutton-Graves equation, modified Newtonian method) resulted in the most efficient multi-fidelity models while maintaining a high level of accuracy. The developed co-Kriging based multi-fidelity methodology was applied to modeling axisymmetric convective and radiative heat flux distributions on HIAD vehicles with surface scalloping in Mars atmospheric entry under both laminar and turbulent flow. For scalloped HIAD vehicles in Mars entry, it was found that the co-Kriging based multi-fidelity modeling approach resulted in heat flux models that had a mean error of 10% and a five order of magnitude computational cost reduction when compared to high-fidelity CFD simulations. The developed co-Kriging based multi-fidelity approach was then adjusted to model two-dimensional aerothermal response distributions. This adjusted approach was then used to model the two-dimensional convective and radiative heat flux distributions on ADEPT vehicles in Mars atmospheric entry under both laminar and turbulent flow. For ADEPT vehicles in Mars entry, it was also found that the co-Kriging based multi-fidelity modeling approach resulted in heat flux models that had a mean error of 10% and a six order of magnitude computational cost reduction when compared to high-fidelity CFD simulations. It was determined that the developed multi-fidelity approach for modeling the aerothermal response on deployable entry vehicles resulted in significant computational cost savings while maintaining a high level of accuracy and that the developed approach can be applied to a range of hypersonic vehicles (rigid entry systems, mid-L/D entry systems, etc.).
","infoText":"Closed out","infoTextExtra":"","dateText":"July 2021"}],"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.
","programId":69,"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"},"responsibleMdId":4875,"stockImageFileId":36658,"title":"Space Technology Research Grants"},"leadOrganization":{"canUserEdit":false,"city":"Rolla","country":{"abbreviation":"US","countryId":236,"name":"United States"},"countryId":236,"external":true,"linkCount":0,"organizationId":2877,"organizationName":"Missouri University of Science and Technology","organizationType":"Academia","stateTerritory":{"abbreviation":"MO","country":{"abbreviation":"US","countryId":236,"name":"United States"},"countryId":236,"name":"Missouri","stateTerritoryId":38},"stateTerritoryId":38,"murepUnitId":178411,"naorganization":false,"organizationTypePretty":"Academia"},"supportingOrganizations":[{"acronym":"LaRC","canUserEdit":false,"city":"Hampton","country":{"abbreviation":"US","countryId":236,"name":"United States"},"countryId":236,"external":false,"linkCount":0,"organizationId":4852,"organizationName":"Langley Research Center","organizationType":"NASA_Center","stateTerritory":{"abbreviation":"VA","country":{"abbreviation":"US","countryId":236,"name":"United States"},"countryId":236,"name":"Virginia","stateTerritoryId":7},"stateTerritoryId":7,"naorganization":false,"organizationTypePretty":"NASA Center"}],"statesWithWork":[{"abbreviation":"MO","country":{"abbreviation":"US","countryId":236,"name":"United States"},"countryId":236,"name":"Missouri","stateTerritoryId":38}],"lastUpdated":"2024-2-6","releaseStatusString":"Released","viewCount":674,"endDateString":"Jul 2021","startDateString":"Aug 2017"}}