{"project":{"acronym":"","projectId":93456,"title":"Dynamic Flight Simulation Utilizing High Fidelity CFD-Based Nonlinear Reduced Order Model","primaryTaxonomyNodes":[{"taxonomyNodeId":10959,"taxonomyRootId":8816,"parentNodeId":10955,"level":3,"code":"TX15.2.4","title":"Modeling and Simulation for Flight","definition":"Modeling and simulation for flight supports the design, development, and implementation of vehicle flight dynamic simulations (simulation architecture, coordinate systems, equations of motion, etc.) and subsystem models (aerodynamic, aerothermal, propulsion, power, thermal, mass property, slosh, aero-servo-elastic structural, natural environment, geodesy, gravity, and uncertainty models) to enable accurate analysis and predictions of vehicle dynamics, trajectories, and performance.","exampleTechnologies":"Development of technologies that simulate the physics of flight vehicles, including GN&C, natural environment models, and vehicle subsystem (plant) models that affect vehicle performance and dynamics; development of visualizations of the flight vehicle to better communicate and determine operational performance; integration of visualization tools with trajectory design, reconstruction, and end-to-end mission design; math models of vehicle subsystems (aerodynamic, aerothermal, propulsion, power, thermal, mass property, slosh, aero-servo-elastic, structural, sensors, effectors, separation systems etc.) and environments (atmosphere, gravity, geodesy, etc.) that can be included as a software component in flight mechanics tools such as 6-DOF flight simulation; uncertainty modeling; simulation and trajectory visualization","hasChildren":false,"hasInteriorContent":true}],"startTrl":3,"currentTrl":8,"endTrl":8,"benefits":"A flight dynamics simulation capability with an add-on nonlinear aeroelastic solver using N-S solver generated ROMs is still not available within NASA. NASA has been working for many years towards achieving a software package that would accurately predict the interaction between flight dynamics considering structural flexibility in closed-loop with flight control laws. NASA is currently working on several N+3 advanced aircraft design concepts such as Truss-Braced Wing, Blended Wing-Body and Supersonic Business Jet. These advanced aircraft design concepts will be more flexible, more slender, and/or sizable where there may be insufficient frequency separation between the rigid body dynamics and the relatively low frequency elastic modes. The flight control law based on the rigid model may result in an unacceptable stability or an undesirable response characteristic due to control input or turbulence. The NL-DFS system will allow these advanced aircraft design concepts to be tested in a cost-effective manner; while increasing performance and confidence in the control law designs.
The maneuver and gust loads on transport aircraft usually are two of the critical design loads that dominate the structural design. To avoid the weight penalty by reducing the dynamic loads, modern commercial aircraft usually are equipped with a maneuver and gust load alleviation control system using the aileron and spoiler to provide the control authority. To suppress the body-freedom flutter and limit cycle oscillation problems, several military aircraft are equipped with a flutter suppression control system. To verify the performance of these control systems, it usually requires an enormous amount of wind-tunnel testing and flight testing to tune the control laws. The proposed NL-DFS system can be used as a virtual flight test environment in which control law testing can be performed; thereby reducing the number of wind tunnel and flight tests.","description":"The Nonlinear Dynamic Flight Simulation (NL-DFS) system will be developed in the Phase II project by combining the classical nonlinear rigid-body flight dynamics model with an add-on nonlinear aeroelastic solver to compute the airframe response due to pilot input command and to identify the key aeroelastic coupling mechanisms between the structural dynamics and unsteady aerodynamics with classic rigid-body dynamics. The nonlinear aeroelastic solver solves the aeroelastic equation of motion to add the incremental aeroelastic forces to the right hand side of the 6 degree-of-freedom equation in the flight dynamic model to account for the dynamic aeroelastic effects in the flight dynamic simulation. The generalized aerodynamic forces involved in the nonlinear aeroelastic solvers are provided by three nonlinear aerodynamic Reduced Order Models (ROMs); namely the modal, gust and control surface ROMs, that are derived from the Navier-Stokes (N-S) solver of FUN3D. The nonlinear modal ROM is constructed by a neural network model and the nonlinear gust and control surface ROMs are in the form of the first and second order Volterra Kernels. A wrapper around FUN3D, called OVERFUN, will be enhanced to drive FUN3D for generating the training data that leads to the three ROMs. OVERFUN also can directly drive FUN3D to perform a full order aeroelastic analysis including trim, flutter, gust and maneuver loads analyses whose solutions can be used to verify the accuracy of these three ROMs. The NL-DFS system will be validated with the flight test data of F/A-18 Active Aeroelastic Wing.","startYear":2017,"startMonth":4,"endYear":2019,"endMonth":4,"statusDescription":"Completed","principalInvestigators":[{"contactId":504772,"canUserEdit":false,"firstName":"Zhicun","lastName":"Wang","fullName":"Zhicun Wang","fullNameInverted":"Wang, Zhicun","primaryEmail":"Zhicun@Zonatech.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":3164223,"canUserEdit":false,"firstName":"Walter","lastName":"Silva","fullName":"Walter Silva","fullNameInverted":"Silva, Walter","primaryEmail":"Walter.A.Silva@nasa.gov","publicEmail":true,"nacontact":false},{"contactId":461333,"canUserEdit":false,"firstName":"Theresa","lastName":"Stanley","fullName":"Theresa M 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Model","startTrl":4,"currentTrl":5,"endTrl":5,"benefits":"A flight dynamics simulation capability with an added nonlinear aeroelastic solver is still unavailable. NASA has been working for many years towards achieving a software package that would accurately predict the interaction between flight dynamics considering airframe structural flexibility in closed-loop with flight control laws. The proposed NL-DFS is aimed at providing an expedient multidisciplinary nonlinear flight simulation tool to perform an efficient flaw debugging for advanced control laws as well as to promote a physical understanding of the in-flight observed dynamic behaviors due to evolutionary designs. It also will assist in the prediction of the instabilities onset prior to envelop expansion programs. NL-DFS will be especially valuable during NASA's current and next generation flying quantities and envelope expansion programs.
The capabilities developed in NL-DFS will strengthen ZONA's market position in the aerospace industry. NL-DFS will be marketed towards flight test applications on a wide class of aerospace vehicles such as: (a) USAF's F-22 and F-35 aircrafts at Edwards AFB; (b) UASF's long range supersonic strike bomber as well as stealth UAV/UCAV; (c) DARPA's advanced design concept; (d) Boeing 787; and (e) future executive jet designs of Cessna, Raytheon, etc. The proposed NL-DFS can also be applied to validate health management strategies specifically designed for aircraft designs with prominent aeroelastic characteristics.","description":"The overall technical objective of the Phase I effort is to develop a nonlinear aeroelastic solver utilizing the FUN3D generated nonlinear aerodynamic Reduced Order Model (ROM). Two types of aerodynamic reduced order models will be developed; the first is the Neural Network nonlinear ROM that can provide the aerodynamic feedback forces due to structural deformation and the second is a nonlinear Volterra-kernels-based gust ROM that provides the aerodynamic forces due to gust excitation. Once developed, this nonlinear aeroelastic solver will be integrated into the Nonlinear Dynamic Flight Simulation (NL-DFS) system in Phase II to perform flight dynamic simulation including nonlinear aeroelastic and nonlinear rigid body interaction effects, which can be used to predict the gust loads, ride quality, flight dynamic stability, and aero-structural control issues. In addition, the nonlinear aeroelastic solver developed can be a standalone code for rapid static/dynamic aeroelastic analysis. With the utilization of the FUN3D generated nonlinear aerodynamic (ROM), this nonlinear aeroelastic solver will be computational efficient for accurate flutter analysis, gust loads analysis and limit cycle oscillation analysis.","startYear":2016,"startMonth":6,"endYear":2016,"endMonth":12,"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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