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检索条件"机构=Multiscale and Multiphysics Modeling Branch"

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Comparison of multiscale method of cells-based models for predicting elastic properties of filament wound C/C-SiC 32

Comparison of multiscale method of cells-based models for pr...

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32nd Technical Conference of the American Society for Composites 2017

作者： Pineda, Evan J. Fassin, Marek Bednarcyk, Brett A. Reese, Stefanie Simon, Jaan-Willem Multiscale and Multiphysics Modeling Branch NASA Glenn Research Center 21000 Brookpark Road MS 49/7 ClevelandOH44113 United States Institute of Applied Mechanics RWTH Aachen University Mies-van-der-Rohe-Str. 1 Aachen52074 Germany

ISBN: (纸本)9781510853065

Three different multiscale models, based on the method of cells (generalized and high fidelity) micromechanics models were developed and used to predict the elastic properties of C/C-SiC composites. In particular, the following multiscale modeling strategies were employed: Concurrent multiscale modeling of all phases using the generalized method of cells, synergistic (two-way coupling in space) multiscale modeling with the generalized method of cells, and hierarchical (one-way coupling in space) multiscale modeling with the high fidelity generalized method of cells. The three models are validated against data from a hierarchical multiscale finite element model in the literature for a repeating unit cell of C/C-SiC. Furthermore, the multiscale models are used in conjunction with classical lamination theory to predict the stiffness of C/C-SiC plates manufactured via a wet filament winding and liquid silicon infiltration process recently developed by the German Aerospace Institute. Copyright © (2017) by DEStech Publications, Inc. All rights reserved.

关键词： Filament winding

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Order-reduced solution of the nonlinear high-fidelity generalized method of cells micromechanics relations 32

Order-reduced solution of the nonlinear high-fidelity genera...

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32nd Technical Conference of the American Society for Composites 2017

作者： Ricks, Trenton M. Lacy, Thomas E. Pineda, Evan J. Bednarcyk, Brett A. Arnold, Steven M. Department of Aerospace Engineering Mississippi State University PO Box A Mississippi StateMS39762 United States Multiscale and Multiphysics Modeling Branch Materials and Structures Division NASA Glenn Research Center 21000 Brookpark Rd. MS 49-7 ClevelandOH44135 United States

ISBN: (纸本)9781510853065

The High-Fidelity Generalized Method of Cells (HFGMC) is one technique for accurately simulating nonlinear composite material behavior. The HFGMC uses a higher-order approximation for the subcell displacement field that allows for a more accurate determination of the subcell stress/strain fields at the cost of some computational efficiency. In order to reduce computational costs associated with the solution of the ensuing system of simultaneous equations, the HFGMC global system of equations for doubly-periodic repeating unit cells with nonlinear constituents was reduced in size through the use of a Petrov-Galerkin-based Proper Orthogonal Decomposition order-reduction scheme. A number of cases were presented that address the computational feasibility of using order-reduction techniques to solve solid mechanics problems involving complex microstructures. Copyright © (2017) by DEStech Publications, Inc. All rights reserved.

关键词： Computational efficiency

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A thermodynamically based work potential theory for predicting progressive damage and failure in 3D textile composites 17

A thermodynamically based work potential theory for predicti...

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17th European Conference on Composite Materials, ECCM 2016

作者： Huang, H. Sam Pineda, Evan J. Department of Mechanical Engineering State University of New York Stony BrookNY United States Multiscale and Multiphysics Modeling Branch NASA Glenn Research Center ClevelandOH United States

ISBN: (纸本)9783000533877

In this paper, a 3D thermodynamically-based work potential theory for modeling progressive damage for laminated, unidirectional composites,extend from 2D Schapery's theory, is used to predict the response of unidirectional composites under three point bending. An internal state variable, S, is defined to account for the dissipated energy due to damage evolution in the form of microstructural changes in the matrix. With the stationary of the total work potential with respect to the internal state variable, a thermodynamically-consistent set of evolution equations is derived. The internal state variable is related to the transverse and shear moduli through microdamage functions. The shear modulus and transverse modulus expressed as a function of internal state variable are obtained from coupon tests. The shear modulus and transverse modulus expressed as a function of internal state variable are implemented into 3D Schaperys theory to predict unidirectional composites under three point bending. The comparison of show good agreement between simulations and experiments under three point bending. © 2016, European Conference on Composite Materials, ECCM. All rights reserved.

关键词： Elastic moduli

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Experimental evaluation of an embedded boundary layer ingesting propulsor for highly efficient subsonic cruise aircraft 53

Experimental evaluation of an embedded boundary layer ingest...

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53rd AIAA/SAE/ASEE Joint Propulsion Conference, 2017

作者： Arend, David J. Wolter, John D. Hirt, Stefanie M. Provenza, Andrew J. Gazzaniga, John A. Cousins, William T. Hardin, Larry W. Sharma, Om P. NASA Glenn Research Center at Lewis Field Inlets and Nozzles Branch 21000 Brookpark Rd M.S. 5-12 ClevelandOH44135 United States United Technologies Research Center East HartfordCT06108 United States Multiscale and Multiphysics Modeling Branch 21000 Brookpark Rd M.S. 49-8 United States Acoustics Branch 21000 Brookpark Rd M.S. 49-8 United States Thermal and Fluid Sciences 411 Silver Lane United States Aerodynamics 411 Silver Lane United States Aerodynamics and Gas Turbines 411 Silver Lane United States

ISBN: (数字)9781624105111

ISBN: (纸本)9781624105111

Experimental tests have been completed of the performance and operability of a 0.289 scale Boundary Layer Ingesting (BLI) propulsor within the transonic test section of NASA's 8ft x6ft Supersonic Wind Tunnel (SWT). Utilizing its new 6.5ft x 6ft embedded propulsor testbed configuration, trials were completed of a multi-displinary, designed-integrated propulsor in a simulated upper aft Hybrid Wing Body (HWB) aircraft installation. This propulsor consisted of a Length-to-Diameter (L/D) ratio 0.66 inlet coupled with a 22 inch diameter, 1.34 Fan Stage Pressure Ratio (FSPR), 16 Bypass Ratio (BPR) distortion-tolerant turbofan stage. Data were acquired at the embedded propulsor's Mach 0.78 inflow Aerodynamic Design Point (ADP) operating conditions where it achieved a mass flow weighted inlet total pressure recovery and an adiabatic fan stage efficiency of 96.5% and 87.9%, respectively. This propulsor demonstrated a constant 100% corrected speed stability margin of approximately 12%. Tests were also conducted across the extents of its fan map from 70% through 105% corrected speed and from near choke operating conditions through its stability limit. These tests revealed that the propulsor's operation was generally well-behaved. Both steady state and high response inlet airflow distortion were measured in accordance with the Society of Automotive Engineers' (SAE) Aerospace Recommended Practice 1420. Application of Reynolds number scaling to the wind tunnel test results indicates that a full-scale aircraft equivalent fuel burn reduction of approximately 3.6% was achieved relative to the same aircraft and engine featuring a modern conventional fan in a strut mounted installation.

关键词： Boundary layers

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Information management workflow and tools enabling multiscale modeling within ICME paradigm 57

Information management workflow and tools enabling multiscal...

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57th AIAA/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference, 2016

作者： Arnold, Steven M. Bednarcyk, Brett A. Austin, Nic Terentjev, Igor Cebon, Dave Marsden, Will Multiscale Modeling Structures and Materials Division NASA Glenn Research Center 21000 Brookpark Road ClevelandOH44135 United States Multiscale Modeling and Multiphysics Branch NASA Glenn Research Center 21000 Brookpark Road ClevelandOH44135 United States Software Division Granta Design Ltd. Rustat House 62 Clifton Road CambridgeCB1 7EG United Kingdom Granta Design Ltd. Rustat House 62 Clifton Road CambridgeCB1 7EG United Kingdom

ISBN: (数字)9781624103926

ISBN: (纸本)9781624103926

With the increased emphasis on reducing the cost and time to market of new materials, the need for analytical tools that enable the virtual design and optimization of materials throughout their processing - internal structure - property - performance envelope, along with the capturing and storing of the associated material and model information across its lifecycle, has become critical. This need is also fueled by the demands for higher efficiency in material testing;consistency, quality and traceability of data;product design;engineering analysis;as well as control of access to proprietary or sensitive information. Fortunately, material information management systems and physics-based multiscale modeling methods have kept pace with the growing user demands. Herein, recent efforts to establish workflow for and demonstrate a unique set of web application tools for linking NASA GRC’s Integrated Computational Materials Engineering (ICME) Granta MI® database schema and NASA GRC’s Integrated multiscale Micromechanics Analysis Code (ImMAC) software toolset are presented. The goal is to enable seamless coupling between both test data and simulation data, which is captured and tracked automatically within Granta MI®, with full model pedigree information. These tools, and this type of linkage, are foundational to realizing the full potential of ICME, in which materials processing, microstructure, properties, and performance are coupled to enable application-driven design and optimization of materials and structures. © 2016, American Institute of Aeronautics and Astronautics Inc, AIAA. All rights reserved.

关键词： Product design

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Overcoming the adoption barrier to electric flight 54

Overcoming the adoption barrier to electric flight

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54th AIAA Aerospace Sciences Meeting, 2016

作者： Borer, Nicholas K. Nickol, Craig L. Jones, Frank P. Yasky, Richard J. Woodham, Kurt Fell, Jared S. Litherland, Brandon L. Loyselle, Patricia L. Provenza, Andrew J. Kohlman, Lee W. Samuel, Aamod G. NASA Langley Research Center HamptonVA23681 United States NASA Glenn Research Center ClevelandOH44135 United States NASA Armstrong Flight Research Center EdwardsCA93523 United States Aeronautics Systems Analysis Branch MS 442 United States Operations and Engineering Branch MS 255A United States Safety Critical Avionics Branch MS 130 United States Aeronautics Systems Engineering Branch MS 238 United States Photovoltaic and Electrochemical Systems Branch MS 309-1 United States Multiscale and Multiphysics Modeling Branch MS 49-8 United States Rotating and Drive Systems Branch MS 49-8 United States

ISBN: (数字)9781624103933

ISBN: (纸本)9781624103933

Electrically-powered aircraft may enable dramatic increases in efficiency and reliability, reduced emissions, and reduced noise as compared to today’s combustion-powered aircraft. This paper describes a novel flight demonstration concept that will enable the benefits of electric propulsion, while keeping the convenience and utility of common fuels available at today’s airports. A critical gap in airborne electric propulsion research is addressed by accommodating adoption at the integrated aircraft-airport systems level, using a confluence of innovative but proven concepts and technologies in power generation and electricity storage that need to reside only on the airframe. Technical discriminators of this demonstrator include (1) a novel, high-efficiency power system that utilizes advanced solid oxide fuel cells originally developed for ultra-long-endurance aircraft, coupled with (2) a high-efficiency, high-power electric propulsion system selected from mature products to reduce technical risk, assembled into (3) a modern, high-performance demonstration platform to provide useful and compelling data, both for the targeted early adopters and the eventual commercial market. The proposed demonstrator concepts all meet or exceed the program goal of a 50% reduction in mission fuel cost compared to the unmodified aircraft. © 2016, American Institute of Aeronautics and Astronautics Inc, AIAA. All Rights Reserved.

关键词： Electric propulsion

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Forced response analysis of a fan with boundary layer inlet distortion 50

Forced response analysis of a fan with boundary layer inlet ...

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50th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and exhibit 2014

作者： Bakhle, Milind A. Reddy, T.S.R. Coroneos, Rula M. NASA Glenn Research Center Multiscale and Multiphysics Modeling Branch ClevelandOH44135 United States University of Toledo Multiscale and Multiphysics Modeling Branch ToledoOH43606 United States

ISBN: (数字)9781624103032

ISBN: (纸本)9781624103032

Boundary layer ingesting propulsion systems have the potential to significantly reduce fuel burn for future generations of commercial aircraft, but these systems must be designed to overcome the challenge of high dynamic stresses in fan blades due to forced response. High dynamic stresses can lead to high cycle fatigue failures. High-fidelity computational analysis of the fan aeromechanics is integral to an ongoing effort to design a boundary layer ingesting inlet and fan for a wind-tunnel test. An unsteady flow solution from a Reynoldsaveraged Navier Stokes analysis of a coupled inlet-fan system is used to calculate blade unsteady loading and assess forced response of the fan to distorted inflow. Conducted prior to the mechanical design of a fan, the initial forced response analyses performed in this study provide an early look at the levels of dynamic stresses that are likely to be encountered. For the boundary layer ingesting inlet, the distortion contains strong engine order excitations that act simultaneously. The combined effect of these harmonics was considered in the calculation of the forced response stresses. Together, static and dynamic stresses can provide the information necessary to evaluate whether the blades are likely to fail due to high cycle fatigue. Based on the analyses done, the overspeed condition is likely to result in the smallest stress margin in terms of the mean and alternating stresses. Additional work is ongoing to expand the analyses to off-design conditions, on-resonance conditions, and to include more detailed modeling of the blade structure.

关键词： Boundary layers

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Assessing fan flutter stability in presence of inlet distortion using One-Way and Two-Way coupled methods 50

Assessing fan flutter stability in presence of inlet distort...

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50th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and exhibit 2014

作者： Herrick, Gregory P. NASA Glenn Research Center LMS/Multiscale and Multiphysics Modeling Branch ClevelandOH44135 United States

ISBN: (数字)9781624103032

ISBN: (纸本)9781624103032

Concerns regarding noise, propulsive efficiency, and fuel burn are inspiring aircraft designs wherein the propulsive turbomachines are partially (or fully) embedded within the airframe;such designs present serious concerns with regard to aerodynamic and aeromechanic performance of the compression system in response to inlet distortion. Previously, a preliminary design of a forward-swept high-speed fan exhibited flutter concerns in clean-inlet flows, and the present author then studied this fan further in the presence of off-design distorted in-flows. Continuing this research, a three-dimensional, unsteady, Navier-Stokes computational fluid dynamics code is again applied to analyze and corroborate fan performance with clean inlet flow and now with a simplified, sinusoidal distortion of total pressure at the aerodynamic interface plane. This code, already validated in its application to assess aerodynamic damping of vibrating blades at various flow conditions using a one-way coupled energy-exchange approach, is modified to include a two-way coupled time-marching aeroelastic simulation capability. The two coupling methods are compared in their evaluation of flutter stability in the presence of distorted in-flows.

关键词： Navier Stokes equations

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Computationally efficient solution of the High-Fidelity Generalized Method of cells micromechanics relations 30

Computationally efficient solution of the High-Fidelity Gene...

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30th Annual Technical Conference of the American Society for Composites, ASC 2015

作者： Ricks, T.M. Lacy, T.E. Pineda, E.J. Bednarcyk, B.A. Arnold, S.M. Department of Aerospace Engineering Mississippi State University PO Box A Mississippi StateMS39762 United States Mechanics and Life Prediction Branch NASA Glenn Research Center 21000 Brookpark Rd. MS 49-7 ClevelandOH44135 United States Multiscale Multiphysics Modeling Materials and Structures Division NASA Glenn Research Center 21000 Brookpark Rd. MS 49-7 ClevelandOH44135 United States

ISBN: (纸本)9781605952253

The High-Fidelity Generalized Method of Cells (HFGMC) is a powerful technique for simulating composite materials and is based on Aboudi's method of cells micromechanics theories. Unlike the original generalized method of cells, the HFGMC uses a higher order approximation for the subcell displacement field. Although this allows for a more accurate determination of the subcell stress/strain fields, the solution to the simultaneous set of equations can become computationally burdensome. In order to overcome expensive computational costs associated with solving large systems of equations, order-reduction techniques have been developed to approximate the solution with an acceptable error. These techniques are widely used in the computational fluid dynamics community and are increasingly being implemented for solving solid mechanics problems involving the finite element method. In this study, the HFGMC global system of equations for doubly-periodic RUCs was reduced in size through the use of Proper Orthogonal Decomposition (POD) with Galerkin projection. Order-reduced models were then implemented within an ABAQUS UMAT and used to perform multiscale analyses. A number of cases were presented that show the computational feasibility of using order-reduction techniques to solve the HFGMC set of simultaneous equations. By simulating composite materials in a more computationally efficient manner, a pathway forward is presented for performing multiscale analyses of composite structures consistent with the Airframe Digital Twin concept. Copyright © 2015 by DEStech Publications, Inc. and American Society for Composites. All rights reserved.

关键词： Composite materials

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Technique for mapping characteristic lengths to preserve energy dissipated via strain softening in a multiscale analysis 29

Technique for mapping characteristic lengths to preserve ene...

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29th Annual Technical Conference of the American Society for Composites, ASC 2014;16th US-Japan Conference on Composite Materials;ASTM-D30 Meeting

作者： Pineda, E.J. Bednarcyk, B.A. Arnold, S.M. Multiscale and Multiphysics Modeling Branch NASA Glenn Research Center 21000 Brookpark Rd ClevelandOH United States

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