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检索条件"机构=Center for Computer Applications in AeroSpace Science and Engineering"

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Aerodynamic shape optimization of supersonic aircraft configurations via an adjoint formulation on distributed memory parallel computers 6th

Aerodynamic shape optimization of supersonic aircraft config...

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6th AIAA/NASA/ISSMO Symposium on Multidisciplinary Analysis and Optimization, 1996

作者： Reuther, J. Alonso, J.J. Rimlinger, M.J. Jameson, A. Research Institute for Advanced Computer Science NASA Ames Research Center MS 227-6 Moffett Field CA94035 United States Department of Mechanical and Aerospace Engineering Princeton University PrincetonNJ08544 United States Simco NASA Ames Research Center MS 227-6 Moffett Field CA94035 United States James S. McDonnell Distinguished University Aerospace Engineering United States

This work describes the application of a control theory-based aerodynamic shape optimization method to the problem of supersonic aircraft design. The design process is greatly accelerated through the use of both control theory and a parallel implementation on distributed memory computers. Control theory is employed to derive the adjoint differential equations whose solution allows for the evaluation of design gradient information at a fraction of the computational cost required by previous design methods [13, 12, 44, 38]. The resulting problem is then implemented on parallel distributed memory architectures using a domain decomposition approach, an optimized communication schedule, and the MPI (Message Passing Interface) Standard for portability and efficiency. The final result achieves very rapid aerodynamic design based on higher order computational fluid dynamics methods (CFD). In our earlier studies, the serial implementation of this design method [19, 20, 21, 23, 39, 25, 40, 41, 42, 43, 9] was shown to be effective for the optimization of airfoils, wings, wing-bodies, and complex aircraft configurations using both the potential equation and the Euler equations[39, 25]. In our most recent paper, the Euler method was extended to treat complete aircraft configurations via a new multiblock implementation. Furthermore, during the same conference, we also presented preliminary results demonstrating that this basic methodology could be ported to distributed memory parallel computing architectures [24]. In this paper, our concern will be to demonstrate that the combined power of these new technologies can be used routinely in an industrial design environment by applying it to the case study of the design of typical supersonic transport configurations. A particular difficulty of this test case is posed by the propulsion/airframe integration. © 1996 by the American Institute of Aeronautics and Astronautics, Inc. All rights reserved.

关键词： Supersonic aircraft

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Experiments in automated load balancing 96

Experiments in automated load balancing

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Proceedings of the tenth workshop on Parallel and distributed simulation

作者： Linda F. Wilson David M. Nicol Institute for Computer Applications Science and Engineering NASA Langley Research Center Hampton VA Department of Computer Science The College of William and Mary P.O. Box 8795 Williamsburg VA

ISBN: (纸本)9780818675393

One of the promises of parallelized discrete-event simulation is that it might provide significant speedups over sequential simulation. In reality, high performance cannot be achieved unless the system is fine-tuned to balance computation, communication, and synchronization requirements. In this paper, we discuss our experiments in automated load balancing using the SPEEDES simulation framework. Specifically, we examine three mapping algorithms that use run-time measurements. Using simulation models of queuing networks and the National Airspace System, we investigate (i) the use of run-time data to guide mapping, (ii) the utility of considering communication costs in a mapping algorithm, (iii) the degree to which computational ``hot-spots'' ought to be broken up in the linearization, and (iv) the relative execution costs of the different algorithms. We compare the performance of the three algorithms using results from the Intel Paragon.

关键词： load balancing discrete-event simulation parallel computing performance analysis

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On computing sound radiation of a temporally evolving mixing layer by vortex method and matched asymptotic expansions 34th

On computing sound radiation of a temporally evolving mixing...

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34th aerospace sciences Meeting and Exhibit, 1996

作者： Hu, F.Q. Martin, J.E. Hussaini, M.Y. Department of Mathematics and Statistics Old Dominion University NorfolkVA23529 United States Department of Mathematics Christopher Newport University Newport NewsVA23606 United States Institute for Computer Applications in Science and Engineering NASA Langley Research Center HamptonVA23681 United States

In this paper, sound radiation associated with a temporally evolving mixing layer is considered. Numerical simulations are carried out by a vortex method in which the mixing layer is modeled by an array of vortex blobs and perturbed with the wavelength of the most amplified wave. Since the vortex method computes an incompressible flow, a methodology of computing the acoustic field based on matched asymptotic expansions is employed. A singular perturbation is developed in which the incompressible solution obtained by the vortex method is the inner solution while the acoustic field is the outer solution. The formal matching process is carried out by introducing intermediate variables. It is shown that in the limit of zero Mach number, the leading terms match smoothly. The inner solution of the incompressible flow..thus provides the boundary condition for the outer solution of radiated sound. Numerical results of the vortex simulation and computed acoustic pressure are presented. © 1996 by the American Institute of Aeronautics and Astronautics, Inc. All Rights Reserved.

关键词： Acoustic fields

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Response surface approximations for pitching moment including pitch-up in the MDO design of an HSCT 6th

Response surface approximations for pitching moment includin...

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6th AIAA/NASA/ISSMO Symposium on Multidisciplinary Analysis and Optimization, 1996

作者： Crisafulli, Paul Kaufman, Matthew Giunta, Anthony A. Mason, William H. Grossman, Bernard Watson, Layne T. Haftka, Raphael T. Center for Advanced Vehicles Virginia Polytechnic Institute and State University Mail Stop 0203 BlacksburgVA24061 United States Dept. of Aerospace Engineering Mechanics and Engineering Science Univ. of Florida GainesvilleFL32611-6250 United States Dept. of Aerospace and Ocean Eng Virginia Tech BlacksburgVA24061 United States Depts. of Computer Science and Mathematics Virginia Tech BlacksburgVA24061 United States

A procedure for incorporating key non-linear aerodynamic characteristics into the design optimization of a high-speed civil transport has been developed. Previously, planforms which were likely to exhibit pitch-up in low speed flight could not be included directly in the design process, Using response surface methodology, polynomial approximations to the results obtained from a computationally expensive estimation method were developed by analyzing a set of statistically selected wing shapes. These response surface models were then used during the optimization process to approximate the effects of wing planform changes on pitch-up. In addition, response surface approximations were used to model the effect of horizontal tail size and wing flaps on the performance of the aircraft. Optimization studies of the high-speed civil transport were done with and without the response surfaces. The results of this study provide insight into the influence of both nonlinear aerodynamics and high lift aerodynamics on the design of a high-speed civil transport. © 1996 by Paul Crisafulli.

关键词： Polynomial approximation

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Dependence of optimal structural weight on aerodynamic shape for a high speed civil transport 6th

Dependence of optimal structural weight on aerodynamic shape...

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6th AIAA/NASA/ISSMO Symposium on Multidisciplinary Analysis and Optimization, 1996

作者： Balabanov, V. Kaufman, M. Knill, D.L. Haim, D. Golovidov, O. Giunta, A.A. Haftka, Raphael T. Grossman, B. Mason, W.H. Watson, L.T. Center for Advanced Vehicles Virginia Polytechnic Institute and State University Dept. of Aerospace and Ocean Eng. Mail Stop 0203 BlacksburgVA24061 United States Center for Advanced Vehicles Virginia Polytechnic Institute and State University Dept. of Computer Sci. and Math. Mail Stop 0203 BlacksburgVA24061 United States Department of Aerospace Engineering Mechanics and Engineering Science University of Florida GainesvilleFL32611-6250 United States MAD Center for Advanced Vehicles Virginia Tech Dept. of Aerospace and Ocean Eng. United States MAD Center for Advanced Vehicles Virginia Tech Dept. of Computer Sci. and Math. United States

A procedure for generating a customized weight function for wing bending material weight of the High Speed Civil Transport (HSCT) is described. The weight function is based on the shape parameters. A response surface methodology is used to fit a quadratic polynomial to data gathered from a large number of structural optimizations. The results of the structural optimization are noisy. Noise reduction in the structural optimization results is discussed. Several techniques are used to minimize the number of required structural optimizations and to maintain accuracy. Simple analysis techniques are used to find regions of the design space where reasonable HSCT designs could occur, thus customizing the weight function to the design requirements of the HSCT, while the response surfaces themselves are created employing detailed analysis methods. Intervening variables and analysis of variance are used to reduce the number of polynomial terms in the response surface model functions. Minimum variance and minimum bias procedures for creation of response surfaces are compared. Configuration optimization of the HSCT employing customized weight functions with different response surfaces are compared. © 1996 by V. Balabanov.

关键词： Structural optimization

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High performance supersonic missile inlet design using automated optimization 6th

High performance supersonic missile inlet design using autom...

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6th AIAA/NASA/ISSMO Symposium on Multidisciplinary Analysis and Optimization, 1996

作者： Zha, Ge-Cheng Smith, Donald Schwabachei, Mark Rasheed, Khaled Gelsey, Andrew Knight, Doyle Haas, Martin Rutgers University The State University of New Jersey PO Box 909 PiscatawayNJ08855-0909 United States United Technologies Research Center East HartfordCT06180 United States Dept. Of Mechanical and Aerospace Engineering United States Computer Science Dept United States

A multi-level design strategy for supersonic missile inlet design is developed. The multi-level design strategy combines an efficient simple physical model analysis tool and a sophisticated CFD Navier-Stokes analysis tool. The efficient simple analysis tool is incorporated into the optimization loop and the sophisticated CFD analysis tool is used to verify, select and filter the final design. The Genetic Algorithms and Multi-start gradient line search optimizers are used to search the non- smooth design space. A geometry model for the supersonic missile inlet is developed. A supersonic missile inlet which starts at Mach 2.6 and cruises at Mach 4 was designed. Significant improvement of the inlet total pressure recovery has been obtained. Detailed flow field analysis is also presented. © 1996 by Ge-Cheng Zha, Donald Smith, Mark Schwabacher, Khaled Rasheed, Andrew Gelsey, and Doyle D. Knight.

关键词： Computational fluid dynamics

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Aerodynamic shape optimization of complex aircraft configurations via an adjoint formulation 34th

Aerodynamic shape optimization of complex aircraft configura...

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34th aerospace sciences Meeting and Exhibit, 1996

作者： Reuther, J. Jameson, A. Farmer, J. Marlinelli, L. Saunders, D. Research Institute for Advanced Computer Science NASA Ames Research Center MS 227-6 Moffett Field CA94035 United States Department of Mechanical and Aerospace Engineering Princeton University PrincetonNJ08544 United States Advanced Combustion and Engineering Research Center Brigham Young University 75J CTB P.O. Box 24214 ProvoUT84602 United States Department of Mechanical and Aerospace Engineering Princeton University PrincetonNJ08544 United States Sterling Software NASA Ames Research Center MS 227-6 Moffett Field CA94035 United States

This work describes the implementation of optimization techniques based on control theory for complex aircraft configurations. Here control theory is employed to derive the adjoint differential equations, the solution of which allows for a drastic reduction in computational costs over previous design methods [13, 12, 43, 38]. In our earlier studies [19, 20, 22, 23, 39, 25, 40, 41, 42] it was shown that this method could be used to devise effective optimization procedures for airfoils, wings and wing-bodies subject to either analytic or arbitrary meshes. Design formulations for both potential flows and flows governed by the Euler equations have been demonstrated, showing that such methods can be devised for various governing equations [39, 25]. In our most recent works [40, 42] the method was extended to treat wing-body configurations with a large number of mesh points, verifying that significant computational savings can be gained for practical design problems. In this paper the method is extended for the Euler equations to treat complete aircraft configurations via a new multiblock implementation. New elements include a multiblock-multigrid flow solver, a multiblock-multigrid adjoint solver, and a multiblock mesh perturbation scheme. Two design examples are presented in which the new method is used for the wing redesign of a transonic business jet. © 1996, American Institute of Aeronautics and Astronautics, Inc.

关键词： Euler equations

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3D shock wave visualization on unstructured grids

3D shock wave visualization on unstructured grids

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IEEE Symposium on Volume Visualization and Graphics

作者： Kwan-Liu Ma J. Van Rosendale W. Vermeer Institute for Computer Applications in Science and Engineering(ICASE) NASA-Langley Research Center Hampton VA USA NASA Langley Research Center Hampton VA US Department of Applied Mathematics and Informatics Delft University of Technnology Delft Netherlands

A critical issue in understanding high speed flows is the study of shock waves. The paper summarizes our research on techniques for the detection and visualization of shock waves occuring in simulations of three dimensional flows on unstructured grids. Detection algorithms based on Mach number, density gradient and directional derivatives are compared using a data set from calculations of a transonic flow with a weak double shock around an airfoil. Both surface and volume rendering techniques are used to display the shocks. The issues in this research area are very much like those occurring in medical imaging. Since the data themselves (in this case the results of the fluid dynamics simulation) are intrinsically low resolution and noisy, properly extracting and visualizing the shock is very difficult. In this environment, blurry, low resolution techniques, like the splatting volume rendering, seem to do rather well. More complex schemes, using sophisticated numerical shock detectors coupled with polygon rendering, produce visually sharper shocks, but also introduce "graphics artifacts," which complicate understanding of the flow physics. On the other hand, visualization results produced with techniques like splatting are, in effect, relying more on the human visual system to compensate for limited resolution in the simulation.

关键词： Shock waves Electric shock Data visualization Detection algorithms Automotive components Displays Biomedical imaging Fluid dynamics Medical simulation Working environment noise

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Understanding and predicting the process of software maintenance release 96

Understanding and predicting the process of software mainten...

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Proceedings of the 18th international conference on Software engineering

作者： Victor Basili Lionel Briand Steven Condon Yong-Mi Kim Walcélio L. Melo Jon D. Valett University of Maryland Institute for Advanced Computer Studies and Computer Science Dept. A. V. Williams Bldg. College Park MD CRIM Montreal Canada Computer Sciences Corporation 10110 Aerospace Rd. Lanham-Seabrook MD NASA Goddard Space Flight Center Software Engineering Branch Greenbelt MD

ISBN: (纸本)9780818672460

One of the major concerns of any maintenance organization is to understand and estimate the cost of maintenance releases of software systems. Planning the next release so as to maximize the increase in functionality and the improvement in quality are vital to successful maintenance management. The objective of the paper is to present the results of a case study in which an incremental approach was used to better understand the effort distribution of releases and build a predictive effort model for software maintenance releases. The study was conducted in the Flight Dynamics Division (FDD) of NASA Goddard Space Flight center (GSFC). The paper presents three main results: (1) a predictive effort model developed for the FDD's software maintenance release process, (2) measurement-based lessons learned about the maintenance process in the FDD, (3) a set of lessons learned about the establishment of a measurement-based software maintenance improvement program. In addition, this study provides insights and guidelines for obtaining similar results in other maintenance organizations.

关键词： case studies

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Mapping of boreal forest biomass using SAR

Mapping of boreal forest biomass using SAR

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IEEE International Symposium on Geoscience and Remote Sensing (IGARSS)

作者： K.J. Ranson Guoqing Sun B. Montgomery R.H. Lang Biospheric Sciences Branch Goddard Space Flight Center NASA Greenbelt MD USA Science Systems and Applications Inc. Lanham MD USA Hughes STX Corporation Lanham MD USA Electrical Engineering and Computer Science Dept George Washington University Washington D.C. DC USA

Knowledge of the distribution and structure of forests can lead to improved estimates of the carbon balance in terms of above ground storage and exchange with the atmosphere from maintenance respiration. As part of the Boreal Ecosystem Atmosphere Study (BOREAS) a study is being made of the use of remote sensing data for estimating land cover and biophysical characteristics of boreal forest study sites in Canada. Earlier work by the authors and others have developed maps of forest cover and above ground biomass. The biomass maps are produced using a regression equation developed from forest measurements and radar backscatter data. Other researchers have made a case for stratifying forest cover and constructing separate biomass relationships for each strata. In this paper the authors examine the use of forest classification maps derived from SIR-C/XSAR images to improve estimates of total biomass. The classification procedure used a supervised Bayesian classifier to map the forest area into several forest and non-forest classes. Forest classes were combined into dry conifer, wet conifer and deciduous. Regression equations of dry biomass and radar backscatter were developed for each forest type and applied to the radar data. A stepwise technique was used to determine the best set or combinations of radar channels for mapping biomass. The best channels for biomass estimation was determined to be LHV and CHV for conifers and a combination of LHH, LHV and CHV worked best for the limited deciduous data available. Analysis of the results indicates that forest type should be considered when mapping biomass in this type of forest. However, the results from a more general equation were adequate.

关键词： Biomass Equations Atmosphere Radar imaging Backscatter Ecosystems Remote sensing Radar measurements Radar remote sensing Bayesian methods

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