The Experts below are selected from a list of 78 Experts worldwide ranked by ideXlab platform
Dimitri N Mavris - One of the best experts on this subject based on the ideXlab platform.
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rapid state space Modeling tool for rectangular wing aeroservoelastic studies
AIAA SciTech 2015- Modeling and Simulation Technologies Conference, 2015Co-Authors: Peter M Suh, Howard J Conyers, Dimitri N MavrisAbstract:This paper introduces a Modeling and simulation tool for aeroservoelastic analysis of rectangular wings with trailing edge control surfaces. The inputs to the code are planform design parameters such as wing span, aspect ratio and number of control surfaces. A doublet lattice approach is taken to compute generalized forces. A rational function approximation is computed. The output, computed in a few seconds, is a state space aeroservoelastic Model which can be used for analysis and control design. The tool is fully parameterized with default information so there is little required interaction with the Model Developer. Although, all parameters can be easily modified if desired.The focus of this paper is on tool presentation, verification and validation. This process is carried out in stages throughout the paper. The rational function approximation is verified against computed generalized forces for a plate Model. A Model composed of finite element plates is compared to a modal analysis from commercial software and an independently conducted experimental ground vibration test analysis. Aeroservoelastic analysis is the ultimate goal of this tool. Therefore the flutter speed and frequency for a clamped plate are computed using V-g and V-f analysis. The computational results are compared to a previously published computational analysis and wind tunnel results for the same structure. Finally a case study of a generic wing Model with a single control surface is presented. Verification of the state space Model is presented in comparison to V-g and V-f analysis. This also includes the analysis of the Model in response to a 1-cos gust.
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rapid state space Modeling tool for rectangular wing aeroservoelastic studies
SciTech 2015, 2015Co-Authors: Peter M Suh, Howard J Conyers, Dimitri N MavrisAbstract:This paper introduces a Modeling and simulation tool for aeroservoelastic analysis of rectangular wings with trailing-edge control surfaces. The inputs to the code are planform design parameters such as wing span, aspect ratio, and number of control surfaces. Using this information, the generalized forces are computed using the doublet-lattice method. Using Roger's approximation, a rational function approximation is computed. The output, computed in a few seconds, is a state space aeroservoelastic Model which can be used for analysis and control design. The tool is fully parameterized with default information so there is little required interaction with the Model Developer. All parameters can be easily modified if desired. The focus of this paper is on tool presentation, verification, and validation. These processes are carried out in stages throughout the paper. The rational function approximation is verified against computed generalized forces for a plate Model. A Model composed of finite element plates is compared to a modal analysis from commercial software and an independently conducted experimental ground vibration test analysis. Aeroservoelastic analysis is the ultimate goal of this tool, therefore, the flutter speed and frequency for a clamped plate are computed using damping-versus-velocity and frequency-versus-velocity analysis. The computational results are compared to a previously published computational analysis and wind-tunnel results for the same structure. A case study of a generic wing Model with a single control surface is presented. Verification of the state space Model is presented in comparison to damping-versus-velocity and frequency-versus-velocity analysis, including the analysis of the Model in response to a 1-cos gust.
Peter M Suh - One of the best experts on this subject based on the ideXlab platform.
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rapid state space Modeling tool for rectangular wing aeroservoelastic studies
AIAA SciTech 2015- Modeling and Simulation Technologies Conference, 2015Co-Authors: Peter M Suh, Howard J Conyers, Dimitri N MavrisAbstract:This paper introduces a Modeling and simulation tool for aeroservoelastic analysis of rectangular wings with trailing edge control surfaces. The inputs to the code are planform design parameters such as wing span, aspect ratio and number of control surfaces. A doublet lattice approach is taken to compute generalized forces. A rational function approximation is computed. The output, computed in a few seconds, is a state space aeroservoelastic Model which can be used for analysis and control design. The tool is fully parameterized with default information so there is little required interaction with the Model Developer. Although, all parameters can be easily modified if desired.The focus of this paper is on tool presentation, verification and validation. This process is carried out in stages throughout the paper. The rational function approximation is verified against computed generalized forces for a plate Model. A Model composed of finite element plates is compared to a modal analysis from commercial software and an independently conducted experimental ground vibration test analysis. Aeroservoelastic analysis is the ultimate goal of this tool. Therefore the flutter speed and frequency for a clamped plate are computed using V-g and V-f analysis. The computational results are compared to a previously published computational analysis and wind tunnel results for the same structure. Finally a case study of a generic wing Model with a single control surface is presented. Verification of the state space Model is presented in comparison to V-g and V-f analysis. This also includes the analysis of the Model in response to a 1-cos gust.
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rapid state space Modeling tool for rectangular wing aeroservoelastic studies
SciTech 2015, 2015Co-Authors: Peter M Suh, Howard J Conyers, Dimitri N MavrisAbstract:This paper introduces a Modeling and simulation tool for aeroservoelastic analysis of rectangular wings with trailing-edge control surfaces. The inputs to the code are planform design parameters such as wing span, aspect ratio, and number of control surfaces. Using this information, the generalized forces are computed using the doublet-lattice method. Using Roger's approximation, a rational function approximation is computed. The output, computed in a few seconds, is a state space aeroservoelastic Model which can be used for analysis and control design. The tool is fully parameterized with default information so there is little required interaction with the Model Developer. All parameters can be easily modified if desired. The focus of this paper is on tool presentation, verification, and validation. These processes are carried out in stages throughout the paper. The rational function approximation is verified against computed generalized forces for a plate Model. A Model composed of finite element plates is compared to a modal analysis from commercial software and an independently conducted experimental ground vibration test analysis. Aeroservoelastic analysis is the ultimate goal of this tool, therefore, the flutter speed and frequency for a clamped plate are computed using damping-versus-velocity and frequency-versus-velocity analysis. The computational results are compared to a previously published computational analysis and wind-tunnel results for the same structure. A case study of a generic wing Model with a single control surface is presented. Verification of the state space Model is presented in comparison to damping-versus-velocity and frequency-versus-velocity analysis, including the analysis of the Model in response to a 1-cos gust.
Howard J Conyers - One of the best experts on this subject based on the ideXlab platform.
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rapid state space Modeling tool for rectangular wing aeroservoelastic studies
AIAA SciTech 2015- Modeling and Simulation Technologies Conference, 2015Co-Authors: Peter M Suh, Howard J Conyers, Dimitri N MavrisAbstract:This paper introduces a Modeling and simulation tool for aeroservoelastic analysis of rectangular wings with trailing edge control surfaces. The inputs to the code are planform design parameters such as wing span, aspect ratio and number of control surfaces. A doublet lattice approach is taken to compute generalized forces. A rational function approximation is computed. The output, computed in a few seconds, is a state space aeroservoelastic Model which can be used for analysis and control design. The tool is fully parameterized with default information so there is little required interaction with the Model Developer. Although, all parameters can be easily modified if desired.The focus of this paper is on tool presentation, verification and validation. This process is carried out in stages throughout the paper. The rational function approximation is verified against computed generalized forces for a plate Model. A Model composed of finite element plates is compared to a modal analysis from commercial software and an independently conducted experimental ground vibration test analysis. Aeroservoelastic analysis is the ultimate goal of this tool. Therefore the flutter speed and frequency for a clamped plate are computed using V-g and V-f analysis. The computational results are compared to a previously published computational analysis and wind tunnel results for the same structure. Finally a case study of a generic wing Model with a single control surface is presented. Verification of the state space Model is presented in comparison to V-g and V-f analysis. This also includes the analysis of the Model in response to a 1-cos gust.
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rapid state space Modeling tool for rectangular wing aeroservoelastic studies
SciTech 2015, 2015Co-Authors: Peter M Suh, Howard J Conyers, Dimitri N MavrisAbstract:This paper introduces a Modeling and simulation tool for aeroservoelastic analysis of rectangular wings with trailing-edge control surfaces. The inputs to the code are planform design parameters such as wing span, aspect ratio, and number of control surfaces. Using this information, the generalized forces are computed using the doublet-lattice method. Using Roger's approximation, a rational function approximation is computed. The output, computed in a few seconds, is a state space aeroservoelastic Model which can be used for analysis and control design. The tool is fully parameterized with default information so there is little required interaction with the Model Developer. All parameters can be easily modified if desired. The focus of this paper is on tool presentation, verification, and validation. These processes are carried out in stages throughout the paper. The rational function approximation is verified against computed generalized forces for a plate Model. A Model composed of finite element plates is compared to a modal analysis from commercial software and an independently conducted experimental ground vibration test analysis. Aeroservoelastic analysis is the ultimate goal of this tool, therefore, the flutter speed and frequency for a clamped plate are computed using damping-versus-velocity and frequency-versus-velocity analysis. The computational results are compared to a previously published computational analysis and wind-tunnel results for the same structure. A case study of a generic wing Model with a single control surface is presented. Verification of the state space Model is presented in comparison to damping-versus-velocity and frequency-versus-velocity analysis, including the analysis of the Model in response to a 1-cos gust.
Patrick Willems - One of the best experts on this subject based on the ideXlab platform.
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Modular conceptual Modelling approach and software for river hydraulic simulations
Environmental Modelling and Software, 2015Co-Authors: Vincent Wolfs, Pieter Meert, Patrick WillemsAbstract:Numerous applications in river management require computationally efficient Models that can accurately simulate the state of a river. This paper presents a reduced complexity Modelling approach that emulates the results of detailed full hydrodynamic Models. Its modular design based on virtual reservoirs allows users to combine different Model structures depending on the river dynamics and intended use. A semi-automatic software tool (Conceptual Model Developer, CMD) was developed to facilitate Model set-up. To prevent instabilities during simulations, a highly efficient discrete calculation scheme is presented with a variable time step. To illustrate the effectiveness of the presented approach, the Marke River in Belgium was conceptualized based on simulation results of a detailed Model. Results show that the derived conceptual Model mimics the detailed Model closely, while the calculation time is reduced by more than 2000 times. Finally, several applications are discussed that employ conceptual Models built according to the presented approach. A reduced complexity Modelling approach for river hydraulic simulations is proposed.Flexible modular framework that incorporates a variety of structures and techniques.A software tool (CMD) was created to speed-up and facilitate Model set-up.A discrete calculation scheme was developed with time and space varying time step.A case study and discussion of applications illustrate the approach's effectiveness.
R Subbarao - One of the best experts on this subject based on the ideXlab platform.
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target processor and co verification environment independent adapter a technology to shorten cycle time for retargeting ti processor simulators in hw sw co verification environments
International Conference on ASIC, 1999Co-Authors: R Shah, R SubbaraoAbstract:Hardware-software co-verification is essential for design and verification of embedded systems at the early development stages to reduce development cycle time. A number of co-verification environments are available from EDA vendors to simulate such designs, each with its own interfaces and mechanisms. TI provides co-verification Models for its DSP devices and cDSP megamodules in these environments. We present an approach that enables TI's instruction set simulators to seamlessly be integrated in these environments. This hides the EDA environment specific interfaces from the simulator/Model Developer thereby shortening the co-verification Model development cycle times.
