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检索条件"主题词=Sequential Quadratic Programming"

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Multidimensional Diagonal-Norm Summation-by-Parts Operators on Quadrilateral Elements

Multidimensional Diagonal-Norm Summation-by-Parts Operators ...

引用

AIAA Aviation Forum and Exposition

作者： Mattalo, Kevin J. Zingg, David W. Univ Toronto Inst Aerosp Studies 4925 Dufferin St Toronto ON M3H 5T6 Canada Univ Toronto Inst Aerosp Studies Computat Aerodynam & Sustainable Aviat 4925 Dufferin St Toronto ON M3H 5T6 Canada Univ Toronto Inst Aerosp Studies Ctr Res Sustainable Aviat 4925 Dufferin St Toronto ON M3H 5T6 Canada Univ Toronto Inst Aerosp Studies Ctr Computat Sci & Engn 4925 Dufferin St Toronto ON M3H 5T6 Canada

ISBN: (数字)9781624105890

ISBN: (纸本)9781624105890

The summation-by-parts (SBP) property provides a rigorous means of proving linear and nonlinear stability. Recently, the SBP property has been extended from tensor-product nodal distributions on multiblock curvilinear meshes to unstructured meshes on arbitrary polytopes. The objective of this paper is to search for efficient cubature rules on quadrilateral elements and perform a comparative analysis of their properties relative to traditional tensor-product operators. To this end, an algorithm for the constrained numerical optimization of multidimensional SBP operators on quadrilateral elements is presented. Using this algorithm, operators are optimized relative to an objective function which accounts for accuracy of the SBP derivative operator. Additionally, properties which affect time stability for explicit time integration methods and conditioning of the node set are calculated and analyzed. Properties necessary to preserve the SBP property are enforced through linear and nonlinear constraints. Numerical experiments are presented comparing tensor-product element-type operators on Legendre-Gauss (LG) and Legendre-Gauss-Lobatto (LGL) nodal distributions and non-tensor-product nodal distributions in order to understand the relative accuracy and computational efficiency of the corresponding methods. It is found that the non-tensor-product nodal distributions are able to achieve cubature rules with lower cubature truncation error compared to tensor-product cubature rules, with fewer nodes. Additionally, the SBP operators constructed on the non-tensor-product cubature nodes are found to have equal or better solution error and efficiency for test cases performed with the linear advection and Euler equations on curvilinear grids.

关键词： Numerical Optimization Advection Euler Equations Vortices sequential quadratic programming Two Dimensional Elements Finite Difference Method Numerical Simulation Hexahedral Element Runge Kutta Methods

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Multi-fidelity efficient global optimization: Methodology and application to airfoil shape design

Multi-fidelity efficient global optimization: Methodology an...

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AIAA Aviation Forum and Exposition

作者： Meliani, Mostafa Bartoli, Nathalie Lefebvre, Thierry Bouhlel, Mohamed-Amine Martins, Joaquim R. R. A. Morlier, Joseph Univ Toulouse ISAE SUPAERO Toulouse France Univ Toulouse DTIS ONERA Informat Proc & Syst Dept Toulouse France Univ Michigan Dept Aerosp Engn Ann Arbor MI 48109 USA Univ Toulouse Inst Clement Ader ISAE SUPAERO CNRS Toulouse France

ISBN: (数字)9781624105890

ISBN: (纸本)9781624105890

Predictions and design engineering decisions can be made using a variety of information sources that range from experimental data to computer models. These information sources could consist of different mathematical formulations, different grid resolutions, different physics, or different modeling assumptions that simplify the problem. This leads to information sources with varying degrees of fidelity, each with an associated accuracy and querying cost. In this paper, we propose a novel and flexible way to use multi-fidelity information sources optimally in the context of airfoil shape optimization using both Xfoil and ADflow. The new developments are based on Bayesian optimization and kriging metamodeling and allow the aerodynamic optimization to be sped up. In a constrained optimization example with 15-design variables problem, the proposed approach reduces the total cost by a factor of two compared to a single Bayesian based fidelity optimization and by a factor of 1.5 compared to sequential quadratic programming.

关键词： Airfoil Databases Aerodynamic Shape Optimization Surrogate Model Shape Optimization Probability Density Functions Bayesian Optimization Reynolds Averaged Navier Stokes sequential quadratic programming Black Box Singular Value Decomposition

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Application of Subdivision Surfaces to Aerodynamic Wing Shape Optimisation

Application of Subdivision Surfaces to Aerodynamic Wing Shap...

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AIAA Aviation Forum and Exposition

作者： Kedward, Laurence J. Allen, C. B. Rendall, T. C. S. Univ Bristol Dept Aerosp Engn Bristol BS8 1TR Avon England Univ Bristol Dept Aerosp Engn Computat Aerodynam Bristol BS8 1TR Avon England

ISBN: (数字)9781624105890

ISBN: (纸本)9781624105890

Subdivision surfaces, which generalise tensor-product splines to arbitrary topology, are seeing increased interest in engineering applications. Significantly, the topological flexibility of such subdivision splines enables truly watertight parametric geometry. Previous work by the authors has performed progressive and adaptive shape optimisation using hierarchies of subdivision control fidelities. Such multilevel methods typically enable both global and local shape modifications to occur. In this paper, theory and preliminary results are presented for the application of subdivision surfaces to the aerodynamic optimisation of a modern transport wing. Spline-like control nets are generated from the discretised surface of the wing geometry and used as shape control within a gradient-based aerodynamic shape optimisation framework. A multiresolution formulation ensures that the exact surface is reproduced by the subdivision shape control while also allowing control at varying fidelity. Gradient-based optimisation is performed using an efficient SQP implementation along with an unstructured Euler solver where aerodynamic sensitivities are provided by discrete adjoint. The optimisation results show consistent reductions in both wave drag and induced drag while satisfying the aerodynamic constraints thereby demonstrating the effectiveness afforded by surface splines for shape optimisation.

关键词： Shape Control Aerodynamic Shape Optimization Shape Optimization sequential quadratic programming Wing Shape Optimization Wing Geometry Computer Aided Design Numerical Analysis Finite Volume Method Search Algorithm

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Comparison of Wind Farm Layout Optimization Results Using a Simple Wake Model and Gradient-Based Optimization to Large-Eddy Simulations

Comparison of Wind Farm Layout Optimization Results Using a ...

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AIAA Science and Technology (SciTech) Forum and Exposition

作者： Thomas, Jared J. Annoni, Jennifer Fleming, Paul Ning, Andrew Brigham Young Univ Dept Mech Engn 360 EB Provo UT 84602 USA Natl Renewable Energy Lab Natl Wind Technol Ctr 15013 Denver West Pkwy Golden CO 80401 USA

ISBN: (数字)9781624105784

ISBN: (纸本)9781624105784

The models used during wind farm layout optimization use simplifying assumptions that can alter the design space. Some characteristics of the simple models may negatively influence the resulting layouts. In this paper, we perform wind farm layout optimization using a simple wake model and compare the resulting improvements to large-eddy simulation (LES) results to confirm that the layout was actually improved. We begin by describing the models used, including changes specific for use with gradient-based optimization. We then compare our models' output to previously published model and LES results. Using the models described, we performed gradient-based wind farm layout optimization using exact gradients. Power production for the original and optimized layouts were recalculated using LES. The model and LES results were then compared. The simple models predicted an improvement in annual energy production (AEP) of 7.4%, while the LES reported an AEP improvement of 9.9%. We concluded that the improvements found by optimizing with the simple models are not just an artifact of the model characteristics, but are real improvements.

关键词： Large Eddy Simulation Energy Production Wind Turbine Wakes Turbulence Intensity sequential quadratic programming Linear Interpolation Gradient Free Optimization Actuator Disk Wind Tunnel Tests Sparse Nonlinear Optimizer

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A Reduced-order model for Aerodynamic Shape Optimization

A Reduced-order model for Aerodynamic Shape Optimization

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AIAA Science and Technology (SciTech) Forum and Exposition

作者： Yao, W. Marques, S. Robinson, T. Armstrong, C. Sun, L. Queens Univ Sch Mech & Aerosp Engn Belfast BT9 5AH Antrim North Ireland Univ Surrey Dept Mech Engn Sci Guildford GU2 7XH Surrey England

ISBN: (数字)9781624105784

ISBN: (纸本)9781624105784

The motivation for the present work is to develop a reduced order model (ROM) for gradient based aerodynamic shape optimization. The fluid Euler equations or full order model (FOM) is converted to a reduced Newton iteration by using the Petrov-Galerkin projection. The reduced order basis (ROB) are extracted by Proper Orthogonal Decomposition (POD) from snapshots collected of the fluid state, along the optimization trajectory. Similarly, the reduced gradient formulation is derived by projecting the FOM state onto the subspace spanned by ROBs. The residual of reduced Newton iteration is used as an indicator to update the snapshots and ROB. The ROM is demonstrated for a subsonic inverse design problem and for airfoil drag minimization at transonic Mach numbers. The results suggest that the constructed ROM is capable of aerodynamic shape optimization while reducing the number of FOM queries with respect to an adjoint gradient based optimization framework. The reduction in computation cost is over one order of magnitude for the subsonic case;however, efficiency deteriorates for the transonic problem, exhibiting a reduction in computational time of about one-third with respect to an optimization using the FOM.

关键词： Aerodynamic Shape Optimization Airfoil Fluid State Euler Equations Transonic Flow Shape Optimization Eigensystem Realization Algorithm sequential quadratic programming Nonlinear Systems MATLAB

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Enhancement of Transmittable Power using Optimal Control of SSSC Considering X/R Ratio of Transmission Line

Enhancement of Transmittable Power using Optimal Control of ...

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IEEE PES GTD Grand International Conference and Exposition Asia (GTD Asia)

作者： Nema, Shruti George, Sincy Fr C Rodrigues Inst Technol Dept Elect Engn Navi Mumbai India St Francis Inst Technol Mumbai Maharashtra India

ISBN: (纸本)9781538674345

Overloading in existing transmission lines can be eliminated by enhancing the transmittable power through existing transmission line using series capacitive compensation, which was introduced long ago. Later, a converter based series compensation called Static Synchronous Series Compensator (SSSC) is introduced and its inherent capability of exchanging real power is efficiently utilized in the proposed work. If an attempt is made to increase transmittable power through a transmission line using SSSC, power loss and X/R ratio of the transmission line gets deteriorated. The trade-off between transmittable power, transmission loss and X/R ratio is tackled by an optimal control of the compensator. In this paper, an optimal control of SSSC is proposed with the objective of minimizing transmission loss while maintaining the X/R ratio and voltage within the limits. A MATLAB simulation platform is used for validating the proposed optimal control of SSSC for enhancing transmittable power of a 400kV, 400km transmission line. It is seen that, for a 30% enhanced transmittable power, power loss could be reduced by 27.89% with proposed optimization technique as compared to power loss without optimization.

关键词： Optimization Static Synchronous Series Compensator sequential quadratic programming Voltage source Inverter X/R ratio

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Multiple Vehicles Merging Control via Sequence and Trajectory Optimization 4th

Multiple Vehicles Merging Control via Sequence and Trajector...

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4th International Conference on Cognitive Systems and Information Processing (ICCSIP)

作者： Tang, Wei Yang, Ming Qian, Qiyang Wang, Chunxiang Wang, Bing Shanghai Jiao Tong Univ Dept Automat Shanghai 200240 Peoples R China Minist Educ China Key Lab Syst Control & Informat Proc Shanghai 200240 Peoples R China Univ Tokyo Sch Engn Tokyo 1138654 Japan

ISBN: (纸本)9789811379864;9789811379857

In multi-lane traffic scenarios, accidents, construction, and other conditions will reduce the number of lanes, and vehicles need to decelerate, merge and pass. Therefore, vehicles merging is a hot topic in multi-vehicle cooperative driving. The existing primary methods focus on merging trajectory optimization based on the known sequence of merging and mainly consider the longitudinal model. Simulated annealing algorithm combined with sequential quadratic programming is used to optimize the merging sequence and the corresponding trajectories. Numerical simulation verifies the stability and feasibility of the algorithm. Finally, the micro intelligent vehicles based simulation platform is introduced to carry out the merging experiment which proves the effectiveness of the proposed algorithm.

关键词： Merging Simulated annealing algorithm sequential quadratic programming

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Rapid Trajectory Optimisation in Mars Pinpoint landing using Pseudo-Spectral method 5

Rapid Trajectory Optimisation in Mars Pinpoint landing using...

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5th Indian Control Conference (ICC)

作者： Swaminathan, Shriram Kumar, Sriram S. Indian Space Rasearch Org Vikram Sarabhai Space Ctr Thiruvananthapuram Kerala India APJ Abdul Kalam Technol Univ Dept Elect Engn CET Thiruvananthapuram Kerala India

ISBN: (纸本)9781538662465

Real time trajectory optimisation of powered descent phase in Mars pinpoint landing is presented in this paper. Pinpoint landing on Mars in the presence of large initial condition dispersions and constraints on thrust, orientation and path are solved in near real time. A new method for implementing Pseudo-Spectral based trajectory optimisation using Levenberg Marquardt algorithm, which is suitable for on board implementation is developed. The algorithm is highly insensitive to initial guess values, exhibiting very good convergence properties. The optimisation scheme is based on sequential quadratic programming. It is tested for robustness with respect to both initial guess and initial condition dispersions in the Monte-Carlo sense and the results are very encouraging.

关键词： Pseudo-Spectral Pinpoint Landing sequential quadratic programming Rapid Trajectory Optimisation Levenberg Marquardt Algorithm

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A high-order partitioned solver for general multiphysics problems and its applications in optimization

A high-order partitioned solver for general multiphysics pro...

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AIAA Science and Technology (SciTech) Forum and Exposition

作者： Huang, Daniel Z. Persson, Per-Olof Zahr, Matthew J. Stanford Univ Inst Computat & Math Engn Durand Bldg Room 226 Stanford CA 94305 USA Univ Calif Berkeley Dept Math Berkeley CA 94720 USA Univ Notre Dame Dept Aerosp & Mech Engn Notre Dame IN 46556 USA

ISBN: (数字)9781624105784

ISBN: (纸本)9781624105784

A high-order accurate adjoint-based optimization framework is presented for unsteady multiphysics problems. The fully discrete adjoint solver relies on the high-order, linearly stable, partitioned solver introduced in [1], where different subsystems are modeled and discretized separately. The coupled system of semi-discretized ordinary differential equations is taken as a monolithic system and partitioned using an implicit-explicit Runge-Kutta (IMEX-RK) discretization[2]. Quantities of interest (QoI) that take the form of space-time integrals are discretized in a solver-consistent manner. The corresponding adjoint equations are derived to compute exact gradients of QoI, which can be solved in a partitioned manner, i.e. subsystem-by-subsystem and substage-by-substage, thanks to the partitioned primal solver. These quantities of interest and their gradients are then used in the context of gradient-based PDE-constrained optimization. The present optimization framework is applied for a 1D fluid-structure-mesh 3-field coupling piston problem and a 2D fluid-structure 2-field coupling foil energy harvesting problem.

关键词： Energy Harvesting Fluid Structure Interaction Finite Volume Method Compressible Fluid Vorticity Discontinuous Galerkin Method Mathematical Models Gas Constant Fluid State sequential quadratic programming

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Computational Modeling of Flutter Constraint for High-Fidelity Aerostructural Optimization

Computational Modeling of Flutter Constraint for High-Fideli...

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AIAA Science and Technology (SciTech) Forum and Exposition

作者： Jonsson, Eirikur Mader, Charles A. Martins, Joaquim R. R. A. Kennedy, Graeme J. Univ Michigan Ann Arbor MI 48109 USA Georgia Inst Technol Sch Aerosp Engn Atlanta GA 30332 USA

ISBN: (数字)9781624105784

ISBN: (纸本)9781624105784

High fidelity computational modeling and optimization of aircraft has the potential to allow engineers to produce more efficient designs, requiring fewer unforeseen design modifications late in the design process. In order for the optimization algorithm to generate a useful design, all the relevant physics must be considered, including flutter. This is especially important for the high-fidelity aerostructural optimization of commercial aircraft, which is likely to result in wing designs that are prone to flutter. To address this issue, we develop a flutter constraint formulation suitable for gradient-based optimization. This paper investigates the feasibility of using a Doublet-Lattice Method (DLM) based flutter constraint for high-fidelity aerostructural optimization. An efficient non-iterative root finding method is developed to compute the flutter eigenvalues from a generalized eigenvalue problem, based on the p-k flutter equation. A mode tracking scheme is implemented at two levels that successfully tracks the mode migration. An effective constraint curve is then developed to define the flutter free flight envelope, in addition to preventing discontinuities in the flutter constraint. This method allows for minimum flutter velocity to be specified implicitly. The Kreisselmeier-Steinhauser (KS) function is used to aggregate the difference of the flutter damping eigenvalues and the constraint curve into a single value that is then used in an optimization. We compute accurate and efficient derivatives of the constraint value with respect to structural sizing variables, as well as wing planform variables. Derivatives are computed using a combination of analytic and automatic differentiation methods in reverse (adjoint) and validated using the complex-step method. To study the behavior of the flutter constraint using this method, we perform a design space analysis and optimize an idealized wing (flat plate) of a rectangular planform.

关键词： High Aspect Ratio Lift to Drag Ratio sequential quadratic programming Commercial Aircraft Structural Damping Aerodynamic Damping Dynamic Pressure Finite Element Analysis Nastran Sparse Nonlinear Optimizer

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