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A Reduced-order model for Aerodynamic Shape Optimization

A Reduced-order model for Aerodynamic Shape Optimization

引用

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 ...

引用

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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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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Optimal Orbital Plane Change by the Heating-Rate-Constrained Aerocruise 38

Optimal Orbital Plane Change by the Heating-Rate-Constrained...

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38th Chinese Control Conference (CCC)

作者： Fu, Jun Beijing Inst Tracking & Telecommun Technol Beijing 100094 Peoples R China

ISBN: (纸本)9789881563972

There are mainly two types of synergetic maneuvers for aeroassisted orbital transfer, which are called aeroglide and aerocruise. Aerocruise mode is considered as means for maximizing the plane change of a circular orbit by considering heating rate when the vehicle maneuvers from high Earth orbit to low Earth orbit. For aerocruise, the maneuver is divided into three phases: descent. cruise, and ascent. In cruise mode the vehicle flies at a constant altitude when thrust is used to cancel the drag and the heating rate is effectively restrained. The heating-rate-constrained aerocruise scheme which consists of cruise altitude, cruise velocity and angle of attack are optimized by using sequential quadratic programming (SQP). The effectivity of the algorithm and existence of the optimal solution are both validated by simulation experiments. Numerical results show that the orbital change ability is closely related to the maximum allowable heating rate. The maximum plane change is obtained when the vehicle remains on the heating-rate boundary. The optimality of the aerocruise maneuver is guaranteed by considering the optimized aerocruise scheme as performance index of descent trajectory optimization.

关键词： Orbital change aerocruise sequential quadratic programming trajectory optimization aeroassisted orbital transfer

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A new Method for Dynamic Economic Emission Dispatch Problem

A new Method for Dynamic Economic Emission Dispatch Problem

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IEEE Congress on Evolutionary Computation (IEEE CEC)

作者： Huang, Chia-Ling Jao, Chen-Wei Zhang, Xianyong Yeh, Wei-Chang Chung, Vera Yuk Ying Wang, Jinhai Yang, Jun Jiang, Yun-Zhi Kainan Univ Dept Logist & Shipping Management Taoyuan 33857 Taiwan Natl Tsing Hua Univ Dept Ind Engn & Engn Management Hsinchu 300 Taiwan Guangdong Polytech Normal Univ Sch Automat Guangzhou Guangdong Peoples R China Natl Tsing Hua Univ Dept Ind Engn & Engn Management Integrat & Collaborat Lab Hsinchu 300 Taiwan Univ Sydney Sch Informat Technol Sydney NSW 2006 Australia Foshan Univ Coll Elect & Informat Engn Foshan 528000 Peoples R China South China Univ Technol Sch Math Guangzhou Guangdong Peoples R China Guangdong Polytechn Normal Univ Sch Math & Syst Sci Guangzhou 510006 Guangdong Peoples R China

ISBN: (纸本)9781728121536

The Dynamic Economic Emission Dispatch Problem (DEED) is a well-known problem in the study of thermal power generation. The goal of the DEED is to meet the demand change by arranging the capacities of power generators to reduce fuel cost and emission. In recent years, the high environmental awareness, the decreasing petrochemical energy, and the increasing energy demand such that the DEED is more important and popular than before. Most of algorithms for the DEED are either limited by less than ten power generators or without considering the power generation limit. The former is impractical due to that the number of power generators in current thermal power plants can be up to 14;the latter results in infeasible solutions. To overcome the above two obstacles, a new algorithm called the SSO-DE-SQP hybrid with the Simplified Swarm Optimization (SSO), Differential Evolution (DE), and sequential quadratic programming (SQP) is developed to solve the larger-size DEED with the power generation limit. The performance of the SSO-DE-SQP is demonstrated by comparing with two existing well-known methods: DE-SQP and PSO-SQP with up to 15 generators for the DEED.

关键词： Dynamic Economic Emission Dispatch Problem Fuel cost and Emission Simplified Swarm Optimization Differential Evolution algorithm sequential quadratic programming

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Structural Topology Optimisation with R-Snakes Volume of Solid

Structural Topology Optimisation with R-Snakes Volume of Sol...

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AIAA Science and Technology (SciTech) Forum and Exposition

作者： Taylor, Alexander D. J. Payot, Alexandre D. J. Allen, C. B. Rendall, Thomas 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)9781624105784

ISBN: (纸本)9781624105784

A topologically flexible parameterisation method developed for aerodynamic optimisation is tested on a variety of 2 dimensional structural topology problems. The background to the restricted snakes volume of solid (RSVS) is explained. A topology optimisation framework is develloped using FreeFem++ as a linear elastic solver and differential evolution as the agent based optimiser. Validation of the analysis is presented as well as mesh convergence and impact studies. The work here is significant such that if a parameterisation method is capable of both aerodynamic and structural optimisation, the potential for multidisciplinary analysis arises. Structural topology optimisation of volume constrained agent-based optimisation, minimising deflection, has been run on four common benchmark cases;two short cantilever beams and two longer centrally loaded (MBB) beams. Results were compared to SIMP calculations made following using Sigmund's 99 line topology optimisation code [1]. RSVS solutions scored objective functions comparable to those found via SIMP in all cases with differences ranging from +40% to -5%. In the long run the combined capability of the RSVS in aerodynamics and structures offers the potential of the development of a general aero-structural topology optimisation framework using a single set of design variables.

关键词： Numerical Optimization Structural Optimization Cantilever Beam Aerodynamic Shape Optimization sequential quadratic programming Aspect Ratio Biaxial Stress Finite Element Analysis Poisson's Ratio Aircraft Configurations

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Using Graph Coloring To Compute Total Derivatives More Efficiently in OpenMDAO

Using Graph Coloring To Compute Total Derivatives More Effic...

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AIAA Aviation Forum and Exposition

作者： Gray, Justin S. Hearn, Tristan A. Naylor, Bret A. NASA Glenn Res Ctr Cleveland OH 44139 USA DB Consulting Corp Bethesda MD USA

ISBN: (数字)9781624105890

ISBN: (纸本)9781624105890

When they are applicable, gradient based optimization algorithms are the most efficient way to solve design optimization problems. Although gradient based methods are generally efficient, they can be made significantly more so through the usage of analytic techniques to compute the necessary total derivatives. The traditional forward (direct) and reverse (adjoint) analytic techniques have computational costs that scale linearly with the number of design variables and the number of constraints, respectively. In this work, we present an application of a graph coloring algorithm to the analytic techniques for computing total derivative Jacobians in order to achieve much better computational scaling than the pure analytic methods can provide alone. A detailed theoretical explanation of how coloring algorithms interact with analytic derivative methods is presented that illustrates specific types of sparsity patterns that must be present in total derivative Jacobians in order for this coloring technique to be effective. The new technique has been implemented as a feature in the OpenMDAO framework and the implementation is demonstrated on two example problems. The performance on the example problems up to 50% reduction in compute cost for optimizations with bi-directional coloring compared to traditional constraint aggregation. Additionally, the results show how coloring technique alleviates some of the numerical difficulties that constraint aggregation can cause, leading to the ability to solve larger problems. It is expected that the new method will have wide applicability to multidisciplinary optimization problems, and that its availability in OpenMDAO will offer significant computational savings for users without the need for them to implement the coloring algorithm themselves.

关键词： Computing sequential quadratic programming Computing Cost Air Traffic Control Optimal Control Structural Optimization Numerical Integration Computational Fluid Dynamics Finite Element Analysis Velocity Profiles

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Improving Ride-Comfort of a Quarter-Car Model using Modal Control 7

Improving Ride-Comfort of a Quarter-Car Model using Modal Co...

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7th IEEE International Conference on Control, Mechatronics and Automation(ICCMA)

作者： Dogruer, C. U. Hacettepe Univ Dept Mech Engn Ankara Turkey

ISBN: (纸本)9781728137872

In this paper, modal control was used to control the active suspension of a quarter-car model. Modal control can be designed to alter the dynamics of any mode of a system without disturbing the remaining modes. Therefore, in this study, modal control was used to alter the complex eigenvalue of the body-bounce mode of a quarter-car suspension model and thereby by optimizing a measure of the frequency response functions from road disturbance to sprung and unsprung mass displacements, the ride-comfort of a vehicle was improved. It has been shown that modal control can be used in a direct manner to change the dynamics of a vehicle suspension i.e. soft suspension, stiff suspension depending on the driver attitude that affects the vehicle stability and road conditions i.e. urban driving, off-road driving.

关键词： Quarter-Car Model Active Suspension Modal Control MM-Max Optimization sequential quadratic programming

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