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AIAA Aviation Forum

作者： Bussemaker, J. H. Ciampa, P. D. Nagel, B. DLR German Aerosp Ctr Inst Syst Architectures Aeronaut Hamburg Germany

ISBN: (数字)9781624105982

ISBN: (纸本)9781624105982

Systematic modeling of architecture design spaces is needed when architecting complex systems, to support experts in making less biased decisions, and to formulate the optimization problem needed to explore the large combinatorial design space. Existing methods do not offer enough compatibility with the Model-Based Systems Engineering (MBSE) approaches, cannot model all needed design scenarios, or are not flexible enough when it comes to architecture evaluation. A new method is presented that provides a semantic representation of the architecture design space, modeled as the Architecture Design Space Graph (ADSG). The ADSG represents three types of architectural decisions: function-component mapping, component characterization, and component connection. The ADSG is constructed from a design space definition, and discrete architectural decisions are automatically inserted according to specified rules. Once decisions and metrics have been defined, the hierarchical, mixed-integer, multi-objective optimization problem can be formulated: decisions are mapped to design variables, and performance metrics are mapped to objectives or constraints. An application of the method to the Apollo mission architecting problem is presented.

关键词： Space Exploration Model Based System Engineering Apollo Missions Earth Orbit Rendezvous Optimization Algorithm Crew Member Earth Centrifugal Pump Turbofan multi objective evolutionary algorithms

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Constrained Many-objective evolutionary Extraction Procedure for an OTFT Compact Model including Contact Effects 12

Constrained Many-Objective Evolutionary Extraction Procedure...

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12th Spanish Conference on Electron Devices (CDE)

作者： Romero, A. Gonzalez, J. Jimenez-Tejada, J. A. Univ Granada Granada Spain

ISBN: (纸本)9781538657799

Parameter extraction in organic thin film transistors (OTFTs) is a labour intensive task when contact effects are present. In this work, a constrained many-objective evolutionary parameter extraction procedure is used to determine the parameters of a compact model for the current-voltage characteristics of OTFTs that also includes a model for the contacts. This evolutionary procedure ensures that the extracted parameters comply with the physical meaning on which they are based by adding rules in form of optimization objectives and constrains for the different parameters. The evolutionary procedure is applied to experimental output characteristics of OTFTs. Our numerical results show an excellent agreement with the experimental data.

关键词： thin-film transistor OTFT parameter extraction device parameters modeling TFT modeling contact effects many-objective optimization multi-objective optimization multi objective evolutionary algorithms

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Optimization of the Aerodynamic and Aeroacoustic Performance of an Axial-Flow Fan

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AIAA JOURNAL 2014年第9期52卷 2032-2044页

作者： Kim, Jin-Hyuk Ovgor, Bavuudorj Cha, Kyung-Hun Kim, Joo-Hyung Lee, Seungbae Kim, Kwang-Yong Inha Univ Korea Inst Ind Technol Inchon 402751 South Korea Inha Univ Natl Renewable Energy Ctr Mongolia Inchon 402751 South Korea Inha Univ Dept Mech Engn Inchon 402751 South Korea

A multidisciplinary optimization to simultaneously enhance the aerodynamic and aeroacoustic performance of an axial-flow fan was performed. Flow analysis through the axial-flow fan was conducted by solving three-dimensional steady and unsteady Reynolds-averaged Navier-Stokes equations with the shear-stress transport turbulence model. Starting with the results for the unsteady flow, aeroacoustic analysis was performed by solving the Ffowcs Williams-Hawkings equations. A single-objective optimization for high-efficiency design was carried out before the multi-objective optimization. The single-objective optimization was conducted using a weighted average surrogate model with five design variables defining the hub-to-tip ratio, hubcap installation distance, hubcap ratio, and angle distributions at the midspan and blade tip. The objective function (i.e., the efficiency) was evaluated at the design points, sampled by Latin hypercube sampling in the design space, to construct the surrogate model. Then, multi-objective optimization on the basis of the single-objective optimization result was performed to simultaneously improve the efficiency and reduce the sound pressure level through a hybrid multi-objective evolutionary algorithm coupled with a response surface approximation surrogate model with two design variables defining the sweep and lean angles at the blade tip. These objective functions were numerically accessed through the aerodynamic and aeroacoustic analyses. Arbitrary selected optimum designs in the Pareto-optimal solutions yielded increases in efficiency and decreases in the sound pressure level compared to the reference design.

关键词： Numerical Analysis Reynolds Averaged Navier Stokes Sound Pressure Level multi objective evolutionary algorithms Shear Stress Turbulent Flow Turbulence Models Turbomachinery Design Rotor Stator Interactions Static Pressure

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Thermal Performance Analysis and Optimization of Microjet Cooling of High-Power Light-Emitting Diodes

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JOURNAL OF THERMOPHYSICS AND HEAT TRANSFER 2013年第2期27卷 235-245页

作者： Husain, Afzal Kim, Sun-Min Kim, Jun-Hee Kim, Kwang-Yong Inha Univ Dept Mech Engn Inchon 402751 South Korea

The present study investigates the thermal and hydraulic performance of the microjet array cooling system for thermal management of a high-power light-emitting diode array. Three-dimensional numerical analyses were performed for steady incompressible turbulent flow and conjugate heat transfer through a finite volume solver. The performances of several microjet array configurations, viz., 1-jet, 4-jet, 9-jet, 13-jet, and 16-jet arrays, were analyzed at two flow rates and top-cavity heights. The design optimization of a 4-jet array cooling system was performed using a multi-objective evolutionary algorithm. For the optimization, two design variables, viz., ratio of the nozzle diameter and height of the top cavity and ratio of the height and length of the top cavity, were selected. The thermal resistance and pressure drop were selected as the objective functions of the design. The Pareto-optimal solutions were obtained and discussed in view of the thermal resistance and pressure drop and sensitivity of design variables to objective functions.

关键词： Thermal Performance Diodes Heat Transfer Coefficients multi objective evolutionary algorithms Thermal Management Turbulent Flow Numerical Modeling Thermoelectric Cooling Total Mass Flow Rate Heat Transfer Fluid

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Comparison of Optimization Strategies for High-Lift Design

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JOURNAL OF AIRCRAFT 2017年第2期54卷 642-658页

作者： Iannelli, Pierluigi Moens, Frederic Minervino, Mauro Ponza, Rita Benini, Ernesto Ctr Italiano Ric Aerosp Fluid Mech Dept Aerodynam Technol & Icing Lab I-81043 Capua Italy Off Natl Etud & Rech Aerosp Appl Aerodynam Dept F-92190 Meudon France Piaggio Aero Ind Res & Dev Dept I-17038 Villanova Dalbenga Italy Ctr Italiano Ric Aerosp Fluid Mech Dept Multidisciplinary Anal & Design Lab I-81043 Capua Italy Univ Padua Dept Ind Engn I-35131 Padua Italy

The design of high-lift systems represents a challenging task within the aerospace community, being a multidisciplinary, multi-objective, and multipoint problem. The Design, Simulation and Flight Reynolds Number Testing for Advanced High-Lift Solution project, funded by the European Commission under the Seventh Framework Programme, aimed at improving the aerodynamics of high-lift systems by developing, in a coordinated approach, both efficient numerical design strategies and measurement techniques for cryogenic conditions. Within the Design, Simulation and Flight Reynolds Number Testing for Advanced High-Lift Solution project, different partners used several numerical automatic optimization strategies for high-lift system design purposes. A realistic multi-objective and multipoint optimization problem was defined and solved by adopting different flow model dimensionality, meshing techniques, geometry parameterization, and optimization strategies. Special attention was devoted to perform a fair comparison of the results, and useful information was obtained about trends, pros, and cons of the approaches used. The outcome of these activities is that an efficient design process can be set up through decoupling of the original multi-objective problem into several, sequential suboptimization processes. Nevertheless, several decoupling possibilities exist, and the most efficient one can be identified only on the bases of preanalysis or preknowledge of the specific problem. Second, the exercise carried out demonstrated the maturity and feasibility of a full three-dimensional automatic high-lift design.

关键词： Aerodynamic Force Coefficients CFD Simulation Aerodynamic Efficiency Flap Deflection Reynolds Averaged Navier Stokes multi objective evolutionary algorithms multi objective Genetic Algorithm Two Dimensional Flow Optimization Algorithm Navier Stokes Solver

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Microchannel heat sink with designed roughness: Analysis and optimization

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JOURNAL OF THERMOPHYSICS AND HEAT TRANSFER 2008年第3期22卷 342-351页

作者： Husain, Afzal Kim, Kwang-Yong Inha Univ Dept Mech Engn Inchon 402751 South Korea

A microchannel heat sink with rib structures is investigated numerically for thermal resistance and pumping power. multi-objective shape optimization of a staggered-rib microchannel heat sink is performed using a multi-objective evolutionary algorithm. Three design variables (i.e., ratios of the rib height to width of channel, width to height of the rib, and channel width to pitch of the rib) are selected for optimization. Thermal resistance and pumping power are taken as objective functions. Navier-Stokes and energy equations for laminar flow and conjugate heat transfer are solved for How analyses using a finite volume solver. Thermal resistance is decreased and the Nusselt number is increased at the expense of pressure drop in a ribbed microchannel. Thermal resistance in a ribbed channel is generally higher than that in a smooth channel for fixed pumping power, but the difference in thermal resistance reduces as pumping power increases. The design variable of the ratio of rib height to width of channel is primarily responsible for and the most sensitive to the heat transfer augmentation, whereas ratios of width to height of the rib and channel width to pitch of the rib are found to be less sensitive in the design space. The ratio of channel width to pitch of the rib is found to be the most Pareto-sensitive (sensitive along the Pareto-optimal front), whereas the ratio of width to height of the rib is found to be the least Pareto-sensitive.

关键词： Microchannel Heat Exchanger Thermal Resistance Heat Transfer Enhancement Techniques Numerical Modeling Mass Flow Rate Shear Layers Conservation of Mass Fractional Factorial Design High Aspect Ratio multi objective evolutionary algorithms

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Optimization of Rotating Cooling Channel with Pin Fins Downstream of Turning Region

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JOURNAL OF THERMOPHYSICS AND HEAT TRANSFER 2012年第1期26卷 85-97页

作者： Moon, Mi-Ae Kim, Kwang-Yong Inha Univ Dept Mech Engn Inchon 402751 South Korea

The heat transfer performance of a rotating two-pass rectangular channel with staggered pin-fin arrays is optimized through Reynolds-averaged Navier-Stokes analysis, a surrogate method, and a multi-objective evolutionary algorithm. As the Pareto-optimal front produces a set of optimal solutions, the trends in the objective functions in relation to the design variables are predicted by a hybrid multi-objective evolutionary algorithm. Two objective functions related to heat transfer and friction loss, respectively, have been considered to estimate the performance of the cooling channel in turbine blades. Two design variables are selected, viz., the ratio of the diameter to height of the pin fins and the ratio of the streamwise spacing between the pin fins to height of the pin fins, and 20 designs are generated by Latin hypercube sampling. A response surface approximation model as a surrogate model is constructed for each objective function, and a hybrid multi-objective evolutionary algorithm is applied to obtain the Pareto-optimal front. The Reynolds number that is based on the hydraulic diameter of the channel is fixed at 10,000, while the rotation number is held constant at 0.15. The turning region upstream of the pin fins enhances the heat transfer through the channel, since a strong vortical flow structure is created in this region. At some optimal points on the Pareto-optimal front, it is found that the present multi-objective optimization enhances both the heat transfer performance and the pressure-loss characteristics. The effects of the rotation number on the heat transfer and pressure loss are also discussed.

关键词： Enhancing Heat Transfer Rate Reynolds Averaged Navier Stokes multi objective evolutionary algorithms multigrid Methods Reynolds Number Turbine Inlet Temperature Friction Factor Aspect Ratio Horseshoe Vortex Coolant

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Optimum Operating Parameters and Blade Setting of a High-Speed Propeller

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JOURNAL OF AIRCRAFT 2022年第2期59卷 484-501页

作者： Boulkeraa, Tayeb Ghenaiet, Adel Benini, Ernesto Polytech Mil Sch Fac Mech Engn & Proc Engn Lab Energy Convers Syst Bordj El Bahri 16046 Algeria Univ Sci & Technol Houari Boumediene Lab Turbomachinery Fluid Mech & Energet Dept Bab Ezzouar 16111 Algeria Univ Padua Dept Ind Engn Via Venezia 1 I-35131 Padua Italy

Traditionally, the design of propellers is accomplished on the bases of engineering experience and the availability of well-established experimental data. However, the emergence of computational fluid dynamics (CFD) tools coupled with advanced optimizers has made this task easier. This paper presents the essentials of an optimization-based CFD chain aimed at finding the optimal operating parameters and blade settings of a high-speed propeller. This fully automated procedure combines an improved hypercube sampling (IHS) for the initial design of experiment and a radial basis function (RBF) as the meta-model, hence leading to lesser CFD simulations. The coupling between IHS and RBF is judiciously implemented, and the sampling strategy and updates are thoroughly examined. The optimization procedure uses the multi-objective evolutionary algorithm nondominated sorting genetic algorithm to determine the operating parameters and blade setting that maximize the propeller efficiency and thrust. At the optimum point the blade operates with mild pressure gradients, whereas the transonic region is restricted to the upper corner of the blade tip.

关键词： High Speed Propellers Large Eddy Simulation multi objective evolutionary algorithms Genetic Algorithm Design of Experiments Freestream Conditions Reynolds Averaged Navier Stokes Blade Element Momentum Theory Aerodynamic Efficiency Optimization Algorithm

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Technique for Concept Selection Using Interactive Probabilistic multiple Attribute Decision Making

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JOURNAL OF AEROSPACE COMPUTING INFORMATION AND COMMUNICATION 2009年第1期6卷 51-67页

作者： Biltgen, Patrick T. Mavris, Dimitri N. Georgia Inst Technol Sch Aerosp Engn ASDL Atlanta GA 30332 USA

Design is a decision-making process that depends on multiple attributes. Analysis of alternatives with respect to a single metric representing the "goodness" of the concept is difficult without resorting to subjective weightings on an overall evaluation criterion. The use of subjective factors in a decision-making process is often met with criticism, as the selection of a design may be traced to preferential decisions made on a certain day by a single individual. A methodology is needed that reduces the impact of uncertainty in the subjective weighting factors while retaining the traceability, defensibility, and rigor provided by traditional multiple attribute decision-making techniques. In this work, a standard process for systems engineering using the quality function deployment approach with a multiple attribute decision-making technique for concept selection is supplemented through the use of parametric slide bars to play "what-if" games and a probabilistic environment that plays all possible "what-if" games and summarizes the results. Using the modified process, families of concepts can be rapidly examined based on varying levels of subjective preferences. Decision makers, armed with a rapid parametric sensitivity analysis tool, can make more informed decisions about future concepts, policies, and acquisition decisions. An interactive graphical environment can be used to visualize the diverse sets of trades and understand non-intuitive answers by tracing customer needs to proposed solutions in real-time. In practice, the proposed process facilitates iteration between needs and concepts and fosters and increased understanding of the concept space between designer and decision maker.

关键词： Systems Engineering Zero Lift Drag Coefficient Sensitivity Analysis Probability Density Functions Missile Design Propellant Transport Aircraft multi objective evolutionary algorithms RADAR Space and Missile Systems Center

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Surrogate-Assisted Differential Evolution Using Knowledge-Transfer-Based Sampling for Expensive Optimization Problems

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AIAA JOURNAL 2022年第5期60卷 3251-3266页

作者： Long, Teng Ye, Nianhui Shi, Renhe Wu, Yufei Tang, Yifan Beijing Inst Technol Sch Aerosp Engn Beijing Peoples R China Beijing Inst Technol Key Lab Dynam & Control Flight Vehicle Minist Educ Beijing 100081 Peoples R China Simon Fraser Univ Sch Mech Syst Engn Surrey BC V3T 0A3 Canada

To sufficiently reuse the knowledge from previous optimization efforts, a surrogate-assisted differential evolution using knowledge-transfer-based sampling (denoted as SADE-KTS) method is proposed for solving expensive black-box optimization problems. In SADE-KTS, a novel knowledge-transfer-based sampling method is integrated with the differential evolution framework to generate promising initial sample points. In this way, a least-squares support vector machine classifier is constructed based on the prior optimization knowledge database to calibrate the initial sample points adaptively, which improves the exploration performance via transferring the existed optimization efforts to the current optimization task. Moreover, the radial basis function and kriging surrogates are employed to replace the expensive simulation models for evolutionary operations, where the tailored differential evolution operators are cooperated with the sequential quadratic programming optimizer to lead the search to the global optimum efficiently. A number of numerical benchmarks are tested to illustrate the optimization capacity of SADE-KTS compared with several competitive optimization algorithms. Finally, SADE-KTS is applied to an airfoil aerodynamic knowledge-based optimization problem considering the existed optimization knowledge, which demonstrates the practicality and effectiveness of the proposed SADE-KTS in engineering practices.

关键词： Airfoil Sequential Quadratic Programming Support Vector Machine Black Box Numerical Simulation multi objective evolutionary algorithms Lagrange multipliers Lift Coefficient Finite Element Analysis multidisciplinary Design Optimization

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