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Some results on the design of brushless DC wheel motor using SQP and GA

INTERNATIONAL JOURNAL OF APPLIED ELECTROMAGNETICS AND MECHANICS 2007年第3-4期26卷 233-241页

作者： Moussouni, F. Brisset, S. Brochet, P. Ecole Cent Lille L2EP F-59651 Villeneuve Dascq France

The sequential quadratic programming and genetic algorithms are finely tuned on the optimal design of a brushless DC wheel motor. Combining both methods, a hybrid approach is tested. Multiobjective optimizations are performed using Nondominated Sorting Genetic Algorithm, Strength Pareto Evolutionary Algorithm, and a variable weighted sum of objectives with the sequential quadratic programming. The Pareto fronts are compared in term of accuracy, uniformity, and coverage criteria using some quality indicators.

关键词： sequential quadratic programming genetic algorithms mixed-integer optimization multiobjective optimization

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Nonlinear semidefinite programming: sensitivity, convergence, and an application in passive reduced-order modeling

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MATHEMATICAL programming 2007年第2-3期109卷 581-611页

作者： Freund, Roland W. Jarre, Florian Vogelbusch, Christoph H. Univ Dusseldorf Inst Math D-40225 Dusseldorf Germany Univ Calif Davis Dept Math Davis CA 95616 USA

We consider the solution of nonlinear programs with nonlinear semidefiniteness constraints. The need for an efficient exploitation of the cone of positive semidefinite matrices makes the solution of such nonlinear semidefinite programs more complicated than the solution of standard nonlinear programs. This paper studies a sequential semidefinite programming (SSP) method, which is a generalization of the well-known sequential quadratic programming method for standard nonlinear programs. We present a sensitivity result for nonlinear semidefinite programs, and then based on this result, we give a self-contained proof of local quadratic convergence of the SSP method. We also describe a class of nonlinear semidefinite programs that arise in passive reduced-order modeling, and we report results of some numerical experiments with the SSP method applied to problems in that class.

关键词： nonlinear semidefinite programming sequential quadratic programming sensitivity reduced-order modeling positive realness

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Thermal optimal design for heat sinks or heat sink/TEC assemblies in a ducted flow

Thermal optimal design for heat sinks or heat sink/TEC assem...

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ASME InterPACK Conference

作者： Wu, T. Y. Wu, M. C. Homg, J. T. Chang, S. F. Chen, P. L. Hung, Y. H. Natl Tsing Hua Univ Dept Power Mech Engn Hsinchu Taiwan

ISBN: (纸本)9780791842782

A series of experimental studies on the heat transfer characteristics from heat sinks or Heat Sink/TEC assemblies in a ducted flow have been performed. Their effects on heat transfer characteristics in ducted flow have been systematically explored. From the results, new performance correlations of the temperature difference (AT) and terminal voltage (P) of the TEC modules are proposed. Besides, two new correlations of steady-state average Nusselt number and external thermal resistance in terms of relevant influencing parameters for confined ppf heat sinks in a ducted flow are also proposed, respectively. The statistical sensitivity analysis of ANOVA F-test is employed to estimate the contributions of relevant parameters. Furthermore, a series of RSM models for evaluating heat transfer characteristics including average Nusselt number, average external thermal resistance and T-c -T-a are established. A sequential quadratic programming with multi-starting-point method is successfully employed to automatically and efficiently seek a globally optimal thermal performance. An optimal design of HS/TEC assemblies under both COP : 2 and pumping power limitation larger than 30 W can be achieved with a reduction of 75% on thermal resistance.

关键词： HS/TEC assembly ducted flow thermal resistance COP pumping power sensitivity analysis response surface methodology sequential quadratic programming thermal optimal design

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Some results on the design of brushless DC wheel motor using SQP and GA

Some results on the design of brushless DC wheel motor using...

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9th International Workshop on Optimization and Inverse Problems in Electromagnetism

作者： Moussouni, F. Brisset, S. Brochet, P. Ecole Cent Lille L2EP F-59651 Villeneuve Dascq France

关键词： sequential quadratic programming genetic algorithms mixed-integer optimization multiobjective optimization

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A new SQP based space-mapping algorithm for on-chip spiral inductor optimization

A new SQP based space-mapping algorithm for on-chip spiral i...

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20th Annual Canadian Conference on Electrical and Computer Engineering

作者： Arbabi, Navid Najmabadi, Mani Devabhaktuni, Vijay Yagoub, Mustapha Concordia Univ Dept ECE Montreal PQ Canada Univ Ottawa SITE Ottawa ON K1N 6N5 Canada

ISBN: (纸本)9781424410200

Computer aided design (CAD) and optimization of on-chip spiral inductors is of immense interest to RFIC designers. Traditional optimization methods rely on approximate/fast "coarse models" of spiral inductors, eg. equivalent circuits, empirical equations, etc. Naturally, the accuracy/validity of optimized results from such methods depends highly on the quality of the coarse models used. Further, the inability of such models to account for full-wave electromagnetic (EM) effects, limits their application to low-frequency circuit designs and/or necessitates additional efforts to formulate an acceptable optimization objective. The pressing need for first-pass success of CAD tools in terms of inductor design mandates consideration of full-wave EM effects within the CAD framework. Space-mapping optimization combines the speed of circuit models and the accuracy of EM simulations. In this paper, we propose a new space-mapping optimization algorithm, which exploits the sequential quadratic programming (SQP) technique for coarse model optimization. Starting with the user-specifications of the spiral inductor, the proposed algorithm yields an acceptable spiral inductor design/layout for RFIC design. The algorithm is illustrated via an on-chip spiral inductor optimization example.

关键词： computer aided design EM optimization RFICs space-mapping sprial inductors sequential quadratic programming

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Robust design with dynamic characteristics using stochastic sequential quadratic programming

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ENGINEERING OPTIMIZATION 2003年第1期35卷 79-89页

作者： Chen, SP Natl Chung Cheng Univ Dept Business Adm Chiayi 621 Taiwan

Robust design with dynamic characteristics is an important oft-line quality engineering technique for improving product quality over a range of input conditions by reducing variations caused by uncontrolled factors. Since several studies have indicated that there are important limitations to Taguchi's S/N ratio analysis, the solution procedure for dynamic systems deserves further investigation. This paper proposes a stochastic optimization modeling procedure to overcome the difficulty in Taguchi's method to accommodate dynamic characteristics. The main idea underlying the proposed method is to minimize the total variations on quality characteristics while attaining the target performance over a range of input conditions. Due to the nonlinear nature of the stochastic optimization model, two stochastic versions of sequential quadratic programming respectively embedded with a Monte Carlo simulation and numerical approximations are devised to solve the problem. In the robust design of a temperature control circuit often discussed in dynamic problems, the proposed method performs efficiently and effectively. Compared with the Taguchi method, the design solved in this paper has smaller variations, indicating that the proposed method is a promising technique for dynamic-characteristic robust design.

关键词： dynamic characteristics Monte Carlo simulation robust design sequential quadratic programming

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Dynamics of circularly towed cable systems, Part 1: Optimal configurations and their stability

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JOURNAL OF GUIDANCE CONTROL AND DYNAMICS 2007年第3期30卷 753-765页

作者： Williams, Paul Trivailo, Pavel RMIT Univ Sch Aerosp Mech & Mfg Engn Melbourne Vic 3083 Australia

When a long cable. is towed in a circular flight path, the system can exhibit quasi-stationary solutions for which the cable tip appears to remain stationary relative to the orbiting aircraft. For applications involving pickup and delivery of payloads, tighter turns at high speeds lead to nearly stationary motion of the cable tip in an inertial frame. This work studies the dynamics of such a system, focusing on the stability and equilibria of solutions. A numerical analysis of the system is carried out using a discretized lumped mass model of the cable. By using constrained numerical optimization, practical towing solutions that achieve small motion of the towed body are obtained.

关键词： Aerodynamic Force Aerodynamic Performance Light Aircraft Aircraft Configurations Flight Testing Aircraft Performance Aircraft Altitude Ultimate Tensile Strength sequential quadratic programming Aircraft Towing

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Design and control of libration point spacecraft formations

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JOURNAL OF GUIDANCE CONTROL AND DYNAMICS 2007年第4期30卷 899-909页

作者： Infeld, Samantha I. Josselyn, Scott B. Murray, Walter Ross, I. Michael Stanford Univ Stanford CA 94305 USA USN Postgrad Sch Monterey CA 93943 USA

We investigate the concurrent problem of orbit design and formation control around a libration point. Concurrency implies that the design and control problem are simultaneously investigated. Separating the two problems is both unnecessary and ill-advised. The full problem can be naturally cast as a multi-agent, nonlinear, constrained optimal control problem. The optimality criterion is fuel consumption because the engineering feasibility of a formation design is dominated by the amount of propellant required to maintain a formation. Contrary to popular belief, quadratic costs do not measure fuel consumption;consequently, we take a direct measure of fuel consumption given by the L-t norm of the control acceleration. Fuel budgets to individual spacecraft are allocated by isoperimetric constraints. As with most nonlinear problems, the resulting problem does not have closed-form solutions. The full problem is solved by a Legendre pseudospectral method implemented in DIDO. DIDO exploits SNOPT, an active-set sequential quadratic programming solver, and generates quick solutions to facilitate redesign, an important requirement during the early stages of formation design. This approach does not use linearizations in modeling the dynamics, nor does it require analytical results;rather, the inherent nonlinearities associated with the problem are automatically exploited. Furthermore, we take advantage of a true distributed system architecture that does not rely on designing a leader-follower system. Sample results for formations about the sun-Earth and Earth-moon L2 point in the three-body circular restricted dynamical framework are presented. Optimal solutions for relaxed and almost periodic formations are presented for both a large separation constraint (about a third to half of orbit size), and a small separation constraint (about a millionth of orbit size).

关键词： Astronomical Unit Spacecraft Formation Covector Mapping Principle Earth Propellant Fuel Consumption sequential quadratic programming Legendre Pseudospectral Method Orbital Elements MATLAB

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Unpowered approach and landing guidance with normal acceleration limitations

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JOURNAL OF GUIDANCE CONTROL AND DYNAMICS 2007年第3期30卷 882-885页

作者： Kluever, C. A. Univ Missouri Columbia MO 65211 USA

An approach and landing (A&L) guidance scheme for an unpowered reusable launch vehicle (RLV) with diminished maneuverability in the vertical plane, is presented. The guidance method computes a new reference trajectory such that load factor is minimized during the A&L phase. Trajectory planning is done by performing a series of 1-D searches by iterating on a single guidance parameter and numerically propagating multiple paths to touchdown conditions. The guidance algorithm determines the minimum constant equilibrium-glide load factor such that the flight-path angle is continually increased during the A&L phase. The corresponding A&L trajectory of the calculated minimum load factor is used as the reference path for a closed-loop guidance scheme. The guidance method is a feasible technique for onboard generation of a new reference A&L trajectory.

关键词： Flight Path Angle Reusable Launch Vehicle Airspeed Proportional Integral Derivative Lift Coefficient Aerodynamic Coefficients Numerical Integration Dynamic Pressure sequential quadratic programming Guidance Algorithms

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Design "feasilization" using knowledge-based engineering and optimization techniques

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JOURNAL OF AIRCRAFT 2007年第6期44卷 1776-1786页

作者： Schut, E. J. van Tooren, M. J. L. Delft Univ Technol Fac Aerosp Engn NL-2629 HS Delft Netherlands

The multidisciplinary design optimization process can be supported by partial automation of analysis and optimization steps. Design-and-engineering engines are a useful concept to structure this automation. Within the design-and-engineering engines, a product is parametrically defined using knowledge-based engineering. This parametric product model needs to be initiated before global multidisciplinary optimization can be performed. The "feasilization" is done by the initiator component in the design-and-engineering engines that simulates the heuristic methods normally used by designers to estimate the first values for the parameters and variables describing their designs. The initiation of values for structural parameters and variables is elaborated for a sample composite-stiffened panel structure. It is shown that the initiator function of the design-and-engineering-engine concept can be implemented on the basis of optimization techniques using sirnplification of the design requirements, simplified representations of the design options, and the class of so-called schematic models to mimic the designer's job in the preliminary sizing phase of the design. An implementation of the initiator is used in a sample design-and-engineering engine for aircraft vertical tail design.

关键词： Finite Element Modeling Buckling Analysis Aircraft Configurations Nastran Maximum Shear Stresses sequential quadratic programming Multidisciplinary Design Optimization Structural Response Wing Configurations Airbus

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