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Euler/Navier-Stokes optimization of supersonic wing design eased on evolutionary algorithm

AIAA JOURNAL 1999年第10期37卷 1327-1328页

作者： Oyama, A Obayashi, S Nakahashi, K Nakamura, T Tohoku Univ Dept Aeronaut & Space Engn Nakahashi Lab Sendai Miyagi 9808579 Japan Natl Aerosp Lab Dept Aeronaut & Space Engn Tokyo 1828522 Japan

An evolutionary algorithm (EA) coupled with a Euler/Navier-Stokes code has been applied to supersonic wing shape design. Aerodynamic evaluations are distributed to the processing elements (PE) of the numerical wind tunnel (NWT) to overcome the enormous computational time necessary for the optimization. The design yields both the minimum drag and the minimum volume wave drag in the given design space. The important features of supersonic wing design as compared with conventional transonic wing design are presented.

关键词： Evolutionary algorithm Aerodynamic Design Aerodynamic Performance Wing Root National Aerospace Laboratories optimization algorithm Aeroplane Camber Numerical optimization Spline Interpolation

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Airfoil and wing design through hybrid optimization strategies

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AIAA JOURNAL 1999年第5期37卷 634-641页

作者： Vicini, A Quagliarella, D Ctr Italiano Ric Aerospaziali Aerodynam & Prop Dept I-81043 Capua Italy

Real-world design problems need robust and effective system level optimization tools inasmuch as they are ruled by several criteria, most often in multidisciplinary environments. In this work a hybrida* optimization algorithm has been obtained by adding a gradient-based technique to the set of operators of a multiobjective genetic algorithm. This makes it possible to increase the computational efficiency of the genetic algorithm while preserving its favorable features of robustness, problem independence, and multiobjective optimization capabilities. Aerodynamic shape design problems, including both airfoil and wing designs, are considered.

关键词： NACA 0012 Genetic algorithm optimization algorithm Aerodynamic Characteristics Aspect Ratio Swept Wing Angle of Attack Sweep Angle Structural Weight Wing Root

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Design optimization of phased-array-fed reflector antennas for mobile communication satellites

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JOURNAL OF SPACECRAFT AND ROCKETS 1999年第1期36卷 105-108页

作者： Tokunaga, K Tsunoda, H Shoki, H Okumura, M Adv Space Commun Res Lab On Board Antenna Technol Sect Chiyoda Ku Tokyo 1010032 Japan Toshiba Corp Ctr Res & Dev Commun & Informat Syst Res Labs Saiwai Ku Kawasaki Kanagawa 2108581 Japan Toshiba Corp Komukai Works Saiwai Ku Kawasaki Kanagawa 2108581 Japan

A satellite antenna system for satellite communications requires high gain and effective transmission power use. To satisfy these requirements, we studied a phased-array-fed reflector antenna for multiple beams, particularly the optimization method to design antenna parameters and to determine the array weight distributions for high gain, low side-lobe levels, and efficient amplifier use. The results of our analytical study and experiment model test clarified the electrical performance and verified the optimum design method. We also studied the effects of the weighting error, given to the optimized weighting distribution, which have a significant effect on the antenna performance.

关键词： Reflector Antennas Asia Cellular Satellite Satellites optimization algorithm Power Generation Radiators

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Aeroelastic tailoring of composite structures

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JOURNAL OF AIRCRAFT 1999年第6期36卷 1041-1047页

作者： Eastep, FE Tischler, VA Venkayya, VB Khot, NS Univ Dayton Dept Mech & Aerosp Engn Dayton OH 45469 USA USAF Res Lab Air Vehicle Directorate Struct Div Wright Patterson AFB OH 45433 USA

A wing-design optimization study is conducted on a composite wing. The objective is to evaluate the effect of the composite layup orientation on the optimized weight while satisfying constraints on strength, roll-reversal velocity, and flutter velocity. The wing optimization studies are presented with the composite layups oriented at 5-deg increments up to +/-20 deg from the midspar of the wing. The multidisciplinary optimization system, ASTROS, was used in the design study. This study, although not conclusive, indicates that optimal designs when subjected to multiple structural constraints are relatively insensitive to the orientation of the laminate layup.

关键词： Composite Structures Control Surfaces Stiffness Matrices Center of Pressure Freestream Velocity Angle of Attack Structural Analysis Aspect Ratio optimization algorithm Sensitivity Analysis

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Multiple rigid-body reorientation using relative motion with constrained final system configuration

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JOURNAL OF GUIDANCE CONTROL AND DYNAMICS 1999年第3期22卷 441-446页

作者： Rubenstein, DS Melton, RG Charles Stark Draper Lab Inc Guidance Navigat & Control Directorate Cambridge MA 02139 USA Penn State Univ Dept Aerosp Engn University Pk PA 16802 USA

Moveable appendages in multibody spacecraft can augment or replace the attitude control actuators. In this work, motions of the movable bodies relative to the main body are used to adjust the system's inertial attitude so as to approach or attain a desired target attitude. A control algorithm designed to generate the maneuver commands that cause the necessary relative motions is tested with several cases representing a variety of dynamic conditions. The control can accommodate many different system configurations and dynamic conditions such as nonzero system momentum, a problem that historically has proved difficult to solve in a generalized, three-dimensional mode. Additionally, the control can return the system's geometric configuration to its initial state by the conclusion of the reorientation. The results indicate that the control can accomplish nearly complete reorientations in all cases tested while meeting the system constraints.

关键词： Attitude Control System Control algorithm Actuators Quaternions Numerical optimization Multibody Simulation Propellant Spacecraft Attitude Control optimization algorithm Spacecraft System

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Using the two-branch tournament genetic algorithm for multiobjective design

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AIAA JOURNAL 1999年第2期37卷 261-267页

作者： Crossley, WA Cook, AM Fanjoy, DW Venkayya, VB Purdue Univ Sch Aeronaut & Astronaut W Lafayette IN 47907 USA USAF Res Lab Struct Div Wright Patterson AFB OH 45433 USA

The two-branch tournament genetic algorithm is presented as an approach to determine a set of Pareto-optimal solutions to multiobjective design problems. Because the genetic algorithm searches using a population of points rather than using a point-to-point search, it is possible to generate a large number of solutions to multiobjective problems in a single run of the algorithm. The two-branch tournament and its implementation in a genetic algorithm (GA) to provide these solutions are discussed. This approach differs from most traditional methods for GA-based multiobjective design;it does not require the nondominated ranking approach nor does it require additional fitness manipulations. A multiobjective mathematical benchmark problem and a 10-bar truss problem were solved to illustrate how this approach works for typical multiobjective problems. These problems also allowed comparison to published solutions. The two-branch GA was also applied to a problem combining discrete and continuous variables to illustrate an additional advantage of this approach for multiobjective design problems. Results of all three problems were compared to those of single-objective approaches providing a measure of how closely the Pareto-optimal set is estimated by the two-branch GA. Finally, conclusions were made about the benefits and potential for improvement of this approach.

关键词： Genetic algorithm Trusses Young's Modulus Multidisciplinary Design optimization Structural optimization optimization algorithm Material Properties Composite Structures Axial Stress

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Framework for multidisciplinary design based on response-surface approximations

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JOURNAL OF AIRCRAFT 1999年第1期36卷 287-297页

作者： Batill, SM Stelmack, MA Sellar, RS Univ Notre Dame Notre Dame IN 46556 USA Summit Grp Inc Mishawaka IN 46545 USA

A framework has been proposed to allow for the multidisciplinary design of coupled, nonhierarchic systems. This approach is based on the ability to decompose a model-based analysis of a coupled system into subspaces or contributing disciplines. These subspaces are defined in terms of the design variables that they can influence and the information they contribute to the characterization of the complete system. The subspace coupling is based on the information they exchange. By using a set of response surface approximations, experts responsible for a particular subspace can make design decisions with the goals of improving the complete system merit and satisfying system constraints. Because design variables can be shared between subspaces, coordination of the subspace design decisions is achieved by the solution of a fully approximate optimization problem involving the complete set of system design variables. The implementation of this framework using two flight vehicle concept design problems is presented.

关键词： Model Based Analysis Flight Vehicle Artificial Neural Network Aerodynamic Force MDO optimization algorithm Structural Dynamics Airframes Iterative Solution Camber

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Creating time-optimal commands with practical constraints

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JOURNAL OF GUIDANCE CONTROL AND DYNAMICS 1999年第2期22卷 241-250页

作者： Tuttle, TD Seering, WP MIT Cambridge MA 02139 USA

In applications that demand rapid response, time-optimal control techniques are often enlisted. Recently, a new technique has been presented for deriving time-optimal command profiles by solving a set of algebraic constraint equations. This time-optimal solution framework is shown to be easily extendable to derive commands satisfying a variety of practical constraints, particularly constraints on command length and sensitivity to modeling errors.

关键词： Time Optimal Control Software Systems Data Management Structural Vibration optimization algorithm Rigid Body Dynamics Active Control Single Input Single Output Numerical Simulation Nonlinear Systems

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Robust design approach for achieving flexibility in multidisciplinary design

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AIAA JOURNAL 1999年第8期37卷 982-989页

作者： Chen, W Lewis, K Univ Illinois Dept Mech Engn Chicago IL 60607 USA SUNY Buffalo Dept Mech & Aerosp Engn Buffalo NY 14260 USA

The interdisciplinary nature of complex systems design presents challenges associated with computational burdens and organizational barriers as these issues cannot be resolved with faster computers and more efficienta* optimization algorithms. There is a need to develop design methods that can model different degrees of collaboration and help resolve the conflicts between different disciplines. An approach to providing flexibility in resolving the conflicts between the interests of multiple disciplines is proposed. We propose to integrate the robust design concept into game theory protocols, in particular the Stackelberg leader/follower protocol. Specifically, the solution for the design parameters that involve the coupled information between multiple players (disciplines) is developed as a range of solutions rather than a single point solution. This additional flexibility provides more freedom to the discipline that takes the role of follower, while also keeping the performance of the leader discipline stable within a tolerable range. The method is demonstrated by a passenger aircraft design problem.

关键词： Robust Design Lift to Drag Ratio Aerodynamics Fuselages Multidisciplinary Design optimization optimization algorithm Robust Design Methods Aircraft Design Wing Span Monte Carlo Simulation

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Improved formulation for geometric properties of arbitrary polyhedra

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AIAA JOURNAL 1999年第10期37卷 1326-1327页

作者： Wang, ZJ CFD Res Corp Huntsville AL USA

Focuses on a study which showed the derivation of a cell centroid of an N-faced polyhedron for which each face is an arbitrary planar polygon. Formulation of face properties; Conclusions.

关键词： Numerical Integration Aerodynamic Performance Aerodynamic Design National Aerospace Laboratories optimization algorithm Wing Root Aeroplane Numerical optimization Spline Interpolation Parallel Computers

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