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Introduction to Dynamics and Control of Flexible Structures

丛书名： AIAA Education Series

1993年

作者： John L. Junkins Youdan Kim

ISBN: (数字)9781600862076

ISBN: (纸本)9781563470547

Effective control laws for mechanical systems are best designed by professionals who understand both the basic mechanics of the system under consideration and the control methodology being used to design the control law. This textbook blends two traditional disciplines: engineering mechanics and control engineering. Beginning with theory, the authors proceed through computation to laboratory experiment and present actual case studies to illustrate practical aerospace applications. Intended for first-year graduate students in engineering and applied science, this book will help structural dynamists and control engineers gain broad competence in mechanics and control. A solutions manual is available for professors.

关键词： Aeronautics algorithms and Data Structures Applied Mathematics Autonomous Systems Avionics Avionics Computers Beam (Structures) Classical Mechanics Computational Fluid Dynamics Computer Networks Computer Programming and Language Computer Storage Devices Computing System Computing and Informatics Computing, Information, and Communication Control Systems Control Theory Data Science Elementary Algebra Embedded Systems Energy Energy Forms Energy Forms, Production and Conversion Feedback Control Finite Element Method Flexible and Active Structures Fluid Dynamics General Physics Geometry Functions Guidance, Navigation, and Control Systems Inverse Problems Kalman Filter Mathematical Analysis Mathematical optimization Mechanical and Structural Vibrations Numerical Analysis Optimal Control Theory optimization algorithm Riccati Equations Robotics Robots Sensors Signal Processing Spacecraft Guidance and Control Structural Analysis Structural Design and Development Structural Engineering Structural Kinematics and Dynamics Structural Modeling and Simulation Structural System Structures, Design and Test Transducers Vibration Control

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optimization Of Observation And Control Processes

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丛书名： AIAA Education Series

1992年

作者： Mihkail Naumovi Krasilshikov Veniamin Vasily Malyshev Valeri Ivanovic Karlov

ISBN: (数字)9781600862229

ISBN: (纸本)9781563470400

This book generalizes the classic theory of the regression experiment design in the case of Kalman-type filtering in controllable dynamic systems. A new approach is proposed for optimization of the measurable parameters structure, of navigation mean modes, of the observability conditions, of inputs for system identification, etc. The developed techniques are applied for enhancing efficiency of spacecraft navigation and control.

关键词： Acoustic Noise Acoustics Aerospace Sciences algorithms and Data Structures Applied Mathematics Astrodynamics Astronautics Boundary Element Method Computational Fluid Dynamics Computing and Informatics Computing, Information, and Communication Continuum Mechanics Control Systems Control Theory Coordinate System Data Science Design of Experiments Elementary Algebra Fluid Dynamics General Physics Guidance, Navigation, and Control Systems Inverse Problems Kalman Filter Materials and Structural Mechanics Mathematical optimization Mechanical and Structural Vibrations Meteoroids Monte Carlo Method Nonlinear Control Theory Numerical Analysis Optimal Control Theory optimization algorithm Orbital Maneuvers Planetary Science and Exploration Planets Riccati Equations Satellites Solar Physics Solar Wind Solid Mechanics Space Orbit Space Science and Technology Space Systems and Vehicles Spacecraft Design Spacecraft Guidance Spacecraft Guidance and Control Spacecrafts Statistical Analysis Structural Design and Development Structural Engineering Structural Mechanics Structures, Design and Test Vibration Measuring Instruments

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AERODYNAMIC SHAPE DESIGN AND optimization - STATUS AND TRENDS

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JOURNAL OF AIRCRAFT 1992年第6期29卷 1020-1026页

作者： DULIKRAVICH, GS Pennsylvania State University University Park Pennsylvania 16802

A limited number of aerodynamic shape design concepts have been surveyed and an attempt has been made to classify them. Characteristics, both positive and negative, of the more prominent methods were outlined. Future research is expected to concentrate on the use of Navier-Stokes equations and applications to three-dimensional configurations. Interdisciplinary constrained optimization is expected to play a more prominent role in the immediate future. Adjoint operator/control theory and its variations are the most promising concepts for interdisciplinary aerodynamic shape design which involves a large number of variables. This theory is expected to constitute the major development area in future research.

关键词： Control Theory Navier Stokes Equations Aerodynamic Configurations Incompressible Viscous Flow Wing Body Combination Sensitivity Analysis Angle of Attack Turbomachinery Cascades Aeroplane optimization algorithm

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SHAPE-SENSITIVITY ANALYSIS AND DESIGN optimization OF LINEAR, THERMOELASTIC SOLIDS

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AIAA JOURNAL 1992年第2期30卷 528-537页

作者： HOU, GJW SHEEN, JS CHUANG, CH Old Dominion University Norfolk Virginia 23529

In this study, a numerical scheme is developed for shape-sensitivity analysis and design optimization of linear, quasistatic, thermoelastic solids. In this scheme, the finite-element method is used as the analyzer for analyzing stress, temperature, shape sensitivity, and design velocity field. Based upon the method of material derivatives, both the techniques of the direct-differentiation method and the adjoint-variable method are applied to derive the shape-sensitivity equations. The shape-optimization formulations discussed here include boundary integrals of displacements and heat fluxes as well as domain integrals of stresses and areas. Numerical results show that the proposed scheme works well in terms of accuracy.

关键词： Mixed Boundary Condition Finite Element Modeling Material Derivatives Fixed Beam Shape optimization Thermal Stress Analysis Thermal Boundary Condition optimization algorithm Material Properties Thermal Insulation

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DEMONSTRATION OF STRUCTURAL optimization APPLIED TO WIND-TUNNEL MODEL DESIGN

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JOURNAL OF AIRCRAFT 1992年第5期29卷 966-968页

作者： FRENCH, M KOLONAY, RM Wright Laboratory Wright-Patterson Air Force Base Ohio 45433

One of the most important tasks in the design of an aeroelastically scaled wind-tunnel model wing is making sure the stiffness charactersistics are correct. The engineer must design a model structure whose stiffness characteristics match known values. These known values are derived by scaling the stiffness characteristics of the full-size structure that the model represents. In the paper a general purpose finite element based analysis and optimization program was used to design a structure made up of beam and plate elements. Using only the widths of the beam elements as design variables, a design was obtained that satisfied the stiffness constraints, and a sample structure was manufactured.

关键词： Wind Tunnel Models Structural optimization Finite Element Modeling Aeroelastic Models Beam (Structures) optimization algorithm Composite Materials Aerospace Engineering Lift Coefficient Wing Geometry

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MULTIDISCIPLINARY optimization OF AEROSERVOELASTIC SYSTEMS USING REDUCED-SIZE MODELS

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JOURNAL OF AIRCRAFT 1992年第5期29卷 939-946页

作者： KARPEL, M Technion—Israel Institute of Technology Haifa 32000 Israel

Efficient analytical and computational tools for simultaneous optimal design of the structural and control components of aeroservoelastic systems are presented. The optimization objective is to achieve aircraft performance requirements and sufficient flutter and control stability margins with a minimal weight penalty and without violating the design constraints. Analytical sensitivity derivatives facilitate an efficient optimization process that allows a relatively large number of design variables. Standard finite element and unsteady aerodynamic routines are used to construct a modal data base. Minimum-state aerodynamic approximations and dynamic residualization methods are used to construct a high-accuracy, low-order aeroservoelastic model. Sensitivity derivatives of flutter dynamic pressure, control stability margins, and control effectiveness with respect to structural and control design variables are presented. A gradient-based constrained optimization algorithm is used to minimize an overall cost function. A realistic numerical example of a composite wing with four controls is used to demonstrate the modeling technique, the optimization process, and their accuracy and efficiency.

关键词： Aeroservoelastic Systems Dynamic Pressure Control optimization optimization algorithm Aircraft Performance Finite Element Modeling Structural optimization Fuselages Nastran Aerodynamic Force Coefficients

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GENERALIZED COMPOUND SCALING algorithm AND APPLICATION TO MINIMUM WEIGHT DESIGN OF PLATE STRUCTURES

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AIAA JOURNAL 1992年第10期30卷 2532-2539页

作者： GRANDHI, RV VENUGOPAL, NS VENKAYYA, VB WRIGHT LAB WRIGHT PATTERSON AFB OH 45433 USA

This paper presents the generalized compound scaling algorithm and its application to optimum weight design of plate structures. The optimum designs are reached by simply scaling the design variables to an optimum intersection of multiple constraints. A four-noded isoparametric plate element is used for modeling the structure. Sensitivity computations and the optimization algorithm are discussed. The optimization cost involved (excluding the finite element analyses) is very small using this algorithm. The procedure is demonstrated on three example problems using stress and displacement constraints with side bounds on the design variables.

关键词： algorithms and Applications optimization algorithm Finite Element Modeling Transverse Shear Sensitivity Analysis Structural optimization Material Properties Cantilever Beam Nastran Structural Weight

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MAXIMUM LIFE SPUR GEAR DESIGN

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JOURNAL OF PROPULSION AND POWER 1992年第6期8卷 1273-1281页

作者： SAVAGE, M MACKULIN, BJ COE, HH COY, JJ NASA LEWIS RES CTRMECH SYST TECHNOL BRANCHCLEVELANDOH 44135

optimization procedures allow one to design a spur gear reduction for maximum life and other end-use criteria. A modified feasible directions search algorithm permits a wide variety of inequality constraints and exact design requirements to be met with low sensitivity to initial guess values. The optimization algorithm is described and the models for gear life and performance are presented. The algorithm is compact and has been programmed for execution on a desktop computer. In the program, the designer is given the opportunity to change the mathematical optimum to a more practical design for comparative evaluation. Two examples are presented to illustrate the method and its application.

关键词： Bending Fatigue optimization algorithm Search algorithm Fatigue Strength Lubrication Theory Gradient Method Shear Stress

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OPTIMUM DESIGN OF A COMPOSITE STRUCTURE WITH 3 TYPES OF MANUFACTURING CONSTRAINTS

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AIAA JOURNAL 1992年第6期30卷 1667-1669页

作者： WANG, BP COSTIN, DP University of Texas at Arlington Arlington Texas 76019

The application of composite materials to aircraft construction has provided the designer with increased flexibility. The purpose of this Note is to mathematically define manufacturing constraints needed to control ply orientation percentage, thickness variation, and interleaving of plies from two adjacent zones. The constraints were implemented in the ASTROS optimization code and applied to the design of the simple wing structure described in the ASTROS applications manual.

关键词： Composite Structures Finite Element Modeling Composite Laminates Structural Weight Aerodynamic Loads Thickness Ratio Aircraft Wings Structural optimization optimization algorithm Stress Concentration

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PARAMETRIC ROBUST-CONTROL BY QUANTITATIVE FEEDBACK THEORY

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JOURNAL OF GUIDANCE CONTROL AND DYNAMICS 1992年第1期15卷 207-214页

作者： NWOKAH, O JAYASURIYA, S CHAIT, Y TEXAS A&M UNIV SYST DEPT MECH ENGNCOLLEGE STNTX 77843 UNIV MASSACHUSETTS DEPT MECH ENGNAMHERSTMA 01003

The problem of performance robustness, especially in the face of significant parametric uncertainty, has been increasingly recognized as a predominant issue of engineering significance in many design applications. Quantitative feedback theory is very effective for dealing with this class of problems even when there exist hard constraints on closed-loop response. In this paper, single-input/single-output quantitative feedback theory is viewed formally as a sensitivity constrained multiobjective optimization problem whose solution cannot be obtained analytically but (when feasible) can be obtained graphically. In contrast to the more recent robust control methods where phase uncertainty information is often neglected, the direct use of parametric uncertainty and phase information in quantitative feedback theory results in a significant reduction in the cost of feedback. An example involving a standard quantitative feedback theory problem is included for completeness.

关键词： Quantitative Feedback Theory Single Input Single Output optimization algorithm Small Gain Theorem Frequency Domain Flight Envelope Flight Control Turbomachinery Engine Control Robust Design

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