检索结果-内蒙古大学图书馆

Toward a Science of Command, Control, and Communications

丛书名： Progress in Astronautics and Aeronautics

1993年

作者： Carl Jones

ISBN: (数字)9781600866296

ISBN: (纸本)9781563470684

To properly engineer systems to provide unity of effort in command and control systems, it is necessary to have a science of command, control, and communications (C3). This book, the results of the Joint Directors of Laboratories Basic Research Group Program, is a collection of papers toward the goal of a science of C3. The topics include the logic of data fusion, command and control decision systems modeling and behavior, experimental findings, models of command and control, and models of C3 architectures. This variety provides the reader with state-of-the-art perspective on concepts, models, and experiments to understand command, control, and communications. The results of a focused DoD basic research program in command, control and communications will be of particular interest to professionals and students working in the C3 field.

关键词： Aeronautics Air Traffic Control Air Traffic Management algorithms and Data Structures Anti-Submarine Warfare Applied Mathematics Artificial Intelligence Artillery Systems Aviation Aviation Communication Avionics Combat Aircraft Communication System Computational Fluid Dynamics Computer Programming and Language Computing and Informatics Computing, Information, and Communication Control Systems Control Theory Data Analysis Data Analytics Data Management Data Processing Data Science Databases Defense Agencies Evolutionary algorithm Fluid Dynamics General Physics Genetic algorithm Guidance, Navigation, and Control Systems Guided Missiles Information System Kalman Filter Machine Learning Major Command Military Aircraft Military Aviation Military Science Military Technology Missile Defense Missile Guidance and Control Missile Systems, Dynamics and Technology Missiles Navigational Guidance Non-Combat Aircraft Numerical Analysis Operating Systems optimization algorithm RADAR Robotics Sensors Signal Processing Software Systems Statistical Analysis Structural Analysis Structural Engineering Structural Modeling and Simulation Structures, Design and Test Systems Software Tracking and Positioning Systems Transducers United States Air Force United States Armed Forces Warfare and Military Operations Weapon Systems

来源：评论

学校读者我要写书评

暂无评论

INDICIAL LIFT APPROXIMATIONS FOR 2-DIMENSIONAL SUBSONIC FLOW AS OBTAINED FROM OSCILLATORY MEASUREMENTS

引用

JOURNAL OF AIRCRAFT 1993年第3期30卷 340-351页

作者： LEISHMAN, JG University of Maryland at College Park College Park Maryland 20742

An approach is described to obtain generalized approximations to the indicial lift response due to angle of attack and pitch rate in two-dimensional subsonic flow. Starting from an assumed representation, the approximations are accomplished by means of a nongradienta* optimization algorithm in which the coefficients of the approximation are free parameters. The optimization is subject to prescribed constraints in terms of the known initial and asymptotic behavior of the indicial response, and by requiring the response duplicate the known exact (analytic) solutions at earlier values of time. The approach is applied to extract the intermediate forms of the indicial lift response, generalized in terms of Mach number and pitch axis location, from experimental measurements of the unsteady lift in the frequency domain.

关键词： Incompressible Flow Freestream Mach Number Lift Coefficient Frequency Domain optimization algorithm Cambered Airfoil Wake Vortices Blade Vortex Interaction Compressibility Aeroelastic Analysis

来源：评论

学校读者我要写书评

暂无评论

DISCRETE-TIME MODEL-REDUCTION IN LIMITED FREQUENCY RANGES

引用

JOURNAL OF GUIDANCE CONTROL AND DYNAMICS 1993年第6期16卷 1125-1130页

作者： HORTA, LG JUANG, JN LONGMAN, RW NASA Langley Research Center Hampton Virginia 23665

A mathematical formulation for model reduction of discrete-time systems such that the reduced-order model represents the system in a particular frequency range is discussed. The algorithm transforms the full-order system into balanced coordinates using frequency-weighted discrete controllability and observability grammians. In this form a criterion is derived to guide truncation of states based on their contribution to the frequency range of interest. Minimization of the criterion is accomplished without need for numerical optimization. Balancing requires the computation of discrete frequency-weighted grammians. Closed-form solutions for the computation of frequency-weighted grammians are developed. Numerical examples are discussed to demonstrate the algorithm.

关键词： Numerical optimization Frequency Response Functions Spacecraft Dynamics Singular Value Decomposition White Noise optimization algorithm Lyapunov Equation Aerospace Engineering Cost Analysis

来源：评论

学校读者我要写书评

暂无评论

OPTIMAL RECOVERY FROM MICROBURST WIND SHEAR

引用

JOURNAL OF GUIDANCE CONTROL AND DYNAMICS 1993年第6期16卷 1010-1017页

作者： MULGUND, SS STENGEL, RF Princeton University Princeton New Jersey 08544

The flight path of a twin-jet transport aircraft is optimized in a microburst encounter during approach to landing. The objective is to execute an escape maneuver that maintains safe ground clearance, establishes a positive climb rate as soon as possible after the abort is triggered, and maintains an adequate stall margin during the climb out. A cost function penalizing rate of climb deviations from a nominal value and rate of elevator deflection produces qualitatively good results in a variety of microburst encounters. The optimal maneuver is a gradual pitch-up that ceases near the core of the microburst, followed by a slight reduction in pitch attitude in the tailwind area of the microburst. A minimum airspeed constraint in the optimization prevents excessive airspeed loss in very severe microbursts. The aircraft equations of motion include short-period dynamics, so that the optimization produces the control surface deflections required to achieve the optimal flight paths.

关键词： Microburst Rate of Climb Elevator Deflection Elevator Transport Aircraft Trajectory optimization Pilot optimization algorithm Feedback Control Aerodynamic Coefficients

来源：评论

学校读者我要写书评

暂无评论

OPTIMAL SELECTION OF WEIGHTING MATRICES IN INTEGRATED DESIGN OF STRUCTURES CONTROLS

引用

AIAA JOURNAL 1993年第4期31卷 714-720页

作者： SUNAR, M RAO, SS Purdue University West Lafayette Indiana 47907

A methodology is developed for the optimal selection of state and input weighting matrices, Q and R, respectively, of the linear quadratic regulator (LQR) method in the integrated design of structures/controls. An optimal control problem is set up in such a way that design variables are the diagonal entries of Q and R, the objective function is the trace of the solution matrix to the algebraic Riccati equation of the LQR method, P matrix;and constraints are imposed on the closed-loop eigenvalues to satisfy minimum stability conditions for the control system. The procedure finds the optimal diagonal Q and R that enables the actively controlled system to meet the prespecified stability and performance bounds. Furthermore, the resulting Q and R yield the minimum possible performance index and hence the control effort is substantially reduced. The proposed method is integrated with a substructure decomposition scheme which results in substantial savings on the numerical computations with very little loss in the accuracy of the original system response. It is found that for trusslike space structures, the proposed optimization scheme is mostly affected by the changes in the diagonal terms of R and the changes in the velocity diagonal terms of Q of the controlled system. The method is expected to be very useful for large-scale systems and is illustrated with the help of two example problems.

关键词： Linear Quadratic Regulator Trusses Flexible Structures Structural Modeling Algebraic Riccati Equation Multivariable Control Stiffness Matrices Vibration Suppression Young's Modulus optimization algorithm

来源：评论

学校读者我要写书评

暂无评论

COMPUTATION OF MAXIMIZED GUST LOADS FOR NONLINEAR AIRCRAFT USING MATCHED-FILTER-BASED SCHEMES

引用

JOURNAL OF AIRCRAFT 1993年第5期30卷 763-768页

作者： SCOTT, RC POTOTZKY, AS PERRY, B NASA Langley Research Center Hampton Virginia 23681 Lockheed Engineering and Sciences Company Hampton Virginia 23665

This article describes and illustrates two matched-filter-theory-based schemes for obtaining maximized and time-correlated gust loads for a nonlinear airplane. The first scheme is computationally fast because it uses a simple one-dimensional search procedure to obtain its answers. The second scheme is computationally slow because ft uses a more complex multidimensional search procedure to obtain its answers, but it consistently provides slightly higher maximum loads than the first scheme. Both schemes are illustrated with numerical examples involving a nonlinear control system.

关键词： Mach Number Model Aircraft Nonlinear Control Atmospheric Turbulence Nonlinear Systems optimization algorithm Computing Federal Aviation Administration Linear Quadratic Gaussian Aeroservoelasticity

来源：评论

学校读者我要写书评

暂无评论

Introduction to Dynamics and Control of Flexible Structures

引用

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

来源：评论

学校读者我要写书评

暂无评论

optimization Of Observation And Control Processes

引用

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

来源：评论

学校读者我要写书评

暂无评论

AERODYNAMIC SHAPE DESIGN AND optimization - STATUS AND TRENDS

引用

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

来源：评论

学校读者我要写书评

暂无评论

DEMONSTRATION OF STRUCTURAL optimization APPLIED TO WIND-TUNNEL MODEL DESIGN

引用

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

来源：评论

学校读者我要写书评

暂无评论

建议与咨询留下您的常用邮箱和电话号码，以便我们向您反馈解决方案和替代方法

时间限定

文献类型

馆藏选择

核心期刊

语言

文献类型

帮助

文字说明：

检索规则说明：

检索范例：

分类表

所选分类

限定检索结果

文献类型

馆藏范围

日期分布

学科分类号

主题

机构

作者

语言

请选择保存的检索档案：

请选择收藏分类：

通借通还

建议与咨询 留下您的常用邮箱和电话号码，以便我们向您反馈解决方案和替代方法

时间限定

文献类型

馆藏选择

核心期刊

语言

文献类型

帮助

文字说明：

检索规则说明：

检索范例：

分类表

所选分类

限定检索结果

文献类型

馆藏范围

日期分布

学科分类号

主题

机构

作者

语言

请选择保存的检索档案： 新增检索档案 确定 取消

请选择收藏分类： 新增自定义分类 确定 取消

通借通还

建议与咨询留下您的常用邮箱和电话号码，以便我们向您反馈解决方案和替代方法

请选择保存的检索档案：

请选择收藏分类：