From the Publisher: 
The accessible presentation of this book gives both a general view of the entire computer vision enterprise and also offers sufficient detail to be able to build useful applications. Users learn techniques that have proven to be useful by first-hand experience and a wide range of mathematical methods. A CD-ROM with every copy of the text contains source code for programming practice, color images, and illustrative movies. Comprehensive and up-to-date, this book includes essential topics that either reflect practical significance or are of theoretical importance. Topics are discussed in substantial and increasing depth. Application surveys describe numerous important application areas such as image based rendering and digital libraries. Many important algorithms broken down and illustrated in pseudo code. Appropriate for use by engineers as a comprehensive reference to the computer vision enterprise.

Computer vision : a modern approach = 计算机视觉 : 一种现代的方法

This book, written by two major figures in adaptive control, provides a wealth of material for researchers, practitioners, and students. While some researchers in adaptive control may note the absence of a particular topic, the book‘s scope represents a high-gain instrument. It can be used by designers of control systems to enhance their work through the information on many new theoretical developments, and can be used by mathematical control theory specialists to adapt their research to practical needs. The book is strongly recommended to anyone interested in adaptive control.

Adaptive Control

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Stable Adaptive Systems

With the capability of high speed flying, a more reliable and cost efficient way to access space is provided by hypersonic flight vehicles. Controller design, as key technology to make hypersonic flight feasible and efficient, has numerous challenges stemming from large flight envelope with extreme range of operation conditions, strong interactions between elastic airframe, the propulsion system and the structural dynamics. This paper briefly presents several commonly studied hypersonic flight dynamics such as winged-cone model, truth model, curve-fitted model, control oriented model and re-entry motion. In view of different schemes such as linearizing at the trim state, input-output linearization, characteristic modeling, and back-stepping, the recent research on hypersonic flight control is reviewed and the comparison is presented. To show the challenges for hypersonic flight control, some specific characteristics of hypersonic flight are discussed and the potential future research is addressed with dealing with actuator dynamics, aerodynamic/reaction-jet control, flexible effects, non-minimum phase problem and dynamics interaction.

An overview on flight dynamics and control approaches for hypersonic vehicles

An integrated autopilot and guidance algorithm is developed, using the sliding mode control approach, for a missile with forward and aft control surfaces. Based on guidance considerations, the zero efiort miss (ZEM), encountered in difierential games guidance solutions, is used as one of the sliding variables in the proposed control scheme. The dual control conflguration provides an additional degree of freedom in the integrated design. This degree of freedom is exploited by introducing a second sliding surface, selected based on autopilot design considerations. Restraining the system to the ZEM surface guarantees zero miss distance, while remaining on the second surface provides a damped response. The performance of the integrated dual controller is evaluated using a two-dimensional nonlinear simulation of the missile lateral dynamics and relative kinematics, assuming flrst order dynamics for the target evasive maneuvers. The simulation results validate the design approach of using ZEM and the ∞ight-control based sliding surfaces to attain high accuracy interceptions.

Integrated sliding mode autopilot-guidance for dual-control missiles

A new super convergent thin walled composite beam element for analysis of box beam structures

The goal of this study is the multi-mode structural vibration control in the composite fin-tip of an aircraft. Structural model of the composite fin-tip with surface bonded piezoelectric actuators is developed using the finite element method. The finite element model is updated experimentally to reflect the natural frequencies and mode shapes accurately. A model order reduction technique is employed for reducing the finite element structural matrices before developing the controller. Particle swarm based evolutionary optimization technique is used for optimal placement of piezoelectric patch actuators and accelerometer sensors to suppress vibration. H{infty} based active vibration controllers are designed directly in the discrete domain and implemented using dSpace® (DS-1005) electronic signal processing boards. Significant vibration suppression in the multiple bending modes of interest is experimentally demonstrated for sinusoidal and band limited white noise forcing functions.

Experimental Demonstration of H∞ Control based Active Vibration Suppression in Composite Fin-tip of Aircraft using Optimally Placed Piezoelectric Patch Actuators:

Variable Structure Controller Design with Application to Missile Tracking

This work presents a theoretical and experimental investigation of vibration control of composite box beams using distributed, surface mounted piezoelectric (PZT) patches as actuators. The finite element modeling of the box beam is done by formulating a first-order shear deformable active composite thin walled beam element. The degrees of freedom at each node are axial, bending in spanwise and chordwise directions, corresponding shears and twist. The superconvergent element derived uses higher order interpolating polynomials obtained by solving electromechanically coupled static governing differential equations. The open loop response is validated with experimental and analytical results available in the current literature. A system equivalent reduction expansion process (SEREP) is implemented for reduced order modeling. Open and closed loop responses to electrical bending actuation are obtained both experimentally and analytically using state space modeling. A proportional-integral (PI) controller using acceleration feedback is implemented for control of vibration due to single-frequency excitations. Experimental and numerical results correlate very well in the above cases. Eigenstructure assignment through output feedback is designed for multimodal control of transient responses.

https://iopscience.iop.org/article/10.1088/0964-1726/13/4/005/pdf

Vibration control in a composite box beam with piezoelectric actuators

The objective of this study is to determine an optimal trailing edge flap configuration and flap location to achieve minimum hub vibration levels and flap actuation power simultaneously. An aeroelastic analysis of a soft in-plane four-bladed rotor is performed in conjunction with optimal control. A second-order polynomial response surface based on an orthogonal array (OA) with 3-level design describes both the objectives adequately. Two new orthogonal arrays called MGB2P-OA and MGB4P-OA are proposed to generate nonlinear response surfaces with all interaction terms for two and four parameters, respectively. A multi-objective bat algorithm (MOBA) approach is used to obtain the optimal design point for the mutually conflicting objectives. MOBA is a recently developed nature-inspired metaheuristic optimization algorithm that is based on the echolocation behaviour of bats. It is found that MOBA inspired Pareto optimal trailing edge flap design reduces vibration levels by 73% and flap actuation power by 27% in comparison with the baseline design.

M. Seetharama Bhat

Papers

A new super convergent thin walled composite beam element for analysis of box beam structures

Experimental Demonstration of H∞ Control based Active Vibration Suppression in Composite Fin-tip of Aircraft using Optimally Placed Piezoelectric Patch Actuators:

Variable Structure Controller Design with Application to Missile Tracking

Vibration control in a composite box beam with piezoelectric actuators

Robust design of multiple trailing edge flaps for helicopter vibration reduction: A multi-objective bat algorithm approach